Form 9.B Project Summary

Chron:

970945

Proposal

Number:

01.01-3155A

Project Title:

Knowlede Complementarity Assessment

Program

Technical Abstract (Limit 200 words)

Intelligent Automation, Inc. will develop and

evaluate the "Knowledge Complementarity

Assessment Program" (KCAP), an automated

approach to assessing the effectiveness of

individual and crew/team training. KCAP is an

innovative combination of Latent Semantic Analysis

(LSA), a statistical procedure for text analysis, and

Intelligent Agents for Instruction (IAI), an

agent-based technology to optimize resource

selection for instruction. KCAP assesses individual

and team performance and training requirements;

evaluates the relative merits of training resources

to enhance each team members' knowledge and

performance for these requirements; and provides

adaptive, individualized training for each team

member, based on their role in a team. KCAP is a

context-independent, low-cost alternative to

domain-specific intelligent tutors. It can be used

developmentally (to monitor and plan training as it

progresses), summatively (to evaluate the team and

individuals at the completion of a sequence) and to

monitor learning retention over time. We will

explore new methods of using KCAP to assess

team members' training during their performance of

real tasks. These advances supports NASA in

evaluating training effectiveness for individual/crew

performance, and in reducing error in tasks such as

aircraft maintenance. KCAP can develop into an

affordable new training and assessment technology,

suitable for use in many operational environments.

Potential Commercial Applications (Limit 200 words)

The proposed work will result in development of a

powerful technology that will be effective and

efficient in providing methods to assess the

effectiveness of training for groups or individuals,

and to use that information to guide training

programs. Using the Web, small training programs,

without sufficient financial resources to conduct

significant evaluation studies alone could use

KCAP through a "fee-for-service website."

Another product/service will be providing

KCAP-based validations of performance based

assessments, which could be provided through the

Web or through typical commercial software

distribution mechanisms. These will complement

IAI's other education and training-oriented Web

services and products.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Jacqueline A. Haynes

Intelligent Automation,Inc.

2 Research Place, Suite 202

Rockville , MD 20850

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Joseph E. Schwartz, Ph.D.

Intelligent Automation, Inc.

2 Research Place, Suite 202

Rockville , MD 20850

Form 9.B Project Summary

Chron:

970968

Proposal Number:

01.01-7100

Project Title:

Collaborative Decision Making

Airspace Visualization Tool

Technical Abstract (Limit 200 words)

This effort will develop a collaborative decision

making visualization

tool that will benefit dispatchers at Airline

Operations Centers

(AOCs), aircraft flight crews, Air Traffic

Management (ATM), and

scientific researchers who are designing decision

support systems for

these decision makers. As new Free Flight

procedures remove jetway

routing, positive control, and other constraints, an

added emphasis

will be placed on collaborative ATM techniques and

distributed

control. Our innovation provides a visual tool for

monitoring

information and collaborating with a common visual

model. This tool

can assist in keeping track of aircraft, negotiating

conflict

detection and resolution options, observing weather

systems and

special use airspace constraints, and viewing

operations data - these

data are dynamic and originate from multiple

sources. Before any of

Free Flight changes take place, scientific

researchers can use this

tool to visualize solutions to problems associated

with the AOC, the

flight crew, and the ATM system. Additionally,

researchers may

visualize conflict detection and resolution results for

analysis, and

evaluate distributed systems concepts like

collaborative decision

making. This visualization tool will assist NASA

achieve effective

and safe control of multiple aircraft in the National

Airspace System

(NAS) through the visual integration of air and

ground-based air

traffic information.

Potential Commercial Applications (Limit 200 words)

The commercial potential for a collaborative

decision making system is

very high because (a) air traffic continues to grow

worldwide and the

demand for more timely, efficient, reliable air travel

is strong on

the part of the airlines and the traveling public; and

(b) the trend

in air traffic control is towards giving airlines more

and more

autonomy while maintaining safety. The FAA,

CAAs, airlines and other

fleet operators will require collaboration tools to

assist with

providing Free Flight operations.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jimmy Krozel, Ph.D.

Seagull Technology, Inc.

16400 Lark Avenue

Los Gatos , CA 95032-2547

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Jan Betke

Seagull Technology, Inc.

16400 Lark Avenue

Los Gatos , CA 95032-254

Form 9.B Project Summary

Chron:

971184

Proposal Number:

01.02-3474

Project Title:

Air Traffic Controller Agent Model for

Free Flight

Technical Abstract (Limit 200 words)

We propose to examine the human factors needs of

air traffic controllers operating under free flight

through the development of a modeling and analysis

tool based on an agent representation of the overall

controller/air traffic system. The approach relies on

a multi-stage agent-based representation of the

controller's SA and decision-making behavior, and

a multidimensional metric that reflects SA,

performance, and error propensity. We propose to

incorporate the controller agent into a simulated

free flight environment that contains a set of

semi-autonomous pilot agent models. Our objective

is to develop a simulation tool that will support the

development of rules and procedures for free flight

implementation, via simulation-based analysis of

controller behavior and airspace system safety

under alternate free flight configurations. One of

the key innovative features of the resulting free

flight simulation tool is a distributed

decision-making model embedded into the

multi-agent architecture, which will provide air

traffic management system designers with a basis

for the formulation of effective decision allocation

between ground control and pilots in free flight.

Potential Commercial Applications (Limit 200 words)

The proposed technology will directly support

closing the human factors loop on the development

of free flight ATM concepts. The underlying

modeling approach will also support human factors

assessments in other domains (e.g., nuclear power

plants, chemical processing centers, power dispatch

stations, intelligent vehicle highway system control

centers, etc.) where it is desirable to determine how

system design affects operator awareness and

performance before committing to a specific

configuration. We also plan to extract the belief

network algorithm that emulates air traffic

controller situation assessment in the presence of

uncertainty, and develop a commercial-quality

software tool for computer-based reasoning under

uncertainty.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Sandeep M. Mulgund

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Greg L. Zacharias

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Form 9.B Project Summary

Chron:

971007

Proposal

Number:

01.02-6070

Project Title:

A Turbulence/Vortex Detection System

Using Optical Scintillation Techniques

Technical Abstract (Limit 200 words)

NASA, FAA, and U.S. Air Force have identified the

need to detect the aircraft trailing wake turbulence

generated by aircraft during take-off and landing

operations. At the present time, one of the major

problems of wake turbulence assessment is the lack

of an operational system to measure it in real-time.

As a result, FAA instituted operational and physical

guidelines to reduce the vortex wake hazard. These

conservative procedures put extra limits on airport

capacity and efficiency.

Scientific Technology, Inc. (ScTi) proposes to

develop a vortex/ turbulence detection system

including a set of scintillometers deployed in the

airport to measure ground and near ground runway

crosswind, turbulence, and wake vortex using

atmospheric turbulence- induced optical

scintillations. ScTi will perform system analysis and

design of the proposed system to detect

occurrences, location, magnitude, and persistence

of wake turbulence. With the simultaneous

measurements of crosswind and turbulence, the

sensor may even be able to forecast the arrival

time of the airplane generated wake vortex drifting

to a nearby runway. Successful development of the

system will serve as a decision support tool to ATC

for the next generation Air-Traffic Management

system to accommodate growth in air traffic while

reducing the aircraft accident rate.

Potential Commercial Applications (Limit 200 words)

Accurate crosswind, turbulence, and wake vortex

measurements are critical for improving airport

safety and efficiency. Successful development of

the proposed sensor technology will lead to the

large scale deployment of the proposed systems at

commercial and military airports around the world.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Ting-i Wang

Scientific Technology, Inc.

205 Perry Parkway, Suite 14

Gaithersburg , MD 20877

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Chung-Dyi Hsu

Scientific Technology, Inc

205 Perry Parkway, Suite 14

Gaithersburg , MD 20877

Form 9.B Project Summary

Chron:

971402

Proposal

Number:

01.02-7569A

Project Title:

Navigation and Situation Awareness for

Landing and Runway Crossing

Technical Abstract (Limit 200 words)

Faced with a projected increase in air traffic in

excess of 30% in the United States over the next

decade, government agencies such as NASA and

the Federal Aviation Administration (FAA) are

developing advanced technologies to increase

traffic-handling capacity at existing airports. Efforts

to increase airport capacity approach the problem

on two fronts: the first obvious solution is to

increase the number of runways (i.e. quantity), and

the second approach is to develop new technologies

to achieve reduction in aircraft separation and

consequently a corresponding increase in landing

rate per runway (i.e. efficiency). Both approaches

have to be accomplished without compromising

safety. The first approach based on increasing

usable runways also imposes new technical

problems. Modifying an existing airport layout

increases surface traffic complexity with increased

volume of aircraft and surface vehicle traffic,

resulting in increased occurrences of runway

crossing. The innovations advanced in this proposal

include both automatic and manual control of the

aircraft for runway crossing that will be tightly and

seamlessly integrated with products currently being

developed under the NASA TAP program. In

addition, the proposed effort includes performance

and benefit analyses to identify the maximum

possible capacity impact, and the potential

achievable benefits from such technologies.

Potential Commercial Applications (Limit 200 words)

Like most of the products being developed under

the NASA Terminal Area Productivity program, the

technologies developed under this SBIR proposal

are targeted for civil aviation. As the global travel

volume increases and the major airports execute

their plans to increase capacity through expansion,

runway crossing will quickly become a major issue

at these airports. The technologies to be developed

under this SBIR will be useful for developing new

avionics systems for improving ground traffic.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Victor H.L. Cheng

Optimal Synthesis

450 San Antonio Road, Suite 46

Palo Alto , CA 94306-4638

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. P.K. Menon

Optimal Synthesis

450 San Antonio Road, Suite 46

Palo Alto , CA 94306-4638

Form 9.B Project Summary

Chron:

970768

Proposal Number:

01.02-8123

Project Title:

SafePath for Airport Surface

Movement

Technical Abstract (Limit 200 words)

Safety and efficiency are primary concerns in the

planning and conduct of vehicle movement on the

airport surface area; yet in many areas of

transportation management and system logistics,

safety and efficiency are competing goals. During

this Phase I SBIR effort Wyndemere Incorporated

proposes to study a system that will meet these two

challenges in a complementary manner through the

development of a detailed plan for airport surface

movement. This plan, formulated through

constraint-based optimization methods to increase

efficiency, will also allow warnings to be issued

when vehicles deviate from the plan, rather than

when an incursion or incident is imminent. The

innovation proposed is the research and prototyping

of a constraint-satisfaction based algorithm for the

generation of efficient airport surface movement

paths. This innovation will provide the fundamental

technology for a complete decision support system

to increase both safety and efficiency in airport

surface movement, considering aircraft and other

airport vehicles during normal, low-visibility and

emergency conditions. This technology will fit well

with NASA's Surface Movement Advisor project

and the recent demonstration of the Low Visibility

Landing and Surface Operations program at

Atlanta's Hartsfield Airport.

Potential Commercial Applications (Limit 200 words)

Technology aimed at increasing the safety and

efficiency of airport surface movement is in rising

demand. The United States has set aggressive

goals for the reduction of the aviation accident rate

in general, and runway incursions in particular. It is

expected that significant investment in safety

improvements will be made by the US government

and international aviation authorities over the next

few years. For airlines and air cargo operators,

ground movement efficiency is a major cost

concern; potential losses from aviation delays

creates a strong market for technology and

products that can increase the efficiency of airport

surface operations. In this regard, Wyndemere has

been working cooperatively with Federal Express to

identify the characteristics of traffic flow, airspace,

airport layout and air traffic control procedures that

contribute to inefficiency in their air cargo

operation. FedEx is interested in supporting the

research, development and use of this proposed

technology at Memphis International Airport, and

in-kind contributions have been committed to

Wyndemere by FedEx to support this Phase I SBIR

study.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

William S. Pawlak

Wyndemere Incorporated

660 Northstar Court

Boulder , CO 80304

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Susan S. Nedell

Wyndemere Incorporated

660 Northstar Court

Boulder , CO 80304

Form 9.B Project Summary

Chron:

971050

Proposal Number:

01.04-4097

Project Title:

Multi-Formal Hardware Verification

System

Technical Abstract (Limit 200 words)

Levetate Design Systems, Inc., as the prime

contractor, and Derivation Systems, Inc., as a

subcontractor, propose to develop an advanced

system for verifying digital electronic hardware

systems. The system addresses the problem of

verifying gate- or register transfer-level design

models against abstract specifications represented

as state machines. Innovative aspects of this

system include: (I) new methods to address the

problem of state explosion in large systems, (ii) new

methods based on theorem proving algorithms

implemented as user- friendly tools featuring

automated operation, fast execution times, and

effective debug support, and (iii) new methods to

implement rigorous, proof-based verifications that

feature automated construction of the proof steps

required by existing mechanical proof checkers.

The proposed research addresses elements of

NASA subtopic 01.04, Reliable and Safety-Critical

Software, by constructing

automated tools to support developing

safety-critical systems. The objective of the

proposed research is to develop a verification

system into an advanced prototype suitable for beta

testing by the end of Phase II. The successful

completion of this goal would go a long way in

moving the electronics design industry towards

methods of greater rigor and automation.

Potential Commercial Applications (Limit 200 words)

The main commercial applications for our proposed

work are electronic design automation (EDA) tools

for digital hardware design and verification. The

commercial potential for tools offering this

combination of automation, verification speed, and

proof security is, conservatively, well above $100

million.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. David A. Fura

Levetate Design Systems, Inc.

4756 Univ. Village Pl. NE, #168

Seattle , WA 98105

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. David A. Fura

Levetate Design Systems, Inc.

4756 Univ. Village Pl. NE, #168

Seattle , WA 98105

Form 9.B Project Summary

Chron:

970624

Proposal Number:

01.06-1313

Project Title:

Wave Turbine Engines: Improvements

to an Existing Wave Turbine Test

Platform

Technical Abstract (Limit 200 words)

Wave rotors are a key technology to enable

significantly increased gas turbine peak

temperatures. Higher specific power results,

providing a more compact unit with the additional

benefit of increased efficiency. These benefits are

realized especially for small gas turbines since

self-cooling is a fundamental feature of the cycle.

Self-cooling is especially applicable to the

improvement of auxiliary power units (APU's) and

small turboshaft engines. Because the expansion

and compression processes occur on the same

rotor, part count and engine complexity is reduced.

The objective of the proposed research is to

determine the requirements for upgrading an

existing wave turbine and, in Phase II, fabricate and

test the resulting upgrades. The primary goal is to

design for improved start-up operation, addressing

an important issue in wave rotor engines. This wave

turbine, the only known operating engine of its

class, was recently resurrected, meticulously

characterized, and partially tested to determine

problems, limitations, and requirements for

continued research. The proposed approach will

minimize the time and cost of developing this timely

technology for improving the APU's specific power,

efficiency, and simplicity. The upgraded

demonstration unit will serve as a research test

platform and an engine demonstration to encourage

commercialization by engine manufacturers.

Potential Commercial Applications (Limit 200 words)

Wave turbine engines have the potential to improve

a wide range of emgine products; in particular,

small engines for propulsion and power (i.e.,

auxiliary power units, APU's). Having established

its benefits in the small gas turbine market, wave

turbine engines can be expanded to larger power

class systems including off-the-road vehicles, high

bypass turbofans, and turboshaft engines.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

John F. Crittenden

UNISTRY Associates, Inc.

1901 Darby Road

Havertown , PA 19083

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Robert M. Carroll

UNISTRY Associates, Inc.

1901 Darby Road

Havertown , PA 19083

Form 9.B Project Summary

Chron:

971138

Proposal

Number:

01.07-0003

Project Title:

Active Combustion Control Using

Micro-Fabricated Sensors and Actuators

Technical Abstract (Limit 200 words)

Physical Sciences Inc. (PSI) proposes to develop a

closed-loop combustion control system for gas

turbine engines utilizing micro-fabricated sensors

and actuators. In previous and on-going work, PSI

has demonstrated the feasibility of active control

systems to suppress combustion instabilities and

improve combustor pattern factor, both of which can

lead to improved engine performance and

efficiency. The primary motivation for incorporating

micro-fabricated components into the system design

is to achieve a compact and highly-integrated

control system which is compatible with the size and

weight constraints of operating within a gas turbine

engine. Additionally, micro-fabricated components

have the potential to provide improved performance

over their macroscopic counterparts, allowing a

wider range of control strategies to be

implemented. PSI proposes to integrate a

micro-fabricated valve directly into a commercial

gas turbine fuel injector for active fuel flow control.

Additionally, strategies for actively controlling

spray patternation with embedded micro-actuators

will be developed. The active fuel injector designed

in the Phase I program will be fabricated and tested

in the Phase II program as part of an overall

combustion control system.

Potential Commercial Applications (Limit 200 words)

Successful development of the proposed technology

will represent one of the first commercial insertions

of micro-fabricated sensors and actuators in gas

turbine engines. A higher level of control over the

operation of gas turbine combustors will be

achieved with the proposed system, and along with

it, improvements in engine performance and

efficiency over the entire life of the engine. The

micro-actuator and sensor based combustion

control system also has the potential to lower the

costs of gas turbine engine development by relaxing

some of the constraints on the combustor design

process.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael F. Miller

Physical Sciences Inc.

20 New England Business Center

Andover , MA 01810

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

George E. Caledonia

Physical Sciences, Inc.

20 New England Business Center

Andover , MA 01810

Form 9.B Project Summary

Chron:

970195

Proposal Number:

01.07-8641

Project Title:

Hi Temp.Fiber Optic Eng.Mtd.

Ceramic Press. Transducer

Technical Abstract (Limit 200 words)

The demand of advanced aircraft propulsion

systems on sensor technologies to operate at

extended

temperature ranges has to date been primarily

focused on redesigning existing measurement

system

techniques. This proposed program will show the

feasibility of a new remote fly-by-light technology

made

possible by the availability of high temperature

air-clad sapphire optical fibers. The LEL concept

for

applying this technology to pressure and related

measurements is electrically passive-optically

active. No

electrically active parts reside in the sensor,

minimizing temperature effect on the sensor output.

The

sensor's input and output optical fibers can be

integrated in the engine's composite structure or

passed

through traditional wire ways to traditional

electronic components which are located remotely

from the

sensor. A primary feature of this new sensor design

concept is to measure differential motion as

opposed

to absolute motion, typical of diaphragm designs. A

properly designed differential motion sensor

measures only the input parameter not the side

effects caused by temperature and induced

stresses,

both static and dynamic. This fiber optic

miniaturized ceramic transducer is "Thermally

Hardened" by

material modifications allowing it to operate in a

high temperature (1000 degrees C) environment. It

does

not require active temperature compensation or

linearization to achieve specified accuracy.

Potential Commercial Applications (Limit 200 words)

The disclosed pressure transducer will provide an

essential input to an engine monitoring system

for the prediction of engine maintenance and stall.

In addition, this sensor technology can be used by

industries such as oil drilling, petrochemicals,

hydraulics, heavy construction equipment,

geothermal, geopressure wells, metal cutting, oceanography,

nuclear power plants and research organizations,

with similar gains in performance and reduced cost.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Charles A Liucci

LEL Corporation

5 Burns Place

Cresskill , NJ 07626

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Charles A Liucci

LEL Corporation

5 Burns Place

Cresskill , NJ 07626

Form 9.B Project Summary

Chron:

970576

Proposal

Number:

02.01-7115

Project Title:

Thin Film Sensors for Measurement of

Engine Emissions

Technical Abstract (Limit 200 words)

Emissions from aircrafts and automobiles are of

significant environmental concern. Various

communities are aggresively planning to set tighter

emission limits for exhausts including those from

aeronautical and aerospace operations. NASA's

goal is to reduce emissions of future aircrafts by a

factor of three within 10 years and five within 20

years. A key enabling technology for this goal are

exhaust sensors for NOx, SOx, HOx, atomic

oxygen, and hydrocarbons. Nanomaterials

Research Corporation (NRC) seeks to develop and

demonstrate nano-precision engineered sensors for

emissions monitoring. Phase I will systematically

establish the proof-of-concept; Phase II will

optimize, scale-up and fabricate prototype devices

for exhaust applications; Phase III will

commercialize the technology.

Potential Commercial Applications (Limit 200 words)

Emission sensors will enable intelligent operation of

sub-sonic engines to prevent pollution and to

increase fuel efficiencies. Spin-off applications

include emission sensors for catalyst monitors in

automobiles (mandated by law in the U.S., Japan,

and Europe), sensors for diesel engines and

turbines.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Charlie Xu, Ph.D.

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Tapesh Yadav, Ph.D.

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Form 9.B Project Summary

Chron:

971578

Proposal Number:

02.01-8614

Project Title:

A Catalytically Stabilized Lean Direct

Injection Combustor for Advanced

Subsonic Technology Emissions

Reduction

Technical Abstract (Limit 200 words)

A catalytic lean direct injection (LDI) design is a

practical approach for achieving NOx emissions

reduction for the Advanced Subsonic Technology

(AST) combustor. Our novel catalytic LDI design

integrates the underlying catalytic combustion

principles behind Precision Combustion's prior lean

premixed prevaporized(LPP)designs with effective

LDI principles applied to liquid fuels. This combines

the benefits of LDI, including avoiding preignition,

with the improved stability and ultra-low NOx

emissions of catalytically stabilized combustion.

Catalytic enhancement of flame stability offers

potential breakthroughs for NASA's advanced

subsonic program gas turbine engine through very

low pressure drop, high inlet duct velocity, high

turndown and stability, and low NOx at pressure.

Potential Commercial Applications (Limit 200 words)

High efficiency and low emissions are twin

objectives of future aerospace gas turbine engines.

This design approach contributes to these

objectives by enhancing stability, mixing, and

turndown of Lean Direct Injection Designs, offering

design flexibility to engine designers. This

combustor is being developed with a focus upon

ease of implementation into engine manufacturers

Advanced Subsonic Technology combustors

designs, and has the potential to create significant

value-added for the aircraft engine manufacturers.

Spinoff low NOx dual fuel stationary gas turbine

applications for this technology also show

significant promise.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Gilbert Kraemer

Precision Combustion, Inc.

25 Science Park, MS 24

New Haven , CT 06511-1968

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Paul Donahe

Precision Combustion, Inc

25 Science Park, MS 24

New Haven , CT 06511-1968

Form 9.B Project Summary

Chron:

971228

Proposal Number:

03.01-332

Project Title:

Rotorcraft Blade Vortex Interaction

Control with Induced-Strain Actuation

of Blade Twist

Technical Abstract (Limit 200 words)

Systems Planning and Analysis, Inc. (SPA)

proposes to develop a Mach-scaled smart

helicopter rotor with on embedded piezoceramic

elements for blade-vortex interaction (BVI) noise

reduction. SPA will use directionally attached

piezoceramics as actuators and sensors, for

closed-loop higher harmonic pitch control of the

main rotor blades. These pitch perturbations will

generate unsteady blade loads that would in turn

counteract loads generated by the BVI, with little

impact on the nominal steady-state rotor thrust. In

the proposed Phase I effort, SPA will use

Euler/Navier-Stokes computational fluid dynamics

(CFD) codes as a Òvirtual experimentÓ to examine

the 3-D interaction of a simplified vortex system

with a rotating blade (for low-speed descent flight)

and the associated aeroacoustic noise to establish

the required performance metrics (i.e., blade twist

deflection, actuator power, frequency response,

etc.) to reduce BVI by 10dB. The calculated leading

edge pressure differentials at several spanwise

stations in the outboard (60 to 90 percent of span)

region of the blade will be used as inputs to simple

control algorithms for determining the appropriate

twist actuation required for BVI noise suppression.

Finally, the CFD calculations will be repeated with

the variable twisting actuation to determine the

actual noise reduction achieved.

Potential Commercial Applications (Limit 200 words)

The successful development of a smart rotor

system will offer unprecedented benefits to military

and commercial rotorcraft. Reductions of BVI and

low frequency rotor noise (and the associated

higher-harmonic rotor vibrations) will reduce the

detectability of military platforms during Nap of

Earth (NOE) operations, while improving the rotor

performance for air-to-air combat. For commerical

rotorcraft, reductions in rotor noise would allow for

operation in urban environments with aircraft noise

restrictions. Furthermore, the reduction of harmonic

blade loads would reduce the maintenance

requirements and associated high cost of all

rotorcraft systems subject to premature failure of

rotor components due to high dynamic stresses.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Peter C. Chen, Ph.D.

Systems Planning and Analysis, Inc.

2000 N. Beauregard St. Suite 400

Alexandria , VA 22311

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Phillip E.Lantz

Systems Planning and Analysis, Inc.

2000 N. Beauregard St. Suite 400

Alexandria , VA 22311

Form 9.B Project Summary

Chron:

971171

Proposal Number:

03.02-0818

Project Title:

Advanced Prediction Tool for

Simulation of Turbomachinery Noise

Sources

Technical Abstract (Limit 200 words)

Serious concerns regarding the adverse

environmental impact of aircraft noise have led to

increasingly stringent regulations on the allowable

acoustic emissions from commercial transport

aircraft. To facilitate future growth in air

transportation while ensuring compliance with

international noise regulations, urgent attention to

noise prediction and reduction technologies is

required at this time. The perceived aircraft noise

levels during both takeoff and approach phases are

controlled by the turbomachinery noise, in

particular, its fan component. Here, an accurate yet

highly efficient numerical technique based on a

(high-order) computational aeroacoustics (CAA)

algorithm is proposed for simulating

turbomachinery noise. This approach is innovative

in tapping the potential of CAA to provide an

enhanced physical understanding of and integrated

prediction methodology for turbomachinery noise.

In addition to providing guidance and checks for

preliminary design tools, simulation tools of this

kind will minimize the overall design cycle time and

significantly enhance the competitiveness of U.S.

engine manufacturers in the global aviation market.

Potential Commercial Applications (Limit 200 words)

Turbomachinery design, engine noise reduction

technologies for subsonic commercial transports,

aerodynamic and aeroacoustic prediction, validation

of analytical prediction tools for turbomachinery

noise, computational electromagnetics, radar

detection and avoidance, wireless communications.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Meelan M. Choudhari

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mujeeb R. Malik

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

971349

Proposal Number:

03.02-8533

Project Title:

Active Control of Broadband

Rotor/Stator Noise in Turbofan

Engines

Technical Abstract (Limit 200 words)

The proposed innovation is a compact active control

system for reduction of tonal and broadband noise

radiated by rotor/stator interaction in turbofan

engines. The concept employs pressure transducers

on stators (outlet guide vanes) to capture signals

correlated with radiated noise. The signals are

processed and distributed to circumferential arrays

of actuators that serve as anti-sound sources to

cancel the rotor/stator noise. Circumferential

arrays of sensor microphones provide error signals

for the adaptive control system. Correlations

between stator vane fluctuating surface pressures

and radiated noise will be measured in the

NASA/LeRC ANCF fan to assess the feasibility of

the concept. Favorable results will lead to a

computer simulation of a simple active noise control

system and implementation of an in-situ

demonstration on the ANCF fan.

Potential Commercial Applications (Limit 200 words)

If successful, the proposed active noise control

system would suppress the lower frequency

(between 0.5 and 1.5 BPF) range of rotor/stator

noise. This would allow passive engine liners to

more effectively target high frequency noise in the

2 BPF to 4 BPF range and to be shallower, taking

less space.

The design concept of the system is such that the

actuator arrays could be integrated with active

control systems directed at tones.

There may be non-aircraft applications for the

concept, such as compact silencers for industrial

axial flow fans commonly used for air exhaust in

power generation systems, mining, parking

garages, etc. where personnel or community noise

exposure are often critical issues.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Bruce E. Walker

Hersh Acoustical Engineering, Inc.

780 Lakefield Road, Unit G

Westlake Village , CA 91361

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Alan S. Hersh

Hersh Acoustical Engineering, Inc.

780 Lakefield Road, Unit G

Westlake Village , CA 91361

Form 9.B Project Summary

Chron:

970560

Proposal Number:

04.01-4755b

Project Title:

Low-Cost Surface Treatment for

Bonding Titanium Panels

Technical Abstract (Limit 200 words)

High speed travel requires reliable airframe

structure and low-cost fabrication technology.

Current adhesive joining methods for Ti panels are

not cost-effective. The resultant junctions are also

limited by the operating temperature under 430K

and the lack of long-term durability. This project

will develop new surface treatment processes to

create unique surface texture and chemistry for

strong and durable bonding with advanced

high-temperature adhesives. Phase I will

demonstrate the feasibility of two physicochemical

surface treatment processes to produce strong and

stable adhesive bonding for Ti panels. Phase II will

select one or two promising processes to optimize

performance, uniformity and cost effectiveness.

These surface treatment processes will be applied

to both monolithic and composite materials, and

titanium and other high-temperature metals, to

achieve a greater thermal stability of adhesive

bonding. Phase III will involve the development of

practical treatment procedures and equipment for

small-scale applications.

Potential Commercial Applications (Limit 200 words)

Physicochemical treatments are needed to prepare

stable metal surfaces for high-temperature

adhesive bonding. High performance and durable

adhesive bonding resulting from these new

processes could be used in high-temperature

aircraft and ground transportation applications. By

using little or no hazardous chemicals, these

processes could also reduce environmental

concerns associated with the use of hazardous and

toxic chemicals.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Rong Wang

Wamax, Inc.

4473 142nd Ave SE

Bellevue , WA 98006

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dora F. Wang

Wamax, Inc.

4473 142nd Ave SE

Bellevue , WA 98006

Form 9.B Project Summary

Chron:

971227

Proposal Number:

04.01-5773

Project Title:

Variable Cell Blanket Sandwich Panel

Technology

Technical Abstract (Limit 200 words)

This project's purpose is to determine the viability

of mathematically modeling the load transfer

properties of uninterrupted variable cell blanket

structures. Variable cell blanket sandwich panel

technology integrates varying density areas into a

laser welded expanded honeycomb core structure

without the need for costly core splicing. The fully

integrated varying cell blanket configuration

creates an uninterrupted load transfer from one cell

size to another.

This effort will consist of the physical testing and

mathematicaly modeling of the properties of

samples of laser welded titanium honeycomb core in

a variety of cell sizes, and foil thicknesses. It is

anticipated that a viable approach to the modeling

of variable cell blanket structures will be

developed. This approach will be the model used in

designing low cost titanium sandwich panel

fabrications.

Variable cell blanket sandwich panels offer reduced

weight, lower cost and higher strength over other

fabricated panel structures. NASA and the

aerospace industry will benefit for this improved

structural design concept. Complex aircraft designs

requiring both low weight and strength can utilize

this technology to stay within their design

parameters.

Potential Commercial Applications (Limit 200 words)

Initially, the aerospace industry, both commercial

and military, will receive the greatest benefit from

variable cell blanket technology. Variable cell

technology offers decreased cost, decreased weight

and increased strength for all honeycomb sandwich

structures. There are a number of commercial

markets that will potentially benefit from this

technology. It is expected that the significantly

lower cost and flexible design possibilities afforded

by this product will encourage the use of

honeycomb in industries such as automobile,

construction, and shipbuilding.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jeffrey Johnson

Benecor, Inc.

5320 West Main

Parsons , KS 67357-8830

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Kristen Johnson

Benecor, Inc.

5320 West Main

Parsons , KS 67357-8830

Form 9.B Project Summary

Chron:

971093

Proposal Number:

04.01-9101

Project Title:

Low Cost Processable High

Performance Materials for High Speed

Research Applications

Technical Abstract (Limit 200 words)

Imitec proposes to make processable low molecular

weight polyimides such as LaRC-PETI-5 and

LaRC-LV type resins from solvent free or low

solvent procedures using simulated extrusion

conditions. The proposed "melt" process is an

innovation because polyimides are traditionally

synthesized using solution polymerization

techniques generating significant quantities of

waste. Efforts will focus on the types of polyimides

currently being tested in NASA's High Speed

Research Program. The project objectives include

the successful synthesis of polyimides via extrusion

like melt processes with resin properties equal or

better than traditional routes and suitable for low

cost fabrications. NASA and the aerospace industry

have significant demands for high performance

polyimides in the need to replace metal components

with light weight composites. Polyimide powders are

becoming more desirable to prepreggers as stricter

environmental regulations are being enforced. In

addition, solvent free polyimides are needed in

various fabrication techniques both by NASA and

the aerospace industry. These techniques include

Advanced Tow Placement (ATP) and Resin

Transfer Molding (RTM). The anticipated results

of polyimides made this way are better composite

properties due to absence of residual solvents and

better wet out because low molecular weight

polymer chains are not extracted.

Potential Commercial Applications (Limit 200 words)

Advanced Tow Placement and Resin Transfer

Molding to make large aerospace components out

of composites. Low density structural foam

insulation.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Betty Tung

Imitec, Inc.

1990 Maxon Road

Schenectady , NY 12308

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Stephen T. Terney

Imitec, Inc.

1990 Maxon Road

Schenectady , NY 12308

Form 9.B Project Summary

Chron:

970286

Proposal Number:

04.02-1100

Project Title:

Reducing Cost, Weight, and NOx of

Combustors by Incorporating Novel

Mixing Techniques.

Technical Abstract (Limit 200 words)

This program introduces novel mixing techniques

for supersonic transport propulsion low emission

combustor designs to dramatically reduce cost,

weight and complexity and to improve performance.

This innovation employs advanced multi-staged

lobed mixers to very rapidly mix fuel and air, both

temporally and spatially, with minimum momentum

loss to the flows. In demonstrations for other

applications, the concept has proven to improve the

transition from air/air mixing to liquid/air mixing.

This proposed work builds upon and extrapolates

the existing body of knowledge to develop a

predic-tive model for the HSCT combustor

environment. The Phase I results will be an

analyti-cal proof-of-concept, characterization of the

anticipated benefits and generation of mixer

designs suitable for verification testing in Phase II.

This program targets the de-fined Subtopic need for

environmentally and economically compatible

improvements directed at combustors for

supersonic transport propulsion systems.

Potential Commercial Applications (Limit 200 words)

The proposed multi-staged-lobe-mixer devices can

find commercial application in a multitude of

aerosol spray devices where a liquid must be

dispersed into a co-flowing, non-reacting gas

stream. Applications include air/fuel mixers for

supersonic transport propulsion systems in addition

to other flight and land-based gas turbines. Other

appli-cations which will be pursued include paint

sprayers, humidifiers and, snow making de-vices.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Stuart S. Hay

FTS Inc.

5448 Westchester Rd

Westchester , OH 45069

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Julio E. hernandez

FTS Inc.

5448 Westchester Rd

Westchester , OH 45069

Form 9.B Project Summary

Chron:

971074

Proposal

Number:

04.02-2200a

Project Title:

A MULTI-SPECTRAL AIRBORNE

RADIOMETER FOR RANGE

RESOLVED HIGH-ALTITUDE AIR

TEMPERATURE MEASUREMENTS

Technical Abstract (Limit 200 words)

Precise air temperature measurements currently

can not be made from high-speed aircraft. We

propose to solve this problem by using a

remote-sensing radiometer. The High-altitude Air

Temperature Radiometer (HATR) will operate in

the 15um CO2 absorption band, near the peak of

the thermal emission for stratospheric air

temperatures. This wavelength region has not been

used for commercialradiometers but has been

explored at Ophir. Using multispectral polarization

modulation and detection techniques, combined with

Ophir's experience and innovations in radiometer

design, we will minimize errors from housing and

window thermal radiance thereby permitting

accurate air temperature measurements on high

speed/high altitude aircraft such as the High Speed

Civil Transport. The unique design will enable the

radiometer to measure true air temperature out of

aircraft traveling at Mach 2.4 at altitudes up to

20km with 0.3C precision, corresponding to a Mach

number uncertainty of 0.002. These air temperature

measurements will be needed for precise control

ofsupersonic engine operation to maximize fuel

efficiency. A multiple wavelength design will allow

prediction of upcoming air temperature variations

to prevent engine unstarts.

Potential Commercial Applications (Limit 200 words)

Potential Commercial Applications

The proposed radiometer will enable accurate air

temperature measurements from high-speed

aircraft and could become an important component

of the HSCT program. In addition, range-resolved

temperature measurements will warn of potential

engine unstart conditions.

The proposed radiometer may find an immediate

market on commercial aircraft providing warning of,

and possibly permitting avoidance of, clear air

turbulence. Additionally, it may allow detection of

approaching icing conditions.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Stuart P. Beaton

OPHIR Corporation

10184 West Belleview Avenue, Suite 200

Littleton , CO 80127

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. James F. Miller

OPHIR Corporation

10184 West Belleview Avenue, Suite 200

Littleton , CO 80127

Form 9.B Project Summary

Chron:

970422

Proposal Number:

04.02-4447

Project Title:

LOW NOISE EXHAUST NOZZLE

FOR A HIGH FLOW,LOW

PRESSURE HSCT ENGINE

Technical Abstract (Limit 200 words)

Environmental acceptability and economic viability

are crucial issues in the development of the next

generation HSCT (High Speed Civil Transport) and

low noise exhaust nozzle technology has a

significant impact on both issues. The design noise

level requirement for the next generation HSCT is

the FAR36 Stage III subsonic rule, with margins.

Since the propulsion system jet is nearly the sole

contributor to the community and sideline noise, the

technology for low noise exhaust nozzle is key to

the HSCT environmental acceptability. To be

economically viable, the low noise exhaust nozzle

must be simple, light weight, and have good

aerodynamic performance throughout its operating

range. A simple axisymmetric plug suppressor

nozzle is presented that reduces the jet velocity at

takeoff, to meet FAR36 Stage III noise levels,

including margin requirements; delivers high

specific thrust at transonic and supersonic cruise;

and delivers high nozzle efficiencies (greater than

0.95), for high performance, at takeoff, transonic

acceleration, subsonic and supersonic cruise flight

conditions. A conceptual design study is proposed

to investigate a low pressure axisymmetric

suppressor nozzle. The conceptual design will

address acoustics, aerodynamic performance, and

mechanical design requirements, as well as their

effects on aircraft takeoff gross weight (TOGW), of

FAR36 Stage III compliance and good nozzle

performance.

Potential Commercial Applications (Limit 200 words)

This effort will provide conceptual design of a low

pressure, axi-plug suppression exhaust nozzle for a

high flow, low pressure (VFX) engine concept. The

proposed nozzle concept utilizes proven suppression

technology that will reduce jet noise, provide good

aerodynamic performance, while save nozzle weight

and reducing mechanical complexity. When applied

to a HSCT or supersonic aircraft, the proposed

exhaust nozzle in conjunction with a VFX engine

cycle has a unique advantage over MFTF engine

cycles using ejector/suppressor nozzles, in its ability

to meet FAR 36 Stage III noise requirements, with

margin, at takeoff conditions.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Bernard Niehaus

Diversitech, Inc.

110 Boggs Lane, Suite 325

Cincinnati , 0h 45246

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

James Askew

Diversitech, Inc.

110 Boggs Lane, Suite 325

Cincinnati , OH 45246

Form 9.B Project Summary

Chron:

971033

Proposal Number:

05.01-1700A

Project Title:

Pilot Voice Recognition for GA Aircraft

Technical Abstract (Limit 200 words)

The innovation proposed by Advanced Creations,

inc.(ACi) is to provide

a generic hands-free interface for general aviation

avionics systems.

ACi will analyze the impact of aircraft vibration,

ambient noise

levels, stress, G forces and atmospheric pressure

changes on the

accuracy of speech recognition algorithms,

developing the basis for an

innovative speech interface that will be low cost,

highly noise

immune, and capable of high level word command

recognition. The ACi

development will leverage the extensive speech

recognition research

funded by the banking community, Wright

Patterson AFB, and others,

coupled with advanced headphone/microphone

technology research being

performed by the cellular phone industry, and the

cockpit research

performed by the military. While tremendous

speech recognition

progress has been made, the existing research has

focused on rather

benign environments when compared to the cockpit.

Incorporation of

solutions for reducing the effects of ambient noise

through integrated

microphone/ headphones will be vital to program

success. We will

utilize the research results from various Air Force

and military

research programs via a Cooperative Research and

Development Agreement

already in place. The interface redundancy offered

by the proposed

system will ensure that performance and safety

levels in general

aviation cockpits increase significantly.

Potential Commercial Applications (Limit 200 words)

The achievement of the objectives of this proposed

SBIR program will

result in a readily exploited commercial product

with tremendous

market demand. An affordable generic hands off

interface will permit

the 21st century pilot to take full advantage of the

advanced avionics

systems being developed under the AGATE

program and others.

Achievement of the full potential of the AGATE

developments will

demand full utilization of the latest avionics systems

that permit the

pilot access to real-time weather and traffic data

and rapid

replanning capabilities. To fully utilize these

advances in a high

stress environment, a hands off pilot-system

interface will contribute

toward increased pilot performance and enhanced

safety.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Mr. Curtis W. Wray

Advanced Creations, Inc.

4403 Dayton-Xenia Rd.

4403 Dayton-Xenia Rd , OH 45432

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. Raymond C. Wabler

Advanced Creations, Inc.

4403 Dayton-Xenia Rd.

Dayton , OH 45432

Form 9.B Project Summary

Chron:

970778

Proposal

Number:

05.01-4565

Project Title:

Automated Manufacturing System For

Grid Stiffened Structures For General

Aviation Aircraft

Technical Abstract (Limit 200 words)

In the 1980's, the General Aviation Industry went

into a tailspin due to liability issues. During the

subsequent hiatus in activity, several proof of

concept developments appeared. These concepts

have matured in the 1990's, under the impluse of

the Advanced General Aviation Transport

Experiments Program and others. As a result the

industry has renewed technical potential to

revitalize.

To date innovative lightweight/low cost, dolphin

shaped, composite airframes, which blend the wings

and the engines into the structure at their ideal

location, have been designed and test flown.

Superior strength/weight performance has been

obtained with structures which are Grid-Stiffened

along geodesic lines. Additionally many first time

observers are stunned by the amount of

unobstructed space available within the airframe.

What is currently lacking is an automated

manufacturing capability for grid stiffened

(geodesic) structures. This issue, if unresolved, will

keep the General Aviation Industry from

developing beyond the level of prototyping and

therefore revitalization would almost certainly be

out of the question.

W. Brandt Goldsworthy & Associates, Inc.

(WBG&AI) propose to solve this problem by

integrating current composites winding and

fiber-tow placement technology with blow-molding

technology to form a liner.

The results, which we need to obtain to consider

this program a success, is a turnkey composites

manufacturing cell which is capable of making a

dozen airframes per day. This challenge is so

profound that it will require entirely new ways of

thinking, and and it will likely have to include the

advantages of thermoplstics technology.

At the end of Phase I we expect to have developed

the concepts and designs necessary to automate

grid stiffened structures manufacturing.

Potential Commercial Applications (Limit 200 words)

The benefit, as described in the abstract, is that a

sorely needed manufacturing capability is created.

This will give rise to high technology and affordable

general aviation aircraft. There is also a significant

potencial to use this manufacturing technology for

producing components and tankage for the big

commercial airliners. As commercial space

initiatives continue to develop WBG&AI also

expects that payload shrouds and rocket tanks will

be made with the automated grid stiffened

manufacturing technology.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

W. Brandt Goldsworthy

W. Brandt Goldsworthy & Associates, Inc.

23930-40 Madison Street

Torrance , CA 90505

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

George Korzeniowski

W. Brandt Goldsworthy & Associates, Inc.

23930-40 Madison Street

Torrance , CA 90505

Form 9.B Project Summary

Form 9.B Project Summary

Chron:

971218

Proposal

Number:

05.01-9859

Project Title:

A HIGH LIFT GENERATION AND

STALL/SPIN RECOVERY SYSTEM

Technical Abstract (Limit 200 words)

The proposal concerns a novel flight control

system, called "Delta Flaps" (Patent Pending) for

the generation of high lift and for stall/spin recovery

of General Aviation (GA) aircraft. The invention

addresses the need to reduce GA aircraft cost while

improving utility, performance and safety.

Compared to conventional high lift devices (HDLs)

such as flaps, the new invention requires much less

installed weight. It is simpler to integrate into the

wing design and can be deployed when the aircraft

is already in a stalled mode. The objective of the

proposed work is to generate a data base that

proves that the proposed high lift concept works

and can be used toward the development of a

generic design for the GA market. The Phase I

effort calls for flow visualization tests, for the

measurement of the polar of the model wings in a

wind tunnel, a first analysis of the aerodynamics of

the proposed HLD and flight tests of a radio

controlled airplane model with fully functional Delta

Flaps.

Potential Commercial Applications (Limit 200 words)

Delta Flaps serve as high lift generating device

during take-off and landing of aircraft, as lift

enhancing device for existing onventional flaps and

as stall/spin recovery device with either hand

operated or automatic deployment. They can be

used as either original or as retrofit system.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Dieter Nowak

MICRON CORPORATION

158 ORCHARD LN

WINCHESTER , TN 37398

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Dieter Nowak

MICRON CORPORATION

158 ORCHARD LN

WINCHESTER , TN 37398

Form 9.B Project Summary

Chron:

971548

Proposal Number:

05.02-1400

Project Title:

Low-Cost Piston Engine Health

Monitoring and Control System for

General Aviation

Technical Abstract (Limit 200 words)

The innovation proposed is a unique combination of

low cost sensors coupled with advanced adaptive

signal processing. The resulting system will

simultaneously provide vital engine diagnostics, and

advanced engine control. Sensors utilized in Phase

1 will include accelerometers and in-cylinder

pressure transducers. Event isolation will be

accomplished using active noise suppression

techniques. It is expected that by utilizing low-cost

multi-use sensors and on-board processing, the

diagnostic components of the system will more than

offset their costs due to a reduction in maintenance

requirements. Phase 1 will concentrate on

development and validation of an innovative

approach to diagnosing engine mechanical fault

conditions. The approach will be demonstrated on

two mechanical faults: excessive connecting rod

bearing wear and compression loss due to piston

ring wear. It is anticipated that the same approach

will be applicable to early detection of a number of

additional mechanical faults including piston skirt

slap, valve seating anomalies, maladjusted valve

train components, and preignition. The diagnostic

components of the production system would provide

failure prediction, thereby enhancing safety,

reducing scheduled maintenance costs, and

extending the required time between overhauls.

The control components will reduce emissions,

enhance performance and efficiency, extend enginelife, and enable single lever control.

Potential Commercial Applications (Limit 200 words)

This engine monitoring and control system

developed for piston powered general aviation

engines has direct commercial potential in the

aviation market. While very few piston powered

general aviation airplanes have been manufactured

recently, there is a promising future for growth in

the market as existing airplanes disappear from the

market and there is great potential for retrofitting

the system to existing airplanes either before or

during engine overhaul. Also, the system or a

similar system could be used in much larger

numbers in automobiles, commercial diesel, marine,

and industrial motors. Finally, adaptations of the

system could be used on turbine engines, electric

motors, or any other rotating machinery.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Keith D. Hoffler

ViGYAN, Inc.

30 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

E. Richard White

ViGYAN, Inc.

30 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

970441

Proposal

Number:

05.02-5963

Project Title:

Lightweight Aircraft Diesel Utilizing

Carbon-Carbon Technology

Technical Abstract (Limit 200 words)

DeltaHawk proposes to utilize carbon-carbon

technology in a lightweight 2-cycle diesel engine we

are developing for general aviation use. Our

engine's design represents substantial

improvements over the current fleet's engines:

lighter weight, smaller, fewer parts, lower BSFC,

smoother running, preferred fuel type, liquid

cooling, no electromagnetic interference,

single-lever power operation, and lower cost.

Carbon-carbon pistons and liners would provide our

engine with additional improvements in:

Efficiency -- Carbon-carbon components provide

the potential for increased thermodynamic

efficiency by reducing heat transfer from the

working gas through the liner, piston crown and

cylinder fireplate. Thermodynamic efficiency

translates in operation to improved fuel efficiency.

Pollution reduction -- Higher cylinder surface

temperatures promote more complete combustion

and shorter ignition delay, and therefore less

pollutants. This benefit would augment the

inherently lower pollution levels of the engine's

diesel (excess air) combustion cycle and use of

unleaded Jet-A fuel.

Weight reduction -- The higher strength and lower

density of the carbon-carbon material can reduce

engine weight by allowing lighter pistons and

smaller crankshaft counterweights.

Potential Commercial Applications (Limit 200 words)

Many dynamics are driving the general aviation

marketplace interest in diesel engines: the need to

migrate to a non-leaded fuel; the need to reduce

emissions; fuel availability, reduced flammability

and price advantages of diesel or Jet-A over

100LL; simplicity of operation; track record of

durability; and fuel economy. The DeltaHawk

diesel technical design will provide these benefits,

and has advantages over known diesel prototypes.

DeltaHawk is within six to eight months of

producing (in Experimental status) the first aviation

diesel in our business plan: the standard upright

V-4 200 hp model. Future development, phased

over the next 2 years, includes an offset drive V-4,

standard and offset-drive 400 hp V-8 models and

potentially V-4 100 hp models (all designed for the

general aviation market). The FAA Certification

process will be initiated for each model as soon as

design is stable. The DeltaHawk 200-400 hp models

will be suitable for most aircraft currently using

150-500 hp gasoline piston engines. Sales are

anticipated for new Experimental aircraft,

replacement engines for both Experimental and

Certificated aircraft, and potentially for new

Certificated aircraft.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Douglas A. Doers

DeltaHawk, Inc.

10698 S. 76th Street

Franklin , WI 53132-9541

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Diane E. Doers

DeltaHawk, Inc.

10698 S. 76th Street

Franklin , WI 53132-9541

Form 9.B Project Summary

Chron:

971107

Proposal

Number:

06.01-0818

Project Title:

An advanced system for dynamic model

deformation and angle-of-attack

measurements

Technical Abstract (Limit 200 words)

The development of a commercially viable model

deformation and angle-of-attack measurement

system is proposed. The system will have a

real-time dynamic measurement capability of at

least 60 Hz, and an accuracy of 0.005 degrees or

better. The Phase I effort focuses on performing a

thorough optimization study and selecting an

appropriate implementation, along with the

demonstration of a prototype system. A follow-on

Phase II effort would result in a ruggedized

commercial version for operation in major NASA

wind-tunnel facilities. The significance of such a

system is that it has the potential to replace the

conventional accelerometer-based angle-of-attack

system under difficult dynamic load conditions. In

addition, it can shorten the wind-tunnel testing

process by providing accurate wind-on model

deformation information for the proper

interpretation of loads data. The approach is

innovative in its combination of the convenient

single-camera photogrammetric approach with

modern digital video systems and a new real-time

target-tracking process. By providing an accurate,

easy-to-use, non-contact measurement of several

very important model parameters, the system will

reduce wind-tunnel testing cycle time and improve

the value of performance data.

Potential Commercial Applications (Limit 200 words)

Current video-based photogrammetry systems in

use at NASA wind tunnels are still in the

development stage, and the importance of these

systems is widely recognized. In the area of

angle-of-attack measurements, there is a clear

need for an optical method to replace the current

accelerometer-based system under dynamic

conditions. Commercial active-target systems have

already been used in some NASA facilities, showing

that a market clearly exists for these systems.

Since it is built with off-the-shelf technology, the

proposed system has the potential to provide

optical angle of attack at a substantially reduced

cost compared to existing systems. In addition to

wind-tunnel applications, there is a huge market for

remote optical measurements in many other areas.

Machine vision systems are now routinely used in

factory environments for quality inspection and

process control. Other industrial applications

include architectural and terrestrial surveying, and

forensic reconstruction. In the medical field, the list

of potential applications includes the diagnosis of

muscular and skeletal problems, studies of

anatomy, and reconstructive surgery. Many of

these applications could benefit from the dynamic

capabilities of our proposed system.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Ronald H. Radeztsky, Jr.

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mujeeb R. Malik

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

971588

Proposal Number:

06.01-7833a

Project Title:

Fiber Bragg Grating Sensors for

Simultaneous Measurement of Shear

Force, Strain, and Temperature for

Aerospace Applications

Technical Abstract (Limit 200 words)

SEACOM proposes to develop new fiber Bragg

grating (FBG) sensors for wind tunnel

instrumentation to measure shear force, strain, and

temperature simultaneously. Innovations include:

· a pair of cross-tilted FBG's subjected to shear

force producing Bragg wavelength shifts in opposite

directions while producing strain and thermally

induced shifts in the same direction. A differential

measurement of Bragg shifts gives a measure of

the shear force independent of strain and

temperature. Currently such an instrument is not

commercially available;

· a dual wavelength method using co-written Bragg

gratings to measure strain and temperature

simultaneously during structural deformation of

wind tunnel models.

The Phase I research objective is to verify the

proposed concepts by conducting experiments on

FBG's subjected to fluid flow, mechanical strain and

thermal stress. In the Phase II research, sensors

will be developed that are capable of distributed or

multi-point measurement to provide more data per

tunnel-occupancy-hour. The all-optical nature of

FBG sensors makes them suitable for remote

operation and for measurement in a severe

environment of electromagnetic interference or

vibration. The proposed FBG sensors will be useful

to NASA for both cryogenic and high temperature

testing of wind tunnel models.

Potential Commercial Applications (Limit 200 words)

Commercial Applications:

- Remote and distributed flow measurement in an

explosive environment such as oil and gas pipes

- Water flow measurement in hydroelectric power

generation

- Industrial processes requiring flow and

temperature measurements

- Shear force measurements in the design of

hydrofoils

- Health monitoring of structures such as bridges

and buildings

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jianli Zheng

Science & Engineering Applications Company

(SEACOM)

4317 Country Club Circle

Virginia Beach , VA 23455

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Arnel C. Lavarias

Science & Engineering Applications Company

(SEACOM)

4317 Country Club Circle

Virginia Beach , VA 23455

Form 9.B Project Summary

Chron:

970003

Proposal Number:

06.02-2748

Project Title:

Vibrostatic Buffeting Alleviation

Technical Abstract (Limit 200 words)

NASA Langley Aeroelasticity Branch is addressing

aircraft lifecycle costs by actively reducing the

vertical tail buffeting due to vortices originating at

wing/fuselage leading edge extensions ("LEX")

during short duration high-alpha maneuvers. In a

departure from previous methods, the system uses

an piezoelectic induced strain actuation ("ISA")

mechanism. As applied to the 1/6 scale F/A-18

Transonic Dynamic Tunnel ("TDT") model, the

port vertical tail is equipped with piezoceramic

elements that enables alleviation of buffet loads

through active means. However, the current system

appears to a number of deficiencies. Although

piezowafers are lightweight and easily

attachable/embeddable the present system requires

bulky electronics and undue control power and

complexity to achieve necessary bandwidth and

stroke requirements. The system provides no level

of passive damping on the vertical tail either in high

strain flight condition or in normal flight. Moreover,

there is insufficient actuator authority to affect

modes other than the fundamental root bending

moment. EMF proposes a new concept of

vibrostatic damping and d33 bimorphs that

increases the control authority, minimizes the drive

electronics requirements and substantially reduces

power consumption while simultaneously

introducing a measure of passive damping at both

low and high alpha regimes.

Potential Commercial Applications (Limit 200 words)

EMF's vibrostatic damping concept creates a new

product for a multifaceted commercial marketplace.

The proposed system has application to almost any

intermittent damping vibratory systems positioning

or attenuation incorporating piezoelectric or

electrostrictive devices. Opportunities include:

Ground and Space-borne Optics, Ultrasonic

Cleaners and Sports & Leisure Equipment.

Exploitation of the size and power reduction in

active mode combined with added passive damping

achieved under this project would make the

technology viable for a wide variety of such

applications. As noted in the support letter, EMF is

developing strategic partnerships for commercial

applications of this technology with Boeing Long

Beach. In particular, significant interest exists for

its application to wing flutter for the HSCT. EMF is

further developing strategic partnerships with

Blatek Corporation and Quiet Power Industries for

direct commercial applications of the outcome of

this research.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Gareth J Knowles

EMF Industries, Inc.

1700 Riverside Drive, Phillips Business Park

So. Williamsport , PA 17701

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Robert Coppola

EMF Industries, Inc.

1700 Riverside Drive, Phillips Business Park

So. Williamsport , PA 17701

Form 9.B Project Summary

Chron:

971120

Proposal Number:

06.02-2775

Project Title:

CFD/CSD Interfacing via an

Innovative Structural Boundary

Element Method

Technical Abstract (Limit 200 words)

An innovative structural Boundary Element

Method (BEM) Solver is developed for interfacing

the Computational Fluid Dynamics (CFD) and

Computational Structural Dynamics (CSD) grids.

Formulated as a solid mechanics problem with a

minimum strain energy requirement, the BEM

Solver generates a truly three dimensional (3-D)

Universal Spline Matrix. The Universal Spline

Matrix is a vector operator which includes the

coupling of displacements and forces along all axes.

Based on a similar formulation, an Exterior BEM

Solver is also developed to account for the flow grid

deformation. Thus the BEM Solver allows a unified

treatment of the displacement and force

transformation for CFD/CSD interfacing as well as

the computation of the flow field grid deformation.

The solution procedure is fully automated and

requires no further user interaction, therefore it is

ideally suitable for Computational Aeroelasticity

(CAE) and Multidisciplinary Optimization (MDO)

applications.

Potential Commercial Applications (Limit 200 words)

Considerable growing interest is being generated in

new methodologies for aircraft aeroelasticity and

rotorcraft/STOVL aircraft CFD/CSD and

computational aeroelasticity (CAA) interactions

requiring high-level, high-resolution CFD solutions

through CFD/FEM grid interfacing. The BEM

Solver can meet this requirement to provide

accurate and effective data transferal in high

fidelity between grid systems, thus improving

solution accuracy in aeroelastic predictions in

problems such as limit cycle oscillation and flutter.

The commercialized BEM Solver will act as a data

transferal modem requiring minimum user learning

time. Meanwhile, ZONA's reputation and track

record in supporting the aerospace industry with the

ZONA codes for aeroelastic applications will assure

the success of the future commercialization of the

BEM Solver.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Ping Chih Chen

ZONA Technology, Inc.

2651 W. Guadalupe Rd., Ste. B-228

Mesa , AZ 85202

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

ZONA Technology, Inc.

2651 W. Guadalupe Rd., Ste. B-228

Mesa , AZ 85202

Form 9.B Project Summary

Chron:

971518

Proposal Number:

06.04-0003

Project Title:

Dynamic Stall Control on Rotorcraft

Technical Abstract (Limit 200 words)

A program for the development of an active control

system for controlling dynamic stall on rotorcraft

blades is proposed. The system utilizes an array of

pulsed jet actuators near the blade leading edge to

control unsteady lift and flow separation during

transient pitch-up. The control system will be

developed and tested on a rotor blade section

mounted in a low-speed subsonic wind tunnel at

Physical Sciences Inc. The ability to control and

delay dynamic stall events during oscillatory

pitching of the model will be evaluated in open-loop

experiments. Results from the open-loop tests will

be used to develop a state-space model to describe

the unsteady aerodynamic loads both with and

without control. Using the model, control algorithms

will be tested in software using MATLAB/Simulink.

The active controller will be implemented on a

high-speed digital signal processor and evaluated

on-line in its ability to suppress dynamic stall. The

experimental results will be used as guidelines for

the design of a Phase II prototype control system

for large-scale testing at flight conditions.

Potential Commercial Applications (Limit 200 words)

The performance of both commercial and military

rotorcraft may be enhanced through the application

of the proposed control system. The system will

alleviate problems which currently limit high-speed

forward flight and which produce excessive noise

and vibration in certain flight regimes. The

successful development and application of this

control system will result in the design of more

versatile and quiet rotorcraft and VSTOL vehicles.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Keith R. McManus

Physical Sciences Inc.

20 New England Business Center

Andover , MA 01810

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

George E. Caledonia

Physical Sciences, Inc.

20 New England Business Center

Andover , MA 01810

Form 9.B Project Summary

Chron:

971574

Proposal

Number:

06.04-4800

Project Title:

A First-Principles Based High Order

Discontinuous Galerkin Methodology

for Rotorcraft Flowfield Studies

Technical Abstract (Limit 200 words)

A first-principles based high order Discontinuous

Galerkin (DG) methodology for rotorcraft flow field

studies is proposed. A 3rd/5th spatial order compact

DG methodology will be developed. The scheme

developed will be compact, i.e., the cell update

overtime depends only on the information from the

cell and its immediate neighbors. A unique

advantage of the compactness of this method is that

it does not require any special treatment near

boundaries and Chimera intergrid boundaries to

maintain high order accuracy.

The compact DG scheme will be implemented in

conjunction with an innovative selective overset

refinement method. This will ensure that the

rotor-blade tip vortices convect over large

distances without dissipation. Thus, this

methodology strives to achieve the philosophy of

h-p refinement for optimal computational efficiency

in the most practical manner. The compact high

order DG/selective overset refinement will be

implemented in an ENO-based high order 3D,

unsteady, overset NS solver specifically developed

for rotorcraft studies by the Principal Investigator

and the Consultant at Georgia Tech during the

demonstration phase.

The proposed methodology will be validated and

tip-vortex core velocity profiles will be compared

with experiments for a rotor in hover. The

comparative costs (CPU, memory overhead),

robustness of the proposed high order compact DG

method with conventional wide-stencil ENO,

MUSCL schemes will be analyzed. Information

fidelity during intergrid flow-feature transfers in

overset grids will be examined.

In Phase II, the focus will be on porting this

methodology to standard NASA platforms such as

OVERFLOW, and their application to handle

complex issues such as rotor-blade interactional

noise issues, generic rotor craft interactional

problems, and tip shape acoustic characteristics

predictions.

Potential Commercial Applications (Limit 200 words)

The proposed first-principles based efficient

resolution of vorticity-laden flowfield will be

applicable to diverse application such as non-linear

lift systems, high lift systems, and vortex buffeting

in fighter planes. Commercial application to civil

aviations include studies of wing-trailing vortex

dynamics from large aircrafts such as 747's, and

prediction of the life-span of such vortices.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Nathan Hariharan

CFD Research Corporation

215 Wynn Dr.

Huntsville , AL 35805

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Andrzej J. Przekwas

CFD Research Corporation

215 Wynn Dr.

Huntsville , AL 35805

Form 9.B Project Summary

Chron:

970640

Proposal Number:

06.04-9282

Project Title:

Reduced Order Free Wake Modeling

for Near Real Time Simulation of

Rotorcraft Flight Mechanics

Technical Abstract (Limit 200 words)

Rapid, realistic simulation of rotorcraft flight

mechanics is a continuing challenge for the

mission/flight simulation community, aircraft

designers, and control system specialists.

Accelerating flight dynamics models while

integrating them with state-of-the art performance

analysis tools is a particularly promising way to

streamline the design, testing, and certification of

new rotorcraft, particularly novel civil tiltrotors.

Efficient modeling of complex

wake/fuselage/empennage aerodynamic

interactions lies at the heart of this problem, though

rapidly evolving computational methods are now

bringing advanced aerodynamic modeling

techniques within reach for these applications. The

thrust of this proposed effort is to address the

limitations of current flight dynamics modeling tools

by developing dramatically accelerated, reduced

order embodiments of validated free wake models.

This will provide high fidelity treatments of

rotor/wake and rotor/body interaction for flight

mechanics and simulation activities while yielding

near real time performance on modern

workstations. This new model will also address

current limitations in predicting helicopter and

tiltrotor response to control inputs for general flight

conditions and will also incorporate

body/empennage effects. While integrating

smoothly with established performance analysis

tools and possessing strong "stand-alone"

capabilities, the model will be designed to be

operable with a variety of existing flight dynamics

codes for maximum utility.

Potential Commercial Applications (Limit 200 words)

Development of this capability would address the

need for new insight into the flight mechanics of

civil tiltrotor designs or other novel dual-rotor

configurations. It would also improve the fidelity of

fixed and moving-base helicopter flight simulators,

as well as aid the development of advanced flight

controls. In addition, better understanding of

helicopter and tiltrotor flow fields could also aid

commercial operators concerned with safe

operating procedures around ground obstructions or

in unusual attitudes or operating conditions caused

by environmental conditions or noise abatement

requirements.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Todd R. Quackenbush

Continuum Dynamics, Inc.

P.O. Box 3073

Princeton , NJ 08543-3073

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Barbara A. Agans

Continuum Dynamics, Inc.

P.O. Box 3073

Princeton , NJ 08543-3073

Form 9.B Project Summary

Chron:

970204

Proposal Number:

06.05-0818

Project Title:

Control and Alteration of Wing-Tip

Flowfield for Induced Drag Reduction

Technical Abstract (Limit 200 words)

The ability to alter positively the wing-tip flowfield

is a dominant factor for reducing drag-due-to-lift

and improving the aerodynamic efficiency of civil

transports. The induced drag problem exists due to

the finite span of the wing and consequently, the

formation of a tip vortex. A novel technique for

reducing induced drag is proposed. This research

focuses on effective control of the wing-tip vortex

through modifications of the tip geometry, thereby

altering the vortex initiation flowfield and

reducing the intensity of the shear-layer roll-up

process. The technique is innovative because of its

simplicity. The effort focuses on the control of

vortex-induced drag for moderate to high aspect

ratio wings and simulation of the modified tip-vortex

flowfield. The reduction in fuel burn associated with

enhanced aerodynamic performance will help

NASA meet its goal of environmental compatibility

(emissions).

Potential Commercial Applications (Limit 200 words)

Design of fuel efficient wings for commercial and

military aircraft, better design of rotor blades to

improve rotorcraft performance, accurate

simulation of trailing-line vortices for developing

wake hazard reduction strategies.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Mehdi R. Khorrami

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mujeeb R. Malik

High Technology Corporation

28 Research Drive

Hampton , VA 23666

Form 9.B Project Summary

Chron:

971300

Proposal Number:

06.06-1049

Project Title:

Space-Time Conservation Element

Solution Element Method for Pulse

Detonation Engine

Technical Abstract (Limit 200 words)

We propose to develop a computer code for

simulating Pulse Detonation Engines (PDEs). This

code will be based on the space-time conservation

element-solution element method. The basic idea of

this method is global and local flux conservation in

a space-time domain. In this method conservation

variables and their derivatives are treated as

unknowns which are defined on the solution

element. A time marching scheme is constructed

using local conservation within each conservation

element. It has been demonstrated by that this

method yields high resolution for shocks,

rarefaction waves, acoustic waves, vortices,

detonation waves, and shock/acoustic,

shock/vortices interactions.

During Phase I of this project, we propose to

develop robust computer codes, based on the above

methodology, for unsteady, implicit one dimensional

and quasi one dimensional PDE problems, with

multistep chemistry. These codes will be extended

to solve general combustion problems, validated

with benchmark problems and compared with

MOZART code.

At the end of Phase II, PDE and combustion

software packages will be available for

axisymmetric and three dimensional geometries

using structured and unstructured grids with full

multistep chemistry.

Potential Commercial Applications (Limit 200 words)

The analytical formulations and their numerical

implementations proposed in this research will

enhance the capability in numerical simulation of

combustion problems and computational fluid

dynamics in general. The computer codes for

deflagration and detonation reactions developed in

the Phase I and Phase II of the proposed

developments, will result in significant performance

improvement in analysis of a wide range of engine

systems. Moreover, they can be utilized to perform

numerical experiments in the design phase, instead

of building expensive prototypes over and over

again. This will benefit new and emerging markets

both in the United States and abroad.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Tae Park

AYT Corp.

2001 Aerospace Parkway

Brook Park , OH 44142

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Ayo Oyediran

AYT Corp.

2001 Aerospace Parkway

Brook Park , OH 44142

Form 9.B Project Summary

Chron 972574

Proposal Number 97-1 06.07-1008

Project Title Reliability-based Optimization for Aircraft Structural Design

Technical Abstract

This proposal describes a six month study to demonstrate the feasibility of applying a

recently formulated algorithm for reliability-based optimization (RBO) to the structural

design of advanced aircraft. The goal of the project is to develop a computationally

efficient RBO capability for practical applications involving large numbers of design

variables and constraints. The new algorithm will be integrated with an existing commercial

structural design optimization code, ASTROS, originally developed for the Air Force Wright

Laboratory. Commercialization and maintenance of the code have been taken over by Universal

Analytics Inc. (UAI) under a Cooperative Research and Development Agreement (CRDA) with

Wright Laboratory. ACTA is teamed with UAI as a subcontractor on this project.

Application of RBO requires the quantification of modeling uncertainty. A second innovation

is proposed to derive modeling uncertainty statistics from readily available dynamic and

static analysis and test data. Dynamic mode shapes and frequencies have previously been

used to generate databases of structural modeling uncertainty for spacecraft and automobiles. The same will be done for aircraft under the proposed contract. In addition, static analysis and test data will be collected and processed to create a historical database of structural modeling uncertainty for aircraft.

Potential Commercial Applications

Structural design of commercial and military aircraft.

Structural design of space structures.

Structural design of automotive structures.

Structural design of advanced structures in general.

Name and Address of Offeror

Firm: ACTA Inc

Name: James Hudson

Street: 2790 Skypark Drive, Suite 310

City: Torrance

ST: CA ZIP: 90505

Name and Address Of Principal Investigator

Firm: ACTA Inc

Name: Timothy K. Hasselman

Street: 2790 Skypark Drive, Suite 310

City: Torrance

ST: CA ZIP: 90505

Form 9.B Project Summary

Chron:

970885

Proposal

Number:

06.07-8074

Project Title:

Reliability-Based Multi-Disciplinary

Optimization of Large Multi-Component

Systems Using Interdigitation

Technical Abstract (Limit 200 words)

The proposed research will develop a new

formulation that makes multi-component

reliability-based optimization (RMDO) problems

only slightly more computationally intensive than

conventional MDO problems. ARA and Northrop

Grumman will team with Engineous Software to

build on Engineous' commercially successful

optimization approach that couples methods

(interdigitation) and develop an algorithm that

explicitly treats uncertainties during the design

optimization. Key to success of this approach is the

use of innovative analysis strategies. Without such

strategies RMDO will be prohibitively expensive.

First, we will use the concept of results sharing

wherein we use the reliability-based analysis results

in the design space search process. Because

solution of the probabilistic analysis problem can be

formulated as a sub-optimization problem, gradient

computations in the random variable space can be

used by the optimizer. Second, we will employ the

Engineous rule-based system to limit probabilistic

analysis to a working set of constraints and random

variables. Third, we will use efficient direct

differentiation and successive approximation

techniques. RMDO obviates the need to do costly

sensitivity analyses after the optimum is found

since uncertainties and variabilities are accounted

for during optimization and RMDO results in a

robust solution since the range of operating

conditions is considered during optimization.

Potential Commercial Applications (Limit 200 words)

The recent strong demand for reliability-based

design methods in the aerospace, automotive, and

civil infrastructure industries provides a strong

market for optimum design methods that can work

within the reliability-based framework. No

commercial RBO tools exist. By working with a

commercially successful MDO package, the

chances of commercial success are quite high.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Robert H. Sues, Ph.D.

Applied Research Associates, Inc.

811 Spring Forest Rd., Suite 100

Raleigh , NC 27609

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Applied Research Associates, Inc.

4300 San Mateo Blvd, NE, A220

Albuquerque , NM 87110

Form 9.B Project Summary

Chron:

970524

Proposal

Number:

06.07-9047

Project Title:

Uncertainty-based Multidisciplinary

Design Optimization for Aerospace

Structures

Technical Abstract (Limit 200 words)

The proposed effort is concerned with the

development of a multi-disciplinary design

optimization [MDDO] software program. This

software would permit the consideration of

numerous different measures of product

performance as well as reliability in order to

determine the optimal product configuration. The

MDDO software would enable engineers to

consider the impact of design changes on all

relevant measures of performance simultaneously.

The software is innovative for several reasons.

First, it would be the first methodology capable of

handling both measures of product performance and

reliability. Second, it would enable the consideration

of variable uncertainty in the analysis of the

product design. The incorporation of variable

uncertainty would enable the designer to determine

the impact such uncertainty plays in the desired

product performance and reliability. The software

would directly estimate the sensitivity of each

performance measure to each random variable, as

well as the performance sensitivities to random

variable uncertainties. The ability to consider

variable uncertainty in a multi-disciplinary

optimization routine would be unique, and would

represent a significant advance over existing design

software.

Potential Commercial Applications (Limit 200 words)

The proposed software program would permit

multi-disciplinary evaluation of product designs and

include both variable uncertainties, measures of

product performance, and reliability. This software

capability would dramatically improve the

performance and reliability of aviation, aerospace,

and other large complex systems. The capability of

assessing a product design under consideration of

multiple performance measures and reliability is a

significant improvement of existing methods.

Application of the software would be found in any

complex product or component where engineering

expertise has been used to determine the

appropriate trade-off in design and performance.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael T. Kowal

PerSyst Development Group of Paul Holland & Assoc.

Inc.

5123 Virginia Way, Suite C-21

Brentwood , TN 37027-7519

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Michael T. Kowal

PerSyst Development Group of Paul Holland & Assoc.

Inc.

5123 Virginia Way, Suite C-21

Brentwood , TN 37027-7519

Form 9.B Project Summary

Chron:

970141

Proposal

Number:

06.09-4367

Project Title:

Resolving Turbulence-Chemistry

Interactions in Supersonic Combustion

Technical Abstract (Limit 200 words)

Beam Technologies will develop a hybrid

finite-volume/Probability

DensityFunction (PDF) code which will significantly

enhance the

ability ofNASA/Langley and industry to study

supersonic combustion

problems. Current finite-volume CFD codes used

for supersonic

combustion (e.g., NSAS's LARCK code) take no

account of the

turbulence-chemistry interactions, which can have

an

order-of-maganitude effect on the mean reaction

rates. PDF

methods are known for their ability to treat the

nonlinear chemical

reaction terms without modeling, thus resolving the

principal

turbulence-chemistry interactions. For this reason,

PDF methods are

becoming the approach of choice in, for example,

the gas-turbine and

chemical processing industries. The proposed

project will extend the

PDF's ability to handle supersonic reacting flows

and integrate the

PDF code with the LARCK code for efficient

simulations. The finished

code will also allow users to choose between

several modules which

will provide both the LARCK code's efficienty in

simulating the

turbulent velocity field and the PDF code's

accuracy in predicting the

thermochemistry. The proposed work directly

supports NASA objectives

in hypersonic and SCRAMJET design.

Potential Commercial Applications (Limit 200 words)

Beam's proposed code will provide significant

improvement for

predicting high-speed reacting flows with complex

chemistry. The code

will make a significant contribution to the

hypersonic industry: it

will be an important step towards the reliable

computer based design

of SCRAMJETS.

The PDF modules developed will be suitable for

connection with other

finite-volume codes.In other applications, the

proposed work will

allow the chemical and power industries to evaluate

the performance of

their products before any prototype or pilot plant is

built. This will

not only significantly reduce their capital

investment but also

provide more flexibility to the design and

modification processes.

These advantagesassure a large commercial

market and potential for

other turbulent reacting flow applications.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Kuochen Tsai

Beam Technologies, Inc.

110 North Cayuga Street

Ithaca , NY 14850

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Gal Berkooz

Beam Technologies, Inc.

110 North Cayuga Street

Ithaca , NY 14850

Form 9.B Project Summary

Chron:

971169

Proposal

Number:

06.09-5128

Project Title:

Microfabricated, Low Maintenance Skin

Friction Sensor for Highly Transient

Applications

Technical Abstract (Limit 200 words)

Although skin friction measurements have been

made in highly transient facilities in the past,

accurate measurement of wall shear stress with

adequate spatial and temporal resolution has been

difficult to perform due to the physical size of the

instrumentation and due to high maintenance

requirements. Earlier designs required oil to fill the

interior of the gage, but by utilizing new

microfabrication techniques, such as stereo

lithography, new design possibilities will allow skin

friction sensors without the oil and its intendant

high maintenance and care but with higher spatial

and temporal resolution.

This instrumentation is crucial to the development

and operation of affordable, safe, and efficient 21st

century aircraft and other high-speed transportation

systems. The accurate measurement of wall shear

stress in fluid dynamic devices is important for

understanding the basic fluid physics involved and

assessing the performance of the device, leading to

improvements in the design and operation of future

high-speed transportation systems.

An excellent development team has been

assembled including Professor Joseph Schetz of

Virginia Tech, a world leader in wall shear stress

measurements, and F&S, a leader in sensor

development and commercialization. The F&S team

is both qualified and motivated to build upon their

combined demonstrated capabilities.

Potential Commercial Applications (Limit 200 words)

The materials and technology now exist to construct

a microfabricated sensor for the accurate

measurement of skin friction in highly transient

wind tunnels. This instrumentation is crucial to the

development and operation of affordable, safe and

efficient 21st century aircraft and other high-speed

transportation systems. The accurate measurement

of wall shear stress in fluid dynamic devices is

important for understanding the basic fluid physics

involved and assessing the performance of the

device, leading to improvements in the design and

operation of future high-speed transportation

systems.

In addition, research in the wide temperature range

instrumentation area will provide transducers with

commercial uses that will include transportation

system design, development and operation,

semiconductor fabrication, commercial jet engines,

automobile engines, the metal, ceramic and wood

processing industries, and the power generation and

monitoring systems for coal-fired, nuclear and

fuel-cell technologies. F&S has identified many end

users of the microfabricated wall shear stress

sensor within the government such as Air Force,

NASA, NASP, ARPA, Army, Navy, and the DOE.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Wade Pulliam

F&S, Inc.

2801 Commerce Street

Blacksburg , VA 24060

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Garnett S. Linkous

F&S, Inc.

2801 Commerce Street

Blacksburg , VA 24060

Form 9.B Project Summary

Chron:

971170

Proposal

Number:

06.10-3474A

Project Title:

Concept Map-Directed Hyperlinking for

Collaborative Design

Technical Abstract (Limit 200 words)

NASA, which depends on the services of many

diverse units to accomplish its missions, is

challenged by a multiplicity of information and the

geographical distribution of its personnel working

towards a common goal. This Phase I effort

proposes a novel technology developed within a

cognitive framework to fulfill the collaborative

design and information sharing needs of NASA

multi-operator teams. Our initial effort is focused

on geographically distributed operators who

generate information products and deploy these

products to a central server. Our Concept

Map-Directed Hyperlinking for Collaborative

Design has three development phases: 1)

identifying the relationships and dependencies

among pieces of information needed and generated

by operators via knowledge elicitation; 2) using the

results from the knowledge elicitation to construct a

concept map to blueprint the cognitive processes of

a multi-operator team; and 3) developing a

server-side software agent to generate hyperlinks,

directed by the concept map, between similar and

related information. Our approach is unique in that

it automatically generates meaningful hyperlinks

among information residing on the server, therefore

facilitating information sharing in a way that

corresponds naturally to the team cognitive

process.

Potential Commercial Applications (Limit 200 words)

The technology developed under the Phase I effort

has several potential commercial applications.

Market areas that can be targeted include the

Internet, corporate intranets, and other large

networks. Specific applications include: 1)

automatic hyperlinking capability for

Internet/intranet-based research groups; 2)

corporate data sharing through hyperlinking; 3)

intelligent-agent directed hyperlinking; and 4)

prevention of dangling hyperlinks.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Christine Illgen

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Greg L. Zacharias

Charles River Analytics

55 Wheeler Street

Cambridge , MA 02138-1125

Form 9.B Project Summary

Chron:

971575

Proposal Number:

06.10-4800A

Project Title:

Intelligent Solution Optimization Using

Artificial Neural Networks Applied to

Numerical Flow Solvers

Technical Abstract (Limit 200 words)

General purpose flow solvers are designed to treat

a wide class of fluid flow problems. Simulation of

any one particular class of problems is therefore

rarely optimized. Moreover, many algorithms

require frequent user monitoring and adjustment of

code parameters to ensure a successful run. A need

therefore exists to automatize code execution, with

concomitant run-time, problem dependent

optimization of the computational effort. Artificial

Neural Network (ANN) approach offers a natural

solution to this problem of "intelligent" algorithm

control. The networks inherent nonlinearity and

trainability allows the development of algorithm

control and optimization software capable of

self-tuning to any problem at hand. ANN-based

code optimization will be applied on two levels. High

level control will automatically determine the best

combinations of code parameters that determine

the most optimal overall simulation convergence

rates. Low level control will optimize performance

of individual computational modules. This project is

of direct benefit to NASA, as the work will result in

a new computational paradigm capable of radically

decreasing design cycles which rely on interaction

between simulations and hardware development.

Potential Commercial Applications (Limit 200 words)

Commercial potential for the developed software is

very high as it will allow, for the first time,

non-experts to use high fidelity CFD simulators. It

will also be of great interest to engineers who

routinely use flow simulators for hardware design,

as the software would significantly reduce

simulation times and increase throughput.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Maciej Z. Pindera

CFD Research Corporation

215 Wynn Dr.

Huntsville , AL 35805

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Andrzej J. Przekwas

CFD Research Corporation

215 Wynn Dr.

Huntsville , AL 35805

Form 9.B Project Summary

Chron:

971442

Proposal Number:

06.10-7242

Project Title:

Coordination Tool for Large, Complex

Aerospace Designs Using Artificial

Intelligence (AI) Techniques

Technical Abstract (Limit 200 words)

The overall goal of this project is to reduce design

errors and design time of aircraft by developing an

Aerospace Design Coordination Tool (ADCT),

which would coordinate a distributed team of

engineers. It will track design decisions, save

decision rationale, recognize conflicts and aid their

resolution, monitor design changes, and coordinate

the design change and updating process - a leading

source of errors in distributed aerospace design

teams. ADCT will use several concepts from AI

which have been combined into a system, called

Redux, of theories, capabilities, concepts, and

formalisms, explicitly to aid the management and

coordination of complex designs and design

changes. The ADCT would be interfaced to current

Aerospace design tools and be useable over several

different kinds of networks, to coordinate a large,

distributed team of engineers. We will prove its

feasibility by developing and demonstrating a

proof-of-concept, limited prototype.

SHAI has complemented our extensive AI R&D

expertise in the field of collaborative design with

Ken Price, a member of Boeing's Aerospace design

team who participated in all phases of the design of

Boeing's 777 and supplies familiarity and

experience with the Aerospace design process and

with design tools used.

Potential Commercial Applications (Limit 200 words)

The primary benefit of this project will be the

dramatic reduction of errors and design time and

the increased quality of designs for complex

aerospace systems. The Aerospace Design

Coordination Tool (ADCT) will facilitate the

management and coordination of complex

aerospace designs and the associated engineers

who are often geographically distributed and in

separate organizations. Use of a Boeing design

engineer facilitates commercialization.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Richard H. Stottler

Stottler Henke Associates, Inc.

2016 Belle Monti Avenue

Belmont , CA 94002

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Christopher J. Rognier

Stottler Henke Associates, Inc.

2016 Belle Monti Avenue

Belmont , CA 94002

Form 9.B Project Summary

Chron:

970649

Proposal Number:

06.10-9282

Project Title:

An Innovative Aerodynamic Engine for

the Next Generation Design System

Technical Abstract (Limit 200 words)

The key to maintaining the United States' lead in

the commercial and military aircraft markets lies in

the reduction of design cycle times. A shorter

design cycle means lower development costs, more

rapid market response, the potential for multi-point

design optimization, and the opportunity to

incorporate future high risk technologies into new

designs. Continuum Dynamics, Inc. proposes the

development of a new "aerodynamic engine" for

this next generation design system. The central

innovations in this approach are: a fast panel

methodology providing order of magnitude

reductions in both computation time and storage

requirements over existing panel methods; a

modular fast kernel which may be integrated

directly into existing panel codes, providing aircraft

manufacturers tremendously improved performance

while maintaining their existing knowledge and

design bases; and the integration of a free vortex

particle formulation into this fast panel

methodology, providing designers with an efficient

tool for modeling vortical wake and separation

phenomena. The development and integration of

these key concepts will both lead to a major

reduction in design cycle times and provide

designers with an expanded envelope modeling tool

to understand and potentially exploit unsteady,

vortical flow structures in future aircraft designs.

Potential Commercial Applications (Limit 200 words)

The ability to rapidly calculate both inviscid and

viscous/vortex-dominated flows about complex

bodies over an entire flight operating range,

constitutes a powerful new tool for assessing

performance, loads, and flow characteristics of new

and existing configurations. The technological

innovations to be developed and implemented here

will power a family of new aerodynamic design

products including: (1) a fast-panel kernel which will

be marketed directly to aircraft manufacturers and

to panel code developers for incorporation into

existing panel based design systems to yield an

order of magnitude reduction in both computation

and storage requirements; (2) a new "aerodynamic

engine" with the potential of revolutionizing the

aircraft design process, by enhancing the flow

modeling fidelity in the preliminary stages of

design; and (3) with the integration of emerging

solid modeling and optimization technologies, a

completely new preliminary design system with the

power to perform multi-point design optimization

and rapidly evaluate high risk technologies.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Alexander H. Boschitsch

Continuum Dynamics, Inc.

P.O. Box 3073

Princeton , NJ 08543-3073

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Barbara A. Agans

Continuum Dynamics, Inc.

P.O. Box 3073

Princeton , NJ 08543-3073

Form 9.B Project Summary

Chron:

970312

Proposal

Number:

07.01-0017

Project Title:

High Density Energy Storage System

Based on an Extremely Lightweight

Proton Exchange Membrane Fuel

Cell/Electrolyzer Set

Technical Abstract (Limit 200 words)

High Altitude Long Endurance (HALE) aircraft,

especially unmanned aerial vehicles (UAVs) offer a

unique combination of capabilities for use as

observation platforms and relay links. They operate

closer to the ground and at lower cost than

satellites, while being capable of staying over a

small area for extended periods and remaining aloft

virtually indefinitely. Staying aloft indefinitely

requires that the aircraft be energetically

self-sufficient, and the most promising way of

achieving this is the use of solar electric power.

Keeping a solar powered aircraft aloft through the

night, requires storing surplus electric power during

the day for use at night. A lightweight proton

exchange membrane (PEM) electrolyzer to convert

electric power into hydrogen and oxygen in

combination with a lightweight PEM fuel cell to

generate electricity at night offers the means for

achieving this. The performance needed requires

lighter fuel cell and electrolyzer hardware than is

currently available. Equipment meeting these needs

can be economically fabricated through the use of a

combination of lightweight metal and polymer

components. The metal components can be

protected from corrosion using little, if any precious

metal plating, and bonded metallurgically to achieve

the highest possible internal conductivity, while

allowing the greatest reduction in mass.

Potential Commercial Applications (Limit 200 words)

The potential commercial applications for HALE

aircraft include meteorology, where they can make

detailed observations to support forecasting and

storm tracking, environmental monitoring, forest

fire detection, tracking and monitoring marine life,

multispectral imaging for locating mineral deposits,

and long range communication relays in sparsely

populated areas. The same lightweight fuel cell and

electrolyzer technology that is required as an

enabling technology for HALE UAVs can also be

used to produce lighter weight and more compact

PEM fuel cells for terrestrial applications, such as

clean portable power units and zero pollution

vehicles.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Alan Cisar

Lynntech, Inc.

7610 Eastmark Drive, Suite 105

College Station , TX 77840

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Oliver J. Murphy

Lynntech, Inc.

7610 Eastmark Drive, Suite 105

College Station , TX 77840

Form 9.B Project Summary

Chron:

970177

Proposal Number:

07.01-8457

Project Title:

Hybrid Propulsion System for

Very-High Altitude Subsonic Aircraft

Technical Abstract (Limit 200 words)

A hybrid propshaft/jet propulsion system is

implemented with a novel piston engine that can

provide either or both shaft and gas power

regardless of atmospheric density. Utilizing a

facultative adiabatic internal-combustion engine

(FAICE) experimentally demonstrated to be

capable of delivering shaft power with and without

aspiration, a controllable hot gas generator for

producing useful reaction propulsion at high

altitudes and low airspeeds is shown. Fueled by

direct-injected nitromethane and backpressured

with a variable area expansion turbine, the engine

combustion power available is divided between

shaft power produced by the expansion of the

combustion products against a piston and by

expansion in a turbine driving a ducted-fan-powered

jet to produce reaction on the vehicle. Maximum

subsonic motive power is found to occur when the

high enthalpy, low mass flow engine exhaust

products are used to augment the total mass flow

ejected and to moderate the ejection velocity by

aspirating, compressing and mixing with available

ram air. Additional impulse energy is shown to be

available by liberating the residual chemical energy

of the underreacted exhaust gases through catalytic

ignition and combustion in the duct with the

inducted air prior to final expansion to ambient

pressure.

Potential Commercial Applications (Limit 200 words)

The performance of very-high-altitude aeronautical

and reusable aerospace vehicles can be enhanced

by using a combination of shaft and reaction power

capabilities available from a hybrid internal

combustion engine that can operate with and

without air to minimize consumption and fixed

weight. Such an engine has application to

maneuverable and recoverable single-stage-to-orbit

spacecraft as well as high-altitude atmospheric

research aircraft. Variations of the system have

merit for general aviation aircraft as well.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Alvin Lowi, Jr.

Lion Engineering, Inc.

2146 Toscanini Drive

Rancho Palos Verdes , CA 90275

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Alvin Lowi, Jr.

Lion Engineering, Inc.

2146 Toscanini Drive

Rancho Palos Verdes , CA 90275

Form 9.B Project Summary

Chron:

971295

Proposal

Number:

07.02-5128

Project Title:

Multimeasurand Optical Fiber Sensors

for Flight Test Applications

Technical Abstract (Limit 200 words)

Optical fiber sensors are rapidly emerging to

replace conventional electrical-based sensor

instrumentation in specific applications where small

size, low mass, multiplexing capability, and high

temperature resistance is a requirement. The

advantages offered by state-of-the-art optical fiber

sensors are particularly important for flight testing

applications where the extremely low-profile

geometry of a hair-thin optical fiber sensor permits

precise measurements of pressure, temperature,

skin friction, and heat flux with minimal intrusion

into the flow field. F&S, Inc. and researchers within

Virginia Tech's Aerospace Engineering

Department propose to develop a novel combined

optical fiber pressure, temperature, and skin

friction gage for distributed hypersonic flow

measurements during aircraft testing. The Virginia

Tech subcontract will be under the direction of Dr.

Joe Schetz who is a world expert in the modeling

and measurement of complex flow fields and the

first researcher to simultaneously measure skin

friction and heat flux at a single location. During

Phase I, together with Dr. Schetz, F&S proposes to

leverage previous experience in the development of

combined optical fiber pressure and skin friction

sensors developed primarily for wind tunnel

applications and investigate the feasibility of

miniaturizing and ruggedizing these sensor arrays

to make them compatible with the harsh aircraft

environment.

Potential Commercial Applications (Limit 200 words)

In addition to NASA's need for high-performance

optical fiber sensors for flight test applications,

there is a large commercial market for such sensors

for wind tunnel test applications, transportation

system design, development and operation,

semiconductor fabrication, commercial jet engines,

automobile engines, the metal, ceramic and wood

processing industries, and the power generation and

monitoring systems for coal-fired, nuclear and

fuel-cell technologies. F&S has also identified many

end users of micromachined optical fiber sensors

within the government such as Air Force, NASA,

DARPA, Navy, and the DOE.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Scott Meller

F&S, Inc.

2801 Commerce Street

Blacksburg , VA 24060

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Garnett S. Linkous

F&S, Inc.

2801 Commerce Street

Blacksburg , VA 24060

Form 9.B Project Summary

Chron 971610

Proposal Number 97-1 07.03-4646B

Project Title Flight Tests of the Low Speed Characteristics of a Hypersonic Waverider Configuration

Technical Abstract

A series of flight tests of the LoFLYTE(TM) aircraft are planned, with the goal of fully

characterizing LoFLYTE(TM)'s aerodynamics, evaluating possible modifications and

enhancements to the aircraft, evaluating LoFLYTE(TM)'s neural adaptive flight control

system, and verifying the controller's generiticity. In the former area a series of flight

tests directed towards the exploration of LoFLYTE(TM) flight envelope, characterization of

its SERN nozzle, and elimination of the dutch roll phenomena are anticipated. In the

control area, flight tests designed to evaluate the performance of the flight controller in

extreme environments; in the face of aircraft modifications, system failures and/or

aircraft damage; and under fully autonomous control are anticipated. A Flight Test Program

Plan will be developed to ensure safe and efficient conduct of the flight test experiments.

Potential Commercial Applications

Fully developing the low speed characteristics of a hypersonic waverider configuration with

an advanced neural vehicle management system provides several near term applications of the

resulting technologies to subsonic, supersonic and hypersonic flight vehicles. The benefits

of this program exhibit tremendous longer term potential applications to operational

military and civilian vehicles. Research applications include subsonic target drone

applications, Mach 2 to 4 ramjet powered vehicles and Mach 4 to 8 dual mode ram/scramjet

powered vehicles. The United States Navy in its Mission Needs Statement has identified the

requirement for a hypersonic vehicle for military missions.

Name and Address of Offeror

Firm: Accurate Automation Corp

Name: Robert M. Pap

Street: 7001 Shallowford Road

City: Chattanooga

ST: TN ZIP: 37421

Name and Address Of Principal Investigator

Firm: Accurate Automation Corp

Name: Walter Sefic

Street: 7001 Shallowford Road

City: Chattanooga

ST: TN ZIP: 37421

Form 9.B Project Summary

Chron:

971396

Proposal Number:

07.04-6100

Project Title:

Large-Scale Performance

Improvements of RBCC Engines Using

the Dynamic Ejector

Technical Abstract (Limit 200 words)

A unique and innovative approach to significantly

increasing the thrust performance of

ejector-configured, rocket-based combined-cycle

(RBCC) engines is proposed. The approach

involves oscillating (switching) the rocket exhaust

at high frequency (the dynamic ejector), rather than

permitting it to simply flow coaxially with the

induced air as in a conventional ejector

configuration. Since the sole mechanism for

transferring momentum and energy between the

two streams in a conventional ejector is viscous

shear through turbulent jet mixing, very large

losses result. This leads to lower thrust levels

(hence, specific impulse) than those achievable

using a more efficient method of momentum and

energy exchange. It is shown herein that oscillation

of the rocket exhaust using secondary fluid

injection (as in thrust vector control techniques)

results in a far more efficient transfer of momentum

and energy, leading to very significant increases in

specific impulse, probably in excess of 50% thrust

augmentation. The proposed concept is responsive

to the solicitation's subtopic calling for "high thrust

performance of ejector-ramjets...at take-off of the

hypersonic vehicle..." Indeed, the performance

benefits derived from the proposed concept occur

principally at take-off.

Potential Commercial Applications (Limit 200 words)

Ejector ram/scramjets will be found to be a cost

effective, high performance propulsion system

technology in the near future. The participants in

NASA's ARTT program have already committed to

this technology. We will seek to move the

technology developed in Phases I and II into

prototype and full-scale engine development in

Phase III, with application to three market sectors:

the military, civil and commercial marketplaces,

both domestic and foreign. The Phase III objectives

will be to continue the process of evolving the

integrated, dynamic ejector-based, RBCC ejector

ram/scramjet, and further reducing the technology

risk through system demonstration at the

prototype, then full-scale level. The reduction of

technical risk is a required precursor to the

reduction of business risk. This, then, is a precursor

to positive investment decisions.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Wallace Chinitz

GASL, Inc.

77 Raynor Avenue

Ronkonkoma , NY 11747-6648

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

John I. Erdos

GASL, Inc.

77 Raynor Avenue

Ronkonkoma , NY 11747-6648

Form 9.B Project Summary

Chron:

970863

Proposal Number:

07.04-7100b

Project Title:

A Pulsed Detonation Engine Ejector

Concept for High Performance

Propulsion

Technical Abstract (Limit 200 words)

MSE Technology Applications, Inc. (MSE)

proposes to evaluate and test a Pulsed Detonation

Engine-Ejector (PDEE) concept for hypersonic

vehicle design. Due to its high specific

performance, design simplicity, and low weight, the

Pulsed Detonation Engine (PDE) is a good

candidate for the low-speed propulsion system for

hypersonic vehicles if the PDE thrust levels can be

increased. This cannot be easily accomplished by

increased pressurization, and there is a practical

size limit on the PDE that can be integrated into the

vehicle. The ejector concept solves that problem by

using the mass flow of a secondary stream for

thrust augmentation. Using the Ramjet/Scramjet

engine as the secondary channel makes use of

existing hardware and does not increase the overall

engine weight. The proposed engine design relies

on the unsteady ejector concept, which is proven to

be much more efficient than the steady ejector,

such as the Rocket-Based Combined-Cycle

(RBCC) engine. This innovative concept also

extends the combustion regime of previous

unsteady ejector designs to the detonation mode,

which can produce higher ejector performance. The

proposed PDEE can therefore simultaneously

achieve the high specific impulse and high

thrust-to-weight required for single-stage

hypersonic vehicles.

Potential Commercial Applications (Limit 200 words)

The proposed PDE-Ejector concept can be used for

the design of the low-speed propulsion system for

hypersonic vehicles. The successful design of this

engine component is extremely important for

NASA, the Air Force, and several private-sector

companies interested in the manufacture of

reusable launch vehicles for the placement in orbit

of a constellation of satellites. The concept can be

applied to large reusable hypersonic vehicles or as

boosters to expendable vehicles. Further

refinement of the technology, notably

miniaturization and soundproofing can also lead to

cruise missile applications and the design of

propulsion systems for a wide range of military and

civilian applications. MSE is also presently

collaborating on PDE technology development with

United Technologies Research Center (UTRC) and

Pratt & Whitney, who may be partners in the

proposed R&D effort and in the commercial

development of the technology.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jean-Luc Cambier

MSE Technology Applications, Inc.

P. O. Box 4078

Butte , MT 59702

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Michael R. Tuck

MSE Technology Applications, Inc.

P. O. Box 4078

Butte , MT 59702

Form 9.B Project Summary

Chron:

971421

Proposal Number:

08.01-6420

Project Title:

Novel Conformal Sandwich Panel

Structures

Technical Abstract (Limit 200 words)

The proposed program will demonstrate the ability

to produce novel conformal titanium sandwich panel

structures. Specifically, techniques will be

demonstrated for controlled thermal spraying and

selective laser sintering of functionally gradient,

conformal, porous titanium structures. Further

enhancements to the specific stiffness will be

achieved through an innovative process enabling

ceramic microspheres to be co-sprayed with a

titanium matrix. The resultant structure will have

controlled porosity varying from 0-60%, with

graded distributions of both porosity and ceramic

fillers. Structures fabricated using the proposed

process will be suitable for use in high speed flight

vehicles and space structures including cryogenic

tanks, cowlings, thermal protection structures and

substructures, and other flight vehicle structures.

The program will develop, using laser fusion and

thermal spray techniques, titanium structures

graded from 100% dense to less than 50% dense in

a relaible, repeatable manner. The processing

method relies on the use of innovative sintering aid

titanium encapsulated metal powders and fillers and

controlled heat input during thermal spray

deposition. This spraying of semi-solid particles will

result in a fully dense deposit ranging from 30 mils

to over 1/2 inch in thickness.

Potential Commercial Applications (Limit 200 words)

Anticipated Program Results: Successful

completion of the proposed program will result in

thermal spray/lasar fusion parameters and

microentineered raw materials enabling the buildup

of conformal Ti structures ranging from fully dense

to 60% porous in a repeatable, controlled manner.

These structures will ifnd applications in launch

vehicle structures, including thermal control

structures for operation at 400-800 degrees C,

aircraft structures, combustion engine structures,

injectors, and corrosion resistant coatings.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Animesh Bose

Powdermet, Inc.

416 Trinity Court

Petaluma , CA 94954

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Andrew J. Sherman

Powdermet, Inc.

9960 Glenoaks Blvd., Unit A

SunValley , CA 91352

Form 9.B Project Summary

Chron:

971542

Proposal

Number:

08.01-8074

Project Title:

Prediction of Launch Vehicle Ignition

Overpressure and Liftoff Acoustic

Environments

Technical Abstract (Limit 200 words)

The proposed research addresses a problem of

importance to the design of both expendable and

reusable launch vehicle structures and the satellites

they carry. During rocket engine ignition at liftoff, a

shock wave and exhaust gas mass flow are

produced which interact with the launch pad to

generate pressure waves (Ignition Overpressure or

IOP) that impact the vehicle and cause both

overpressure loading and acoustic concerns. In

addition, the rocket plume generates acoustic

waves which, in turn, interact with the launch pad

geometry and impact the launch vehicle.

The proposed work will extend an existing

simulation of rocket ignition and plume generated

overpressure and acoustic fields to a wide range of

launch vehicles and launch facilities and allow rapid

determination of the structural forcing functions

imposed during launch.

An existing database of Shuttle and Titan data will

be expanded to include all available flight and test

data. The data will be characterized in terms of the

rocket and launch complex characteristics. Selected

data records will be employed to validate the

numerical predictions. Code modifications will be

completed during Phase II of the project.

Potential Commercial Applications (Limit 200 words)

The application of this technology to commercial

launch vehicles and satellites will enable the

determination of critical design loads when

launching a payload on any particular launch

vehicle at a selected launch complex and will offer

methods to predict mitigated overpressure and/or

acoustic environments if the payload and/or launch

vehicle survival is in question.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Gary M. Ogg

Applied Research Associates, Inc.

5941 S. Middlefield Road, Suite 100

Littleton , CO 80123

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Peter T. Dzwilewski

Applied Research Associates, Inc.

4300 San Mateo Blvd., NE, Suite A220

Albuquerque , NM 87110

Form 9.B Project Summary

Chron:

970878

Proposal

Number:

08.01-9457

Project Title:

An Integrated Aerodynamic

Design/Analysis Approach for Advanced

Launch Vehicles

Technical Abstract (Limit 200 words)

A unified aerodynamic design and analysis

procedure for advanced reusable launch vehicles is

proposed as a means to reduce the number of

design iterations for a new vehicle. State-of-the-art

analysis methods, recent technology advances, and

historical knowledge and experience will be

assembled into a knowledge-based system to

provide an economical, unique, and practical means

to analyze and evaluate new designs during the

conceptual, preliminary, and final design phases of

new launch vehicles. The proposed approach is

based on techniques which have proven successful

for a number of launch vehicles. The goal is to

efficiently evaluate the impact of vehicle

aerodynamics on performance, structures, guidance

and control, and cost early in the design. In Phase I,

the feasibility of the design/analysis procedure will

be demonstrated with a prototype system which

includes the latest advances in computational

technology as well as experience from the past. The

proposed procedure is needed by NASA, DoD, and

the new launch provider companies to decrease

design cycle time and thus design costs. Its

commercial potential has been demonstrated by

NEAR during aerodynamic analyses for

commercial booster designs.

Potential Commercial Applications (Limit 200 words)

The proposed aerodynamic design and analysis

method will have commercial application to NASA,

DoD, and commercial launch service providers who

are designing new advanced launch vehicles. The

method will help reduce the number of design

iterations, thus reducing vehicle development costs.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael R. Mendenhall

Nielsen Engineering & Research

526 Clyde Avenue

Mountain View , CA 94043-2212

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Michael R. Mendenhall

Nielsen Engineering & Research, Inc.

526 Clyde Avenue

Mountain View , CA 94043-2212

Form 9.B Project Summary

Chron:

970632

Proposal Number:

08.02-0074

Project Title:

Rocket Thrust System for Reusable

Launch Vehicle Powered by the QED

IEF Power Plant

Technical Abstract (Limit 200 words)

The QED Engine concept offers to the space

program of the 21st Century

a potentially economical means of space access

using single-stage to

orbit and highly reusuable launch vehicle

technologies. Based upon

the posited existence of a compact, lightweight

fusion electric power

source, the QED Engine involves the conversion of

fusion power into

the heating of a working fluid whose subsequent

expansion produces

thrust. The specific innovation proposed here is the

means by which

this power coupling is achieved, and in how the

heated propellant is

to produce thrust. In the proposed effort, the

coupling of power from

an electron beam into a plasma for the purpose of

heating the plasma

to conditions appropriate for producing thrust will

be examined. The

expansion of the heated plasma through a nozzle

created by a carefully

tailored magnetic field, and how this magnetic

nozzle and the plasma

parameters can be configured to optimize thrust will

also be examined.

Phase I will culminate in an understanding of the

appropriate

parameter regimes for the electron beam, the

in-flowing working fluid,

and the magnetic field of the nozzle. This will lay the

groundwork

for more specific investigations and

experimentation.

Potential Commercial Applications (Limit 200 words)

The effort proposed here forms the basis of a larger

and longer term

effort whose success will result in a widespread

commercialization of

space. Involvement of the private sector in

developing early

engineering models of the QED Engine will produce

the earliest

commercial returns from licensing agreements

involving technology

developed in this program.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael H. Frese

NumerEx

1400 Central Ave., SE, STE 2000

Albuquerque , NM 87106-4811

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Michael H. Frese

NumerEx

1400 Central Ave., SE, STE 200

Albuquerque , NM 87106-4811

Form 9.B Project Summary

Chron:

970528

Proposal Number:

08.02-0400

Project Title:

The Terminator Tether: A Low-Mass

System for End-of-Life Deorbit of LEO

Spacecraft

Technical Abstract (Limit 200 words)

The Terminator Tether will utilize propellantless

electrodynamic tether drag to provide a low-mass

means of removing LEO spacecraft from orbit at

the end of their operational lifetimes to prevent the

build-up of orbital debris. The Terminator Tether

will be a small autonomous package that is attached

to a spacecraft before launch. When the satellite

fails, or is no longer needed in orbit, the system will

deploy a conducting tether weighing a small

percentage of the spacecraft mass. This tether will

interact with the Earth's magnetic field, generating

a voltage along the tether. The induced voltage will

drive a current along the tether. The interaction of

the current with the geomagnetic field will generate

a force opposed to the spacecraft's orbital motion.

This drag force is sufficient to deorbit the

spacecraft within several weeks or months,

compared to decades or millennia for atmospheric

drag alone. The SBIR effort will develop innovative

concepts for lightweight subsystems for deploying

survivable conducting tethers, controlling the

dynamics of the tether, and emitting electrons from

the negative end of the tether. These innovations

will enable the Terminator Tether to provide a rapid

deorbit method that requires significantly less mass

than a conventional rocket system.

Potential Commercial Applications (Limit 200 words)

The Terminator Tether will find commercial

applications on every satellite and upper stage

placed into orbits between 500 and 1500 km

altitude. Within the next decade, the number of

satellites in LEO will grow rapidly. Unless these

spacecraft are removed from LEO at the end of

their lifetimes, LEO will soon become filled with

derelict spacecraft and orbital debris. The standard

method of deorbiting a satellite is to use rockets.

This method, however, requires that a large fraction

of the satellite launch mass be allocated for deorbit

propellant. Moreover, it requires that the rocket

and guidance systems be functional. The

Terminator Tether can provide rapid deorbit while

requiring only a small percentage of the launch

mass, maximizing the amount of payload mass that

can be used for transponders and stationkeeping

propellant. In addition, it can deorbit satellites even

after the satellite's power and attitude control

systems have failed. Commercial potential is

demonstrated by the fact that Teledesic has

expressed a strong interest in using the Terminator

Tether on their satellites and dispensers, a launch

system company has offered free test flights worth

$4,500,000, and an investment group has expressed

interest in providing $2,000,000-$5,000,000 in

Phase III funding.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Robert P. Hoyt

Tethers Unlimited, Inc.

1917 NE 143rd St.

Seattle , WA 98125-3236

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Robert L. Forward

Tethers Unlimited, Inc.

8114 Pebble Ct.

Clinton , WA 98236

Form 9.B Project Summary

Chron:

971476

Proposal

Number:

08.02-1122

Project Title:

HIGH-EFFICIENCY, GAS-FUELED

PULSED PLASMA THRUSTER WITH

ALL-SOLID-STATE DRIVE

Technical Abstract (Limit 200 words)

The objective of this effort is to develop a compact,

efficient, gas-fueled pulsed plasma thruster (PPT)

for space propulsion applications. Pulsed power to

drive the thruster will be delivered via a highly

reliable, all-solid-state nonlinear magnetic pulse

compressor to be optimized specifically for pulsed

plasma thruster applications. Initial

proof-of-concept demonstrations conducted at

Princeton University's Electric Propulsion and

Plasma Dynamics Laboratory (EPPDyL) have

demonstrated up to 50% electrical efficiency with

mass utilization efficiencies approaching 100%. The

thruster has also been designed so as to be

propellant insensitive, opening up the possibility of

utilizing propellants which might be mined at the

destination for the return trip.

Potential Commercial Applications (Limit 200 words)

Successful completion of this SBIR will result in a

new class of efficient, reliable, lightweight electric

thrusters for space-based propulsion. These

thrusters will be suitable for providing either

primary propulsion or stationkeeping requirements

to a vast array of commercial satellites.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

DANIEL BIRX

SCIENCE RESEARCH LABORATORY INC

15 WARD ST

SOMERVILLE , MA 02143

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

JONAH JACOB

SCIENCE RESEARCH LABORATORY, INC.

15 WARD ST

SOMERVILLE , MA 02143

Form 9.B Project Summary

Chron:

970252

Proposal Number:

08.02-1170

Project Title:

Antimatter Production at a Potential

Boundary

Technical Abstract (Limit 200 words)

Current antiproton production techniques rely on

high energy collisions between beam particles and

target nuclei to produce particle and antiparticle

pairs, but inherently low production and capture

efficiencies make these techniques inadequate for

the cost-effective production of antimatter for space

propulsion and other commercial applications.

Based on Dirac's theory of the vacuum field, an

innovative antimatter production technique is

proposed in which particle-antiparticle pairs are

created at the boundary of a steep potential step

formed by the suppression of local vacuum fields. A

quantum mechanical analysis of spin-1/2 particle

tunneling and reflection from a potential barrier is

presented which shows that matter particles will be

reflected from the potential step while antimatter

particles continue through the potential barrier,

where they can subsequently be collected and

stored for future use. Techniques for generating the

required potential barrier are discussed, and an

experimental Phase I research program is outlined

that will demonstrate the feasibility of the proposed

technique for antiparticle production. If successful,

the proposed research will lead to the development

of an efficient, cost- effective method to generate

antimatter in sufficient quantities for commercial

and space exploration activities.

Potential Commercial Applications (Limit 200 words)

If successful, the proposed technology will provide

a cost effective method to produce antimatter in

sufficient quantities for spacecraft propulsion and

other commercial applications, including on-site

medical radiation treatments, nondestructive

material testing, and material processing

applications.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Michael R. LaPointe, Ph.D.

Horizon Technologies Dev. Group

4168 Rocky River Drive

Cleveland , OH 44135-1188

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Michael R. LaPointe, Ph.D.

Horizon Technologies Dev. Group

4168 Rocky River Drive

Cleveland , OH 44135-1188

Form 9.B Project Summary

Chron:

970993

Proposal

Number:

08.02-1676

Project Title:

Design of a High-Efficiency Antiproton

Degrader/Accumulator to Support

Advanced Propulsion Research

Technical Abstract (Limit 200 words)

Antiprotons offer the highest potential performance

in advanced space propulsion systems. Several

concepts for using antiprotons for propulsion have

been developed during the past decade. To date,

however, a source of low energy antiprotons to

perform feasibility experiments has not been

available. Because of the recent development of the

high-capacity portable trap developed by G. A.

Smith at Penn State University, the storage

technology now exceeds the production capacity at

the world's acclerators. We intend to design and

computationally verify a new solid-state degrader

that will allow a two order of magnitude increase in

the availability of storable antiprotons. This will

allow the new traps to be filled in hours instead of

months which will enable antiproton reearch to

advance in a number of directions including

proof-of-concept experiments in advanced

propulsion.

Potential Commercial Applications (Limit 200 words)

The potential for commercial applications using

antiprotons is tremendous. Although several

researchers have postulated the need for a portable

source of low energy antiprotons for physics

research and energy source development, the most

promising near term commercial use is in the

production of short-lived, biomedical radioisotopes.

These isotopes are currently used to detect many

forms of cancer using Positron Emission

Tomography. The isotopes, however, are currently

limted to expensive production facilites. A portable

source would allow a 100 fold increase of the

availablility of PET scans across the nation. In

addition to the PET application, antiprotons can be

used in conjunction with proton beam therapy to

precisely locate the end-point position of the proton

beam. Proton therapy is a rapidly growing

procedure at the Massachusetts General and Loma

Linda facilities. Both of these industries could be

revolutionized or enhanced by the development of a

portable source of antiprotons that can be rapidly

refilled. This proposal will enable that technology.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Steven D. Howe

Synergistic Technologies, Inc.

19 Karen Circle

Los Alamos , NM 87544

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Steven D. Howe

Synergistic Technologies, Inc.

19 Karen Circle

Los Alamos , NM 87544

Form 9.B Project Summary

Chron:

970592

Proposal

Number:

08.02-2500

Project Title:

METASTABLE ELECTROEXPLODED

NANOPHASE ALUMINUM BASED

GELS AS A COMPONENT OF

PROPULSION FUELS

Technical Abstract (Limit 200 words)

Aluminum powder is an additive to many

propellants. For more than 60 years attempts to use

it as an energy enhancer for hydrocarbons were not

very successful. Metastable electroexploded

nanosize aluminum powder (Alex), could revitalize

NASA's Metallized Propellant Program. Alex and

other metals produced by the electroexplosion of

metal wire are metastable, producing additional

energy and burning rate. Alex based gels with

water, hydrazine or mixtures of the two, melt as low

as -92C, and burn to produce hot hydrogen at flame

temperatures around 3,200K. Alex may be

passivated by microencapsulation in paraffin

coatings that protects it from spontaneous reaction

with air or reaction in boiling water. Yet, recent

tests show that such Alex when mixed into

kerosene will burn to completion in a

hydrocarbon/air flame, while coarser aluminum in

kerosene could not be ignited or burned at all. The

objectives of the Phase 1 study are to formulate

water and RP-1 gels and test them to determine

combustion characteristics. In Phase 2 we would

perform rocket motor tests to prove the utility of

both Alex/ water as a monopropellant as well as

using Alex to increase the energy and speed of

burning of RP-1.

Potential Commercial Applications (Limit 200 words)

Alex/water gels have application as

monopropellants for small space rockets. They may

also have application as a convenient and energetic

pyrotechnic that can be used as a hydrogen source,

generating heat and light in underwater

applications, and as a heat source in certain welding

and joining applications. Alex additives to

hydrocarbon fuels may find use in ramjets,

scramjets and other air-breathing engines to

enhance the specific mass-energy density of such

engines, and to stabilize their burning. Proving the

utility of Alex gels would enhance the sales of Alex,

already being manufactured and sold by Argonide

for propulsion and energetic applications.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Frederick Tepper

The Argonide Corporation

240 Power Court, Suite 108

Sanford , FL 32771-9530

Form 9.B Project Summary

Chron:

971226

Proposal

Number:

08.05-2306

Project Title:

Emission tomography for non-intrusive

three-dimensional measurements of

density, temperature, and chemical

composition in rocket engine plumes

Technical Abstract (Limit 200 words)

This proposal presents an economical instrument

for making global measurements of density,

temperature, and constituent concentration of

rocket engine plumes. This innovative technique is

based on collecting emitted flame radiation from a

large number of viewing angles; the irradiance

depends on the integrated effects of gas and

particulate temperature and species concentration

along the optical path. Using a large number of

intersecting optical paths allows the resulting set of

radiative transfer equations to be inverted to obtain

the spatial temperature profile of the flame or

plume. This emission tomography approach is

appealing because, unlike conventional

transmission tomography, neither probe beams nor

their associated optics are required. Therefore,

only simple optical access to the combustion

chamber is required to implement this technique.

Emission tomography can be used with both

stimulated and spontaneously emitted radiation,

and spectroscopic methods may be used to isolate

the concentration of one or more constituents. By

using two emission lines of a known species, the

temperature may be extracted by a simple two color

technique. Prior simulations and experiments

presented here illustrate that with simple optical

geometry and a single camera, the reaction zone of

a diffusion flame may be accurately identified; this

illustration applies equally well to temperature

measurement. Iterative algorithms are necessary to

account for self-absorption and refraction effects.

This technique may also be applied directly to other

gas phase processes.

Potential Commercial Applications (Limit 200 words)

The proposed instrument will provide three

dimensional density, temperature, and constituent

concentration measurements using spectroscopic

emission computed tomography. This instrument

will be useful in both research and industrial

monitoring applications, having applications in

areas requiring three dimensional measurement.

Significant applications include high temperature

gas dynamics, welding, plasma spray, and other gas

phase flows.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Timothy D. Upton

Northeast Photosciences, Inc.

18 Flagg Rd.

Hollis , NH 03049

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Paul Bagley

Northeast Photosciences, Inc.

18 Flagg Road

Hollis , NH 03049

Form 9.B Project Summary

Chron:

970070

Proposal Number:

09.03-1248A

Project Title:

A digital holographic monitor for

protein crystals and materials science

Technical Abstract (Limit 200 words)

Proposed innovation: Holographic methods

measure how crystallization parameters influence

protein crystal size, quality, and growth rates.

Traditional holography is labor-intensive and

difficult to use in-orbit. We propose a Digital

Holographic Monitor (DHM) that records on a

CCD array and numerically reconstructs

interferometric and high resolution images in near

real-time.

Project objectives: The central goal is to

demonstrate digital holographic recording of crystal

growth and important materials science parameters

such as temperature and concentration. We build on

and tailor technology we developed for marine

applications.

Effort proposed: (1) Determine measurement

parameters and operational constraints; (2)

construct test samples and record holographically;

(3) verify critical modules under flight conditions;

and (4) develop a Phase II DHM design.

Results anticipated: Phase I results should include

a detailed Phase II DHM design and development

roadmap. The Phase II DHM will be a near flight

prototype.

Expected NASA applications: The DHM supports

experiments such as the Interferometric Study of

Protein Crystal Growth (IPCG) that differentiate

low-g growth from the ground-based process. The

DHM is also valuable for materials science

experiments in fluid mechanics, mixing,

solidification, and other processes that require

monitoring of density fluctuations or high resolution

imaging through deep depths of field.

Potential Commercial Applications (Limit 200 words)

In addition to the proposed biotechnology and

materials science applications, holography has

proven useful in non-destructive testing, surface

characterization, and particle classification and

monitoring. A compact, robust, and stable

instrument such as the DHM should be important

for high-precision industrial monitoring and testing

and environmental sensing.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Robert B. Owen

Owen Research inc.

2525 Arapahoe Ave/Suite E4-262

Boulder , CO 80302-6720

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. Brian L. Sperry

Owen Research inc.

2525 Arapahoe Avenue/ Suite E4-262

Boulder , CO 80302-6720

Form 9.B Project Summary

Chron:

971573

Proposal

Number:

09.03-4800

Project Title:

A Validated Computational Model to

Enable Real Time Control of the Pulsed

OMCVD Process for Heteroepitaxy of

Compound Semiconductors

Technical Abstract (Limit 200 words)

Pulsed Organo-Metallic Chemical Vapor

Deposition (OMCVD) is being investigated for

ground-based and microgravity applications by

NASA and North Carolina State University (NCSU)

as an effective technique to eliminate defects

during heteroepitaxial growth of compound

semiconductors. This technique requires tight

process control to regulate the sequence and

duration of pulses in response to instantaneous

growth patterns. It is proposed to develop and

validate an advanced computational tool as a

critical enabling technology for process control for

pulsed OMCVD.

Phase I will focus on developing a kinetic model for

the surface reaction pathways during OMCVD. The

model will be tested by implementation into an

existing CFD code. A multi-dimensional

computational model will be developed for the

NCSU OMCVD reactor and detailed simulations of

flow, heat/mass transfer and gas/surface chemistry

will be performed. The model predictions for

ground-based growth will be validated against

measured NCSU data . The model will also be used

in support of the NCSU space flight experiment

design and operation. The Phase II work will focus

on extensive validation of the chemistry models

over a range of operating conditions. Advanced

Monte Carlo models will be applied to understand

the microstructural evolution of the film. A series of

parametric simulations will be performed to

determine optimal operating conditions for the

reactor. The model will be fully validated using

ground-based and microgravity flight data.

Potential Commercial Applications (Limit 200 words)

Heteroepitaxy of compound semiconductor

materials on heterogeneous substrates is a vital

technology for optoelectronics in the blue to

ultra-violet wavelength region and non-linear optics

in the infra-red region and power devices and

integrated sensor devices. The proposed model will

be an enabling technology in demonstrating

defect-free heteroepitaxial growth by facilitating

appropriate control of the pulsed OMCVD process.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Samuel A. Lowry

CFD Research Corporation

215 Wynn Drive

Huntsville , AL 35805

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Andrzej J. Przekwas

CFD Research Corporation

215 Wynn Dr.

Huntsville , AL 35805

Form 9.B Project Summary

Chron:

971175

Proposal

Number:

09.03-6458

Project Title:

Gasless Combustion-Driven Furnace for

Materials Research in Microgravity

Technical Abstract (Limit 200 words)

The limits of electrical power available for furnaces

in space-based materials science experiments

severely restricts the maximum attainable

temperatures and the size of the processed

samples. The overall energy density stored in

chemical fuels is several orders of magnitude

greater than electrical batteries or fuel cells.

Conventional fuels, however, cannot be used in

space because of the hazard caused by the

generation of large quantities of hot gaseous

products. A novel concept for heating elements

utilizing gasless combustion of compacted powders

will allow very high temperatures (T > 3000 K) and

high energy densities for use in materials

processing. Furnaces using these heating elements

will be extremely simple and economical, and due to

the wide variety of the reactants available they can

be tailored to the specific needs of a particular

experiment (maximum temperature, duration). The

feasibility of the concept will be demonstrated by

assembling and testing gasless combustion-driven

heating elements that will provide short-duration

peak temperatures in the range of 2500-3000 K or

long-duration stable temperatures in the range of

1000-1500 K. Phase II research will target higher

temperatures (3000-4000 K), and a variety of

combustion-driven heating elements will be

designed for microgravity materials science

applications.

Potential Commercial Applications (Limit 200 words)

Gasless combustion-driven heating elements will

supplement or replace existing furnaces for

materials processing in space. These elements will

be especially useful for applications which require

short-duration high-peak temperatures, in sounding

rockets and satellites where the available electrical

power comes from batteries, and in trial

experiments where designing a permanent

specialized furnace is not economically feasible.

Spin-off of the work may also lead to the

development of heating cartridges for geological

analysis in the field (analysis for dissolved gases),

safe heating elements for canned foods, etc.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Samuel Goroshin

Combustion Technologies International

P.O. Box 090080

Brooklyn , NY 11209-0080

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Samuel Goroshin

Combustion Technologies International

P.O. Box 090080

Brooklyn , NY 11209-0080

Form 9.B Project Summary

Chron:

970109

Proposal Number:

09.03-6634

Project Title:

Apparatus and procedures for

microgravity synthesis of photonic

crystals

Technical Abstract (Limit 200 words)

The innovation proposed comprises a system which

will support the first ever synthesis of a mesoscopic

crystal in a microgravity environment by external

illumination. This organization of microparticles will

be effected in an evacuated cell by

counter-propagating beams generated by a compact

laser. The resulting structure will have lattice

dimensions directly determined by the incident

field. With the apparatus to be developed for

microgravity operation, the particles will be

practically motionless unless disturbed directly or

through electromagnetic force. This will make the

flux intensity requirement for self-organization

considerably less than the necessary intensity on

earth, which must overcome convection forces.

Phase I will entail an investigation which will result

in an in-depth expertise in the system to be

developed. The investigation will deal with

microparticles in a fluid suspension to compensate

for gravity. Phase II will involve the design and

prototyping of a unit that can serve in orbiting

microgravity experiments.

Potential Commercial Applications (Limit 200 words)

Commercialization can be implemented for

spaceborne applications. The basic nature of the

requirements for the desired effects are easily

translated into a low-cost system. The capabilities

of such a system will fill the needs of missions both

in space and on the ground. Ordered phases of

materials are extremely valuable in electronics,

optics and acoustics. In electronics: solar cells and

other photovoltaics will operate with dramatically

increased efficiency due to the emission

modification of the periodic structure imposed. In

optics: frequency-agile filters can be formed with

the particles in a fluid or vacuum host, due to the

wavelength dependency of the lattice constant.

Acoustical filters can be effected as well. Scaled-up

versions of this system can foreseeably make

possible the management of debris. Thus, as space

missions become more cost-contained, the stable

environment for binary media (particle

distributions) provided by this system will be

available to and utilized by an increasing number of

government and industrial customers: aerospace

agencies, communication and surveillance entities,

scientific research companies alike, will have a

need for a system with the capabilities described,

and the means to attain this system will be within

reach.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Laurence Malley, Ph.D.

Altair Center

48-12 Briarwood Lane

Marlborough , MA 01752

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Sergei Krivoshlykov, Ph.D.

Altair Center

48-12 Briarwood Lane

Marlborough , MA 01752

Form 9.B Project Summary

Chron:

970386

Proposal

Number:

09.03-8912

Project Title:

Applying X-ray Topography &

Diffractometry to improve Protein

Crystal Growth

Technical Abstract (Limit 200 words)

The proposed innovation is to develop a process

that is sufficiently non-destructive to detect and

analyze protein crystal defects and still permit a

complete conventional diffraction analysis. By

providing a quantitative means to evaluate protein

crystals it will be possible to gain insights into how

to improve their quality. By this process,

experimental and theoretical research in utilizing

the influence of microgravity in protein crystal

growth can be advanced.

The project is mainly concerned with the

microscopic technique called X-ray topography. An

understanding of the defect structures formed in

macromolecular crystals is important if growth

conditions are to be optimized. To a large extent the

success of the semiconductor industry in growing

large, defect free crystals of silicon and germanium

is due to efforts similar to the effort we are

proposing.

While X-ray diffraction is an inherently destructive

process for many protein crystals and in time will

destroy a macromolecular crystal, the process that

will be developed during this research is expected

to be sufficiently non-destructive that after the

topographic analysis it should be possible to

perform a complete conventional diffraction

analysis, determine the structure of the

macromolecule, and evaluate the quality of the

structural parameters which result.

Potential Commercial Applications (Limit 200 words)

Once fully developed and demonstrated this

process will be a vital tool in growing crystals that

can yield high resolution structural data for

structure-based drug design and for government,

industry and university macromolecular

researchers. To those performing protein crystal

growth on the shuttle and Space Station it will

enable the crystal growing process for the species

being studied to be optimized on the ground before

using these costly and limited resources.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Leonard Arnowitz

BioSpace International, Inc.

335 Paint Branch Drive

College Park , MD 20742

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Leonard Arnowitz

BioSpace International, Inc.

335 Paint Branch Drive

College Park , MD 20742

Form 9.B Project Summary

Chron:

971180

Proposal Number:

09.04-1322

Project Title:

Tunable UV Light Source for

Quantitative Microgravity Combustion

Diagnostics

Technical Abstract (Limit 200 words)

Combustion studies in microgravity are critical to

ensuring the safety of personnel onboard space

craft as well as for improving our knowledge of

combustion phenomena. Under microgravity

conditions, flame ignition, propagation and

extinction become simplified due to the lack of

buoyancy. Quantitative monitoring of combustion

radicals, which control combustion kinetics although

present in trace quantities, is critical to

understanding of combustion and provides tests for

flame modeling. Many currently available

laboratory-based combustion diagnostics cannot be

adapted for microgravity experiments due to unique

space and power constraints. We propose

developing a near-UV laser source for quantitative

combustion radical diagnostics. The instrument will

measure absolute concentration distributions in

laminar and turbulent flames and will be compatible

with NASA Lewis drop tower rigs. Our approach

uses nonlinear upconversion of diode laser light to

measure simultaneously line-of-sight optical

absorbance and laser induced fluorescence images.

We target quantitative monitoring of CH and C2

radicals with 10 Hz (or better) time resolution per

two-dimensional LIF image. With the continued

development of high power diode lasers especially

at visible wavelengths, we envision this technique to

be readily extended to deeper UV wavelengths to

access other species including OH.

Potential Commercial Applications (Limit 200 words)

The proposed technology could be used as a new

combustion diagnostic tool in wind tunnel

combustion facilities, development of new

generations of rocket and jet engines, and turbine

development. In environmental monitoring

applications, many important trace molecular and

atomic species can be probed by accessing strong

electronic transitions using tunable UV and blue

radiation generated by diode laser up conversion.

Such applications include continuous emissions

monitoring of stationary power plants and municipal

incinerators, and perimeter monitoring of chemical

plants and oil refineries.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Daniel B. Oh

Southwest Sciences, Inc.

1570 Pacheco St., Suite E-11

Santa Fe , NM 87505

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Alan C. Stanton

Southwest Sciences, Inc.

1570 Pacheco St., Suite E-11

Santa Fe , NM 87505

Form 9.B Project Summary

Chron:

970178

Proposal Number:

09.04-7288

Project Title:

Fast Infrared Linear Miniature

Spectrometer

Technical Abstract (Limit 200 words)

This Small Business Innovation Research Phase I

project involves a feasibility study for a Fast

Infrared Linear Miniature Spectrometer (FILMS)

system for transient, simultaneous measurements

of carbon dioxide and water vapor concentrations,

soot volume fractions and temperatures in reacting

flows. Such measurements will lead to improved

understanding of the structure of turbulent and

laminar flames. Emission spectroscopy has been

used previously in laboratories to obtain

information on carbon dioxide concentrations, soot

volume fractions and temperatures in luminous

flames. However, a commercial instrument that can

reliably provide simultaneous gas concentration,

soot volume fraction and temperature

measurements at a high data rate is not available.

The stand-alone FILMS system that will be

evaluated using a flame spread experiment at the

Japanese Microgravity Research Facility, which is

part of an ongoing NASA project to understand

ignition and the transition to flame spread of solid

fuels. The proposed FILMS will be the first

instrument, capable of obtaining the infrared

spectrum from 2500 to 5000 nm, resolved to 15 nm,

at 500 Hz.

Potential Commercial Applications (Limit 200 words)

Continuous monitoring of the gas species

concentrations, soot volume fractions and

temperatures is useful in all industries that utilize

hydrocarbon fuels as an energy source. The major

motiviating factor that drives development in

continuous monitoring equipment is the ability to

control the combustion process, both to achieve

greater efficiency and lower pollutant emissions.The potential market for continuous monitoring

equipment includes such diverse industries as fire

protection engineering, waste processing, gas

turbine combustors, power plants, powder metal

processing and chemical manufacturing.

For utilizing either species concentrations or

temperatures as control variables, information on

these is required at a very fast rate. The proposed

FILMS is the first spectrometer that is capable of

obtaining the full infrared spectrum from 2500 nm

to 5000 nm at 500 Hz. This is an essential step for

building process control systems. Therfore, the

commercial potential of the FILMS will increase in

the future.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Yudaya Sivathanu

En'Urga Inc.

1291-A Cumberland Avenue

West Lafayette , IN 47906-1385

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Yudaya Sivathanu

En'Urga Inc.

1291-A Cumberland Avenue

West Lafayette , IN 47906-1385

Form 9.B Project Summary

Chron 970921

Proposal Number 97-1 09.05-5000B

Project Title Moisture and Oxygen Content Sensor Suite for Nutrient Delivery Systems

Technical Abstract

This project will develop a small, low power instrumentation package which includes a two

part sensor suite: 1) sensor for monitoring profiles of moisture content, and 2) sensor to

detect O2 concentration in porous substrate nutrient and water delivery systems designed to

support plant growth in space. Long-term plant growth experiments aboard the Mir Orbital

Station have demonstrated that management of water and O2 in porous substrates is

substantially more difficult than in similar systems on earth. The instrument package will

consist of several pairs of moisture-oxygen sensors used to measure concentration profiles

simultaneously. The substrate moisture content sensor will use the thermal pulse method,

which detects changes in thermal conductivity as the substrate moisture content changes.

Significant innovations exist in the concept and design of each sensor as well as the

integration of the sensor into a usable electronics module with calibrated control.

Innovative improvements in moisture sensor construction, reliability, and improved sensor

design will allow calibration transfer from earth to microgravity. The companion O2

concentration sensor will monitor O2 in close proximity to the moisture content sensor to

allow the two profiles to be compared simultaneously. The innovative design of the O2

sensor includes features permitting the miniaturization of an existing commercial sensor

core to provide safe use in wet, O2 diffusion limited environments.

Potential Commercial Applications

The moisture content and wet oxygen sensors will be important additions to advanced plant

nutrient system maintenance and control for space and ground applications. Near-term space

applications include the Biomass Production System and the Plant Research Unit. These

Sensors could become standard sensor additions to commercial growth chambers, be used in

all types of commercial growth systems where monitoring of appropriate moisture content and

aeration are important. The market is significant, especially in ornamental and more

expensive plant materials. Also markets exist for commercial maintenance plantscapes.

Name and Address of Offeror

Firm: Orbital Technologies Corp

Name:Dr. Eric Rice

Street: 1212 Fourier Drive

City: Madison

ST: WI ZIP: 53717

Name and Address Of Principal Investigator

Firm: Orbital Technologies Corp

Name: Jon Frank

Street: 1212 Fourier Drive

City: Madison

ST: WI ZIP: 53717

Form 9.B Project Summary

Chron:

971283

Proposal Number:

10.01-0890A

Project Title:

Mars Aromatic Hydrocarbon and

Olefin Synthesis System

Technical Abstract (Limit 200 words)

The Mars Aromatic Hydrocarbon and Olefin

Synthesis System (MAHOSS) is a device for

producing low hydrogen to carbon (H/C) ratio

hydrocarbons on Mars with minimal power

requirements. It works by combining the CO and

hydrogen output of a RWGS reactor over a

Fischer-Tropsch catalyst to prepare paraffinic

hydrocarbons. These hydrocarbons are thermally

cracked to produce compounds such as ethylene,

propylene, toluene and acetylene. Its primary

advantage is the production of fuel hydrocarbons

that are low in hydrogen content relative to

normally considered fuels, such as methane. This

reduces the amount of liquid hydrogen that must be

imported or the size and power requirements of an

in situ hydrogen recovery unit by a factor of two for

ethylene and propylene, or a factor of four for

toluene and acetylene. The other advantage of the

MAHOSS is the generation of important chemical

feedstocks for plastics production. These uses

make the MAHOSS an attractive concept for early

robotic and manned missions and a critical

technology for development of a permanently

staffed Mars base. Despite the importance of these

compounds, to date there has been no experimental

work done on building an apparatus for in situ

Martian production of aromatic hydrocarbons and

olefins.

Potential Commercial Applications (Limit 200 words)

The potential commercial applications of a

combined RWGS/Fischer-Tropsch reactor are

numerous, particularly with the current

international interest in reducing CO2 emissions.

The RWGS can use a carbon dioxide feed from a

power plant or other source and can create syngas.

The Fischer-Tropsch reactor can reform the syngas

into liquid fuels for automotive or chemical use.

This project will be the first demonstration of an

end-to-end CO2 abatement system that produces

useful products.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Brian Frankie

Pioneer Astronautics

445 Union Blvd. #125

Lakewood , CO 80228

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Robert Zubrin

Pioneer Astronautics

445 Union Blvd. #125

Lakewood , CO 80228

Form 9.B Project Summary

Chron:

971492

Proposal Number:

10.01-3930

Project Title:

Atmospheric Water Vapor Adsorption

for Mars In Situ Resource Utilization

Technical Abstract (Limit 200 words)

The innovation addressed in this proposal is a

method for extracting water vapor from the

atmosphere of Mars in an efficient, lightweight, and

reliable manner. Through the use of molecular

sieve technology, the Water Vapor Ad-sorption

Reactor (WAVAR) would provide a dependable

source of water to future exploration missions from

sources indigenous to the red planet. This water can

be used as feedstock for propellant production, for

direct human con-sumption, or as the basis for a

multitude of industrial, agricultural and biological

processes. Using locally available materials at the

site of an interplanetary misson is known as in situ

resource utilization (ISRU). Missions employing

ISRU techniques can attain dramatic cost savings,

while improving mission robustness, by reducing the

amount of raw materials that have to be transported

from Earth. The most important of these materials

is water. The WAVAR would meet this need,

providing a crucial technology for future missions.

The effort described in this pro-posal would

positively impact NASA¹s Mars Surveyor,

Planetary Science and Human Exploration and

Development of Space (HEDS) programs by

enabling the development and commercialization of

low cost, high performance WAVAR technology.

Potential Commercial Applications (Limit 200 words)

The innovation described in this proposal would

provide a reliable, low cost and high performance

method for extracting water from the Martian

atmosphere. Incorporating the Water Vapor

Adsorption Reactor (WAVAR) into future Mars

exploration missions would provide substantial

increases in crew safety and operational flexibility

while reducing cost, risk, and Earth- and

Mars-launch mass. By providing self-sufficiency

and reducing risk, the WAVAR would enable

commercial and industrial development of Mars,

thereby expanding human presence in the solar

sys-tem. Follow-on commercial oportunities exist in

a wide variety of markets where separation of fluid

species is required.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Mr. John Williams

Adroit Systems, Inc.

411 108th St. NE Ste. 1080

Bellevue , WA 98004

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Thomas R.A. Bussing

Adroit Systems, Inc.

411 108th St. NE Ste. 1080

Bellevue , WA 98004

Form 9.B Project Summary

Chron:

970335

Proposal Number:

10.02-7115

Project Title:

Microsensor Arrays for Monitoring of

Multiple Chemical Species

Technical Abstract (Limit 200 words)

Manned space mission require a variety of

environmental monitoring and biomedical activities

to protect crew health and to counter the effects of

space on human physiology. To successfully

accomplish this, there is a critical need for

microsensor devices capable of multifunctional

monitoring of various chemical species found in air.

This program seeks to focus on demonstrating a

technology that can enable such devices. The

approach proposed is based on proprietary

nano-precision engineering of sensor arrays.

During Phase I, NRC will demonstrate the

proof-of-concept. Phase II will optimize, build

prototypes, and field test the technology. Phase III

will commercialize the technology.

Potential Commercial Applications (Limit 200 words)

The technology will help detect, identify, and

quantify multiple chemical species in real time. For

NASA, this would help ensure crew safety and

extend long-term operations. Spin off applications

include clinical diagnosis for lower cost health care,

chemical and petrochemical process control,

pharmaceutical discovery, safe transport of

chemicals and significantly improved home and

office HVAC systems.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Tapesh Yadav, Ph.D.

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Neil Lupton

Nanomaterials Research Corporation

2849 East Elvira Rd

Tucson , AZ 85706-7126

Form 9.B Project Summary

Chron:

970161

Proposal

Number:

10.02-7270

Project Title:

Novel Electrochemical Ozone Generator

for Disinfection of Spacecraft Water

Technical Abstract (Limit 200 words)

Development of an advanced electrochemical ozone

generator for evolution of ozone directly into water

streams to be treated is proposed for water

reclamation applications on long-duration space

missions. The primary innovation is development of

a biologically inert anode catalyst to replace the

lead dioxide presently used, eliminating the

possibility of lead contamination. The

electrochemical ozone generator will be compact,

lightweight, easy to use and maintain. The water to

be treated is the only reactant, eliminating the need

for expendable biocides. Possible applications of

the ozone generator include: wastewater treatment,

production and maintenance of potable water, and

sterilization of potable-water systems.

The objectives of the proposed program are to

develop the anode catalyst and anode electrode

structure and demonstrate performance and

stability of this structure. The program will

culminate in demonstration of a breadboard

prototype ozone generator and development of a

system design model.

Potential Commercial Applications (Limit 200 words)

Ozone is a powerful disinfectant, with wide potential

applications for water treatment and sterilization.

Due to the compact size, low cost and ease of use of

the proposed electrochemical ozone generator,

there are a myriad of potential commercial

applications in the dental, medical, pharmaceutical

and food industries for this device. Applications

include sterilizing dental units and dialyzers and

general hospital and laboratory disinfection.

Treatment of drinking and waste waters in homes

and public and private utilities is another potential

application.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Cecelia Cropley

GINER, INC.

14 Spring Street

Waltham , MA 02154-4497

Form 9.B Project Summary

Chron:

970468

Proposal

Number:

10.03-1358

Project Title:

A Functional Visual Assessment Test For

Human Health Maintenance And

Countermeasures

Technical Abstract (Limit 200 words)

We will develop a portable computer-based test of

functional visual acuity that can be applied to

conditions involving whole-body perturbation that

are common in aerospace operations and in the

activities of daily living. Our visual-acuity test is

innovative in that (a) it can be applied while the

observer is walking, in a vehicle cockpit, or in

standardized optometric conditions, (b) it is

commensurate with international standards for

optometric procedures and diagnostic information,

and (c) it allows for differentiation between

ophthalmic and neuromuscular causes of impaired

acuity. These unique characteristics of our

innovative test are relevant to Topic 10.03,

On-Board Human Health Maintenance and

Countermeasures, because they can enhance

"understanding of the effects of microgravity and

other components of the space environment on the

physiological systems of the body" by allowing for

standardizable quantification of visual acuity and

coordination of the associated neuromuscular

systems through "novel software methods for

documentation, storage, retrieval, analysis and

diagnosis of crew health." Moreover, by enhancing

diagnostic differentiation and generality, our

innovative test can support the development of

"countermeasures against deleterious changes in

body systems in flight or upon return to the ground

[including]... post-flight reduction in neuromuscular

coordination."

Potential Commercial Applications (Limit 200 words)

Aerospace medicine.

Research & design of displays & controls for

vehicle cockpits.

Clinical medicine: diagnosis, rehabilitation

evaluation.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Gary E. Riccio

Nascent Technologies Limited

3171 Research Boulevard, Suite 171

Dayton , OH 45420-4014

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Gary E. Riccio

Nascent Technologies Limited

3171 Research Boulevard, Suite 171

Dayton , OH 45420-4014

Form 9.B Project Summary

Chron:

970265

Proposal Number:

10.03-5075

Project Title:

Novel RF Coils for MRI/MRS of the

Human Bone and Muscle

Technical Abstract (Limit 200 words)

Magnetic resonance imaging (MRI) is an elegant

modality for performing volumetric measurements

and obtaining metabolic information of the human

bone and muscle, in-vivo, non-invasively without the

use of ionizing radiation. A major aim of this project

is to provide novel RF coil hardware to support the

on-going pre/post space flight protocols and bed

rest studies performed on astronauts/cosmonauts at

the Baylor College of Medicine. The proposed

SBIR research is relevant to NASA's subtopic

10.03 On-Board Human Health Maintenance and

Countermeasures. In Phase I, a homogeneous, RF

coil volume array with a further 30-40%

improvement in S/N for high-resolution calcaneus

imaging will be developed at 1.5T. Phantom

measurements (S/N, uniformity) will be made and

compared to existing coils. Phase II will involve

extensive volunteer evaluations to assess

trabecular bone quality. We will extend our RF coil

technology and build a custom detector array for

high-resolution imaging of the neck muscles.

Furthermore, we intend to build a hybrid

quadrature, dual-tuned 31P-1H volume resonator

for 1H anatomical imaging as well as obtaining 31P

metabolite information from the entire human calf

muscle. All three coils will be extensively tested

with phantoms and volunteers first.

Potential Commercial Applications (Limit 200 words)

Clinical applications include non-ionizing,

non-invasive and a cost effective approach toward

diagnosis of arthritis and musculoskeletal diseases

of the knee, wrist and hand, foot and ankle when

compared to the invasive arthrography. The

proposed R&D will provide improvements to MR

phased array and dual-tuned RF coil technologies

including sequence and technique optimizations. If

clinical value is demonstrated, MR systems based

on this technology will find wide spread applications

in MR imaging and spectroscopy of the joints and

the human musculoskeletal system.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Mr. Ravi Srinivasan

Advanced Imaging Research, Inc.

540 East 105th Street, Suite 350

Cleveland , OH 44108

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mr. Ravi Srinivasan

Advanced Imaging Research, Inc.

540 East 105th Street, Suite 350

Cleveland , OH 44108

Form 9.B Project Summary

Chron:

970933

Proposal Number:

10.04-0236

Project Title:

Blackbody Photoreactor for

Space-Based Water Treatment

Technical Abstract (Limit 200 words)

While many forms of chemical waste are easy to

destroy via simple oxidation processes, others are

not. These include propellants, explosives, dyes,

halocarbons, and wastes tainted with heavy metals.

However, these materials, as well as simple

organics, are amenable to treatment via advanced

oxidation processes (AOPs) such as ultraviolet

(UV)/peroxide treatment, UV/ozone treatment, the

use of Fenton's reagent, and titanium dioxide

(TiO2)-assisted photocatalysis. While all AOPs

operate by generating OH_ radicals, TiO2-assisted

photocatalysis has the greatest promise for low-cost

operation due to the fact that it requires only air (or

water) and sunlight. The primary drawback to

TiO2-assisted photocatalysis reactors is the low

solar absorptivity of TiO2. Only a small fraction

(1-2%) of the visible light is absorbed, while the

rest is transmitted and lost. Such low absorptivities

yield low oxidation rates and are an

impediment to the commercialization of this

technology. In this Phase I project, Ultramet

proposes to design and fabricate a novel reactor

that will yield order of magnitude increases in the

removal rate. This will be achieved by fabricating a

blackbody cavity of the catalyst material, which will

result in virtually all of the incident radiation being

absorbed by the catalyst. A second innovation will

be the use of a TiO2 aerofoam as the catalyst. This

high surface area, high absorptivity, low pressure

drop material can be used as a fixed catalyst bed,

eliminating the need to separate the catalyst from

the effluent stream. Techniques such as doping the

TiO2 with other catalytic oxides or noble metal

clusters and using charge injection from organic

dyes will also be investigated.

Potential Commercial Applications (Limit 200 words)

The applications for an efficient photocatalyzed

reactor in both the government and private sectors

are numerous. With over 65 metric tons of

hazardous solvent waste and 60 metric tons of other

chemical wastes being generated by the chemical

process industry each year, the demand for a

cost-effective, high-efficiency treatment process is

immense. Military stockpiles are also in need of

remediation. And although the U.S. is the leading

producer of waste chemicals, other industrial

countries are also in need of a low-cost remediation

technology.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Arthur J. Fortini, Ph.D.

Ultramet

12173 Montague Street

Pacoima , CA 91331

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Craig N. Ward

Ultramet

12173 Montague Street

Pacoima , CA 91331

Form 9.B Project Summary

Chron:

970058

Proposal

Number:

10.04-7770A

Project Title:

On Demand Electrochemical Production

of Reagents to Minimize Resupply of

Expendables.

Technical Abstract (Limit 200 words)

Electrochemical methods are proposed for the

on-demand generation of strong

acids (HCl, H2SO4), strong bases (KOH, NaOH),

and oxidants (KHSO5, Na2S2O8). Acids,

bases, and oxidants are required for the operation

of a variety of present and future

components of regenerative life support systems.

They will also be needed for use in

analytical instruments, and as reagents in

experiments and commercial processes which

exploit the unique aspects of the microgravity

environment. Because these chemicals are

highly reactive, their storage and use aboard

spacecraft must satisfy very stringent

containment requirements. Their use also imposes

a significant resupply burden.

UMPQUA Research Company proposes the

development of a microgravity and

hypogravity compatible process for the production

of acids and bases from the

corresponding salt by electrodialytic water splitting.

Strong oxidants such as oxone and

persulfate will be produced by the electro-oxidation

of sulfuric acid. The ability to

produce these chemicals, when needed, offers many

advantages with regard to

operational flexibility, storage, containment, safety,

and resupply logistics, and will be

particularly beneficial in support of future long

duration manned missions in space.

Potential Commercial Applications (Limit 200 words)

The primary commercial application for the

on-demand electrochemical

generation of acids, bases, and oxidants will be as

Flight Hardware purchased by NASA,

or by an aerospace contracting firm on behalf of

NASA, to provide enhanced capability

with minimum resupply requirements for component

processes in future advanced life

support (ALS) systems needed for long duration

manned missions in space, such as a

space station retrofit, a permanently inhabited

Lunar base, or a manned mission to Mars.

The technology may also be employed in support of

earth based systems which are used

in remote locations such as Antarctica, where

resupply of chemicals is difficult and

costly.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

James R. Akse, Ph.D.

Umpqua Research Company

P.O. Box 609 - 125 Volunteer Way

Myrtle Creek , OR 97457

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

John S. Aker

Umpqua Research Company

P.O. Box 609 - 125 Volunteer Way

Myrtle Creek , OR 97457

Form 9.B Project Summary

Chron:

971577

Proposal Number:

10.04-8614

Project Title:

Low Temperature Lightoff, Lightweight

Catalytic Oxidation Reactor for Life

Support Systems

Technical Abstract (Limit 200 words)

A new class of catalyst technology for catalytic

oxidation is developed based on ultra-short channel

metal monolith(USCMM)substrate with a high

specific surface area (SSA) slip coat. The

technology provides smaller, lighter, more energy

efficient catalytic systems than are possible with

conventional monolith or pellet substrates.

Catalytic oxidation is highly effective in destroying

a wide range of contaminants in applications

ranging from industrial sources such as solvents to

trace airborne contaminants in life support systems.

The technology builds upon Precision Combustion's

previous success in developing an electrically

heated catalytic oxidizer for NASA's Trace

Contaminant Control Subassembly (TCCS) that was

based on a low SSA USCMM catalyst system. This

new catalyst technology combines the excellent

transport properties of the USCMM (low thermal

inertia and excellent mass transfer) with the lower

temperature activity of the high SSA support.

Potential Commercial Applications (Limit 200 words)

The technology can provide lower overall launch

and resupply costs and lower power requirements

when integrated into NASA life support systems for

the Trace Contaminant Control

Subassembly(TCCS), catalytic oxidation for waste

water reclamation, or treatment of exhaust gas

from solids waste incineration. There are

substantial spinoff commercial opportunities for this

technology, primarily for automotive catalytic

converters, air cleaners, clean burners, and

chemical reactors.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Robert Carter

Precision Combustion, Inc.

25 Science Park, MS 24

New Haven , CT 06511-1968

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Paul Donahe

Precision Combustion, Inc.

25 Science Park, MS 24

New Haven , CT 06511-1968

Form 9.B Project Summary

Chron:

971117

Proposal

Number:

10.05-2100

Project Title:

ICAT Enhanced Multimedia-Based

Training

Technical Abstract (Limit 200 words)

LinCom Corporation is proposing an innovative

approach to improving training for ground support

and mission operation personnel by embedding the

capabilities of NASA's award winning Intelligent

Computer Aided Training (ICAT) software into

mainstream commercial Computer Based Training

(CBT) tools. NASA has invested over ten years of

research and development into ICAT technology.

ICAT reflects state-of-the-art technology for

developing high-fidelity interactive training

systems. However, this technology has primarily

been confined to federal laboratories, universities,

and a few corporations. Traditional Computer

Based Training (CBT) software is now beginning to

require extensive high-end features beyond the

standard integration of sound, video, and animation.

Current corporate expectations include advanced

student interactions, sophisticated user tracking,

and extensive navigation features similar to those

already available in ICAT. The innovation of

integrating ICAT, whose focus is on "learning by

doing", with CBT would be a natural fit and would

satisfy this demand. Since the use of

commercial-off-the-shelf CBT authoring tools for

training in mission operations at NASA is an

established and growing practice, intelligent

tutoring that would encompass student performance

throughout a CBT training module would

dramatically increase the power of the training

Potential Commercial Applications (Limit 200 words)

Anyone who develops courseware using the most

popular CBT authoring systems - such as

Authorware, Toolbook, Quest, IconAuthor, and

Director - is a potential customer for the ICAT

CBT Plug-In. This includes courseware developers

from industry, government, education or in CBT

consulting. These developers will typically maintain

a portfolio of products that expand the functionality

of their work. The ICAT CBT Plug-In will be

designed for seamless integration into any delivery

method, whether via CD-ROM, Internet, LAN or

DVD, thereby assuring the broadest possible

commercial application. A follow-on market for

upgrades, technical support and custom

development will also be created.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Ms. Grace Hua

LinCom Corporation

1020 Bay Area Blvd., Suite#200

Houston , Tx 77058-2628

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Bob Culpepper

LinCom Corporation

1020 Bay Area Blvd., Suite #200

Houston , Tx 77058-2628

Form 9.B Project Summary

Chron:

970227

Proposal Number:

10.05-7766

Project Title:

Space Shuttle Frozen Dessert System

Technical Abstract (Limit 200 words)

The Joseph Company (TJC) proposes to develop

The Space Shuttle Frozen Dessert System, which

will address the requirements of Subtopic 10.05,

Space Crew Performance Enhancements and

Accommodations. It will provide cold and frozen

desserts for the Space Shuttle crew using a simple,

lightweight system. This is a novel food system for

microgravity, which allows the crew to make ice

cream and other desserts in the Shuttle during the

mission by evaporating water based refrigerant at

vacuum pressures in a small Heat Exchange Unit

(HEU). The cross tie connection to the potable

water overboard dump nozzle provides unlimited,

ultra low pressure vacuum for the HEU to dump the

evaporated water vapor overboard. The system will

require no additional power, be lightweight and

compact.

Potential Commercial Applications (Limit 200 words)

There is tremendous potential and need for civilian

consumers to purchase a shelf stable portable

instant ice cream novelty for children's lunches and

outdoor recreational food supplies. Currenly,

Baskin Robbins is entertaining a possible joint

venture with TJC to develop and market the

commercial version of the results from this SBIR.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Jeffrey W. Chen

The Joseph Company

28202 Cabot Road, Suite 310

Laguna Niguel , CA 92677

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Mitchell J. Joseph

The Joseph Company

28202 Cabot Road, Suite 310

Laguna Niguel , CA 92677

Form 9.B Project Summary

Chron:

970475

Proposal

Number:

10.05-8100

Project Title:

Intranet/Internet Accessible Inventory

Management System (IA-IMS) for

On-Board and Ground Based Mission

Operations

Technical Abstract (Limit 200 words)

APTEK proposes an innovative approach for

accessing real-time spacecraft and ground

operations inventory data using Java and the

Intranet/Internet. Our approach uses

object-oriented Internet technology to enable

astronauts, ground support and mission training

personnel to efficiently and accurately manage their

inventory. This is innovative in that for the first

time, inventory data will be accessible from any

computer connected to the Internet that is capable

of running a Java-aware Web browser. With

extensive security measures in place, astronauts,

ground support, and other authorized personnel

from around the world can have real-time access to

the on-board Inventory Management System (IMS)

for scientific and/or educational purposes. In

addition, hard to represent storage configurations

will be more accurately modeled using the powerful

graphics available through Internet technology. The

proposed improvement to the current IMS will

increase overall crew and ground operations

performance and productivity and reduce inventory

management costs by providing the following

specific benefits to NASA: 1) Improved distribution

and reliability of data; 2) Reduced support and

maintenance costs; 3) Reduced hardware and

networking costs; 4) Reduced learning curve for

IMS operations; 5) Improved habitability of

extended space missions; 6) Increased availability

throughout NASA and to other educational and

scientific communities.

Potential Commercial Applications (Limit 200 words)

The proposed APTEK Intranet/Internet

Accessible-Inventory Management System

(IA-IMS) innovation has significant commercial

potential for both the government and the private

sectors. For the government, the IA-IMS will

provide a software system which is accessed via the

Internet whereby all participants on a project can

have instantaneous access to the identical

inventory information associated with that project.

A key feature of the innovation proposed is the

Java software capability. The Java software allows

a central data base to reside on a central computer

and the capability to rapidly download the

information of interest to individual clients. The

initial commercial application is envisioned to be for

NASA in support of the International Space Station

(ISS) project. All foreign and domestic researchers

and mission operations personnel associated with

the ISS can access the current inventory on board

the ISS. Additional commercial activities exist

whenever multiple remote operations are concerned

with a central inventory. This is a characteristic of

virtually every large corporation, particularly those

with international operations. Military logistics and

operations are another prime example where the

APTEK IA-IMS software can produce a significant

reduction in operating costs and an increase in

efficiency. Thus the potential markets for the

IA-IMS software are huge.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Carolyn M. Yeager

APTEK, Inc.

1257 Lake Plaza Drive

Colorado Springs , CO 80906

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Eugene A. Fitzgerald

APTEK, Inc.

1257 Lake Plaza Drive

Colorado Springs , CO 80906

Form 9.B Project Summary

Chron:

970708

Proposal Number:

10.06-0604b

Project Title:

Inflatable Structure for Mars Trans

Hab

Technical Abstract (Limit 200 words)

The shape and strength of inflatable structural

components can be closely controlled by taking

advantage of the high specific strength and stiffness

of fibers such as Kevlar and Vectran in forming the

skin for inflatable structures. Enhanced dimensional

control during inflation has been demonstrated by

selectively controlling the type and direction of the

structurally dominant fabric fibers in all material

layers. This proposal describes the use of this

demonstrated capability to select the optimum

structural fabric material for an inflatable structural

shell, select a compatible elastomeric adhesive,

perform an investigation of winding and braiding

fabrication techniques including a finite element

structural analysis of the optional configurations,

and construction of a scale model of the Trans Hab

module using the selected fabrication techniques.

Conduct of this program will result in identifying the

optimum construction method for the inflatable

toroid used in the Mars Trans Hab concept

developed by NASA Johnson Space Center (JSC).

Potential Commercial Applications (Limit 200 words)

The fabrication materials and techniques to be

identified/developed during this project are suitable

for other large inflatable structures needed for

space applications, including: expanding the space

station habitat and storage modules to

accommodate more crew members and a greater

number of experimental facilities; and potential

applications for inflatable structure concepts

suitable for both Lunar and Mars habitats.

This methodology for building inflatable structures

also has potential terrestrial uses. Large collapsible

storage vessels can be constructed using these

techniques that would be suitable for moderate

pressure storage and transport of gases and liquids

with temperatures ranging from cryogenic to 200

°F.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Glen J. Brown

Vertigo, Inc.

458 Thayer Road

Santa Cruz , CA 95060

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Glen J. Brown

Vertigo, Inc.

29885 2nd St. Unit N

Lake Elsinore , CA 92532

Form 9.B Project Summary

Chron:

970723

Proposal Number:

10.07-4239

Project Title:

Lightweight, Low Thermal Conductivity

Cryogenic Penetrations

Technical Abstract (Limit 200 words)

Foster-Miller proposes to refine and utilize its

proprietary and patented liquid crytalline prolyemrs

(LCP) processing technology to produce low weight

and low thermal conductivity cryogen tank

penetrations such as feed lines, vent lines and

instrumentation feed throughs. Our biaxially

oriented LCPs are ideal for cryogenic applications

because of their proven compatibility with LOX,

retention of ductility and strength at cryogenic

temperatures, low permeability to gases, far lower

density than metals or composites, and

exceptionally low thermal conductivity. Our

proposed approach is expected to reduce cryogen

tnak thermal induced losses by 17-25%. This will

result in significant reductions in the cryotank

weight or major increases in strorage capacity if the

original tank weight is maintained. Such savings can

extend mission life or increase payload capacity.

Potential savings are expected to range from

$275,000 to $2,000,000 per launch/mission.

In Phase I Foster-Miller will demonstrate the

feasibility of our minimal heat transfer LCP

cryogenic tank penetrations. We will produce

tube/pipe at varying biaxial orientations and wall

thicknesses, and establish their mechanical,

thermomechanical (CTE) and thermal conductivity

properties. A cost/benefit analysis will then be used

to establish the technical and economic viability of

our LCP cryogenic tank penetration components.

Potential Commercial Applications (Limit 200 words)

Commercial applications include high strength

tubes for aerospace and astrospace structures

where zero axial CTE can provide major benefits,

accurate gauge medical tubing for endoscopic

instruments and tools, and high voltage electrical

tubing and conduit. In addition a larger scale

version of this technology may be readily applied to

advanced-high performance solid rocket motors.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Leslie S. Rubin

Foster-Miller, Inc.

350 Second Avenue

Waltham , MA

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Adi R. Guzdar

Foster-Miller, Inc.

350 Second Avenue

Waltham , MA 02154-1196

Form 9.B Project Summary

Chron:

970345

Proposal Number:

10.08-0851A

Project Title:

Heat-Driven Pyroelectric Pump

Technical Abstract (Limit 200 words)

Pumps with moving parts are prone to failure and

are often subject to gravitational limitations.

Proposed is demonstration (Phase I) and

development (Phase II) of a novel heat-activated

pump using the pyroelectric effect. With materials

whose dielectric constant is a strong function of

temperature, this effect can be used for heat

engines. Direct pumping of liquids is also possible,

by heating them within the electric field. Water is

an ideal fluid for this application because the

dielectric constant changes rapidly with

temperature. Recuperation of sensible heat yields

an efficient pump with no moving parts, and staging

can be used to achieve a large pressure head. The

electric field is not consumed, so electric power

consumption for field generation is limited to

leakage losses. Heat in any form can drive the

pump. The lack of moving parts (motor,

transmission, etc.) will not only increase reliability

but will also reduce weight, especially for small

capacity pumps. The heat-driven pyroelectric pump

is proposed as an alternative to

"piezoelectric/magnetoresrictive driven pumps with

high reliability" suggested under subtopic 10.08.

Potential Commercial Applications (Limit 200 words)

If proven, this innovative pump would find use in

many applications where its special features

(heat-driven, no moving parts, maintenance free)

are desirable. Specific examples include: (1)

solution pumps on sorption refrigeration systems,

where heat is available and electric pumps add

considerably to operating costs, (2) very small flows

where motors and mechanical pumps are very

inefficient and reliability is a problem, and (3)

pumps for solar heating systems, in which case the

pump would be heat driven with pumping rate

increasing as more heat was available.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Lance Kirol

Rocky Research

1598 Foothill Dr.

Boulder City , NV 89005

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Rocky Research

1598 Foothill Dr.

Boulder City , NV 89005

Form 9.B Project Summary

Chron:

971449

Proposal Number:

10.08-7223

Project Title:

Low Energy Plasmas Applied to

Transparent Organic Optoelectronic

Devices

Technical Abstract (Limit 200 words)

The anticipated results of the proposed research

could lead to basic improvements in the

performance of organic high-emitting devices

(OLEDs) poised to enter the electronic display

market. Specific objectives: 1) Confirm the concept

of low energy plasma deposition of thermally

evaporated organic precursors to form sandwich

layers. 2) Demonstrate a practical deposition

process which excludes air. 3) Verify that such

layers can be electrically excited to controlled light

emission. 4) Confirm the luminosity, transparency,

and flexibility of prototype OLEDs. 5) Demonstrate

extended life and reduced power drain after

prolonged flexing of hermetically sealed prototypes.

6) Characterize the layers' surface structure and

electroluminescent performance. 7) Relate results

to a Phase II development of a prototype to meet

NASA's requirements. 8) Analyze the Phase III

commercial potential.

Potential Commercial Applications (Limit 200 words)

Portable displays (radio receivers, cellular

telephones, calculators). Automotive instrument

and safety displays. Flat panel displays. Flexible

optoelectronic displays. Electroluminescent and

photosensitive polymers. Heads-up displays for

windshields, helmets, visors, and mirrors.

Information readout: panel meters, test and audio

equipment, and home appliances.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Hiroshi Nomura, Ph.D.

NeoMecs Inc.

4832 Park Glen Road

St. Louis Park , MN 55416

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Hiroshi Nomura Ph.D.

NeoMecs Inc.

4832 Park Glen Road

St. Louis Park , MN 55416

Form 9.B Project Summary

Chron:

970243

Proposal Number:

10.09-0562

Project Title:

Advanced display for immersive

telepresence system

Technical Abstract (Limit 200 words)

Flogiston Corporation proposes to design and

develop an advanced display system for immersive

telepresence applications which provides full

spherical field of view, using its proprietary Bubble

Dome technology, combined with a Head Mounted

Display (HMD) to provide high resolution stereo

vision in the foveal area. Astronauts will use the

compact display system on board the Space Station

to interact with and control robotic systems such as

the Robonaut, perform inspections of external

systems using autonomous EVA robotic cameras,

and view immersive virtual and telepresenced

environments for training and communications.

Existing robots retain their current head tracked

stereoscopic cameras, while adding fixed fisheye

view cameras. The fisheye image is back projected

on to the exterior of the small dome, called a

telesphere, to provide a general field of view

without lag that engages peripheral vision, while the

stereoscopic image is displayed on the HMD for

detailed inspection. This enables the astronaut to

look around freely inside the telesphere, providing

a sense of presence that HMDs alone cannot

convey. This display significantly increases the

capabilities of humans to control robotic systems

and put their awareness at the robot's location.

Potential Commercial Applications (Limit 200 words)

The advanced display has many applications in

commercial telepresence and immersive

cyberspace applications. Flogiston is already

marketing the Flostation with its basic dome for

commercial use in the entertainment, research,

education and medical fields. Any improvements to

the display can readily be assimilated into the

Flostation and improve the image quality. The

addition of a high resolution HMD to compliment

the dome has practical applications for surgery

training, telepresence surgery, control of remotely

piloted aircraft, submersible vehicles, hazardous

area robots, and in the entertainment field. The

complete telesphere also has applications for

remote viewing of sites for surveillance and

security.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Brian Park

Flogiston Corporation

16921 Crystal Cave Drive

Austin , TX 78737

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Brian Park

Flogiston Corporation

16921 Crystal Cave Drive

Austin , TX 78737

Form 9.B Project Summary

Chron:

970859

Proposal Number:

10.10-2020

Project Title:

Carbon Nanotubes for High Capacity

Fuel Storage Systems

Technical Abstract (Limit 200 words)

One of the most intriguing applications of

nanotubes is in use as an absorptive/adsorptive

material for hydrogen storage, where the high

surface area dn graphitic naure of carbon

nanotubes can be used to significantly reduce the

pressure and temperature of containment, as well

as potentially dramatically increase the storage

capacity of a storage vessel with a given volume.

The observation that carbon nanotubes can absorb

and adsorb large amounts of hydrogen offers the

prospect that carbon nanotubes can be used for

high capacity, low volume fuel storage vessels for

improved range and/or reduction of tank volume.

The availability of low-cost carbon nanotubes based

on the high volume production process of nanotubes

will enable cost-effective near-term exploitation of

this physical phenomenon. The objectives of the

Phase I work are to demonstrate the feasibility of

using carbon nanotubes for hight capacity hydrogen

storage, and to determine relationships between

fiber size and morphology to hydrogen storage

capacity and thermal stability of the system.

Potential Commercial Applications (Limit 200 words)

Potential aerospace uses of this technology include

hydrogen storage for propulsion or power (fuel

cells). Compact storage of hydrogen could be

enabling technology for the transportation industry.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

David J. Burton

Applied Sciences, Inc.

141 W. Xenia Ave. PO Box 579

Cedarville , OH 45314-0579

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Max L. Lake

Applied Sciences, Inc.

141 W. Xenia Ave. PO Box 579

Cedarville , OH 45314-0579

Form 9.B Project Summary

Chron:

971375

Proposal Number:

10.10-2370

Project Title:

Applications of Single-Walled Carbon

Nanotubes

Technical Abstract (Limit 200 words)

The overall goal of this program is to develop a new

class of nanocomposite electronic materials from

single-walled carbon nanotubes. The properties of

carbon nanotubes offer a unique solution for

fabrication of practical electronic materials.

However, development of practical carbon

nanotube devices has been limited, and still remains

at the laboratory level, despite the substantial

amount of time and money that has been devoted to

studying their properties.

Specifically, in Phase I, we will demonstrate the

feasibility of our approach by preparing useful

materials that utilize single-walled carbon

nanotubes, fabricating prototype electrodes, and

then testing the them for the following electronic

properties 1) specific capacitance (farads/g), 2)

specific energy (Wh/kg), 3) energy density (Wh/L),

4) cycle lifetime, and 5) ease of manufacturing and

cost.

Based on successful proof of feasibility in Phase I,

we will pursue a Phase II program where emphasis

will be placed on optimizing the most promising

candidates identified in Phase I. Phase II will

involve the design and development of prototype

devices and demonstrating their utility.

Potential Commercial Applications (Limit 200 words)

The projected market for energy storage devices

such as ultracapacitorsis expected to exceed

exceeds 1.3 billion dollars by the year 2000. This

represents a substantial economic opportunity for

development of such devices. Utilization of carbon

nanotube technology in this arena will require

improvements in technical performance and cost

specifications in order for a practical device to

reach the marketplace.

The electronic devices we propose to develop in

this program will have widespread application in the

automotive industry, consumer electronics, energy

management in computers for start-up and memory

back-up, cellular phones and emerging

technologies.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Dr. Thomas A. Reynolds

ReyTech

63140 Britta St., Suite C-100

Bend , OR 97701

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Dr. Thomas A. Reynolds

ReyTech, Inc.

63140 Britta St., Suite C-100

Bend , OR 97701

Form 9.B Project Summary

Chron:

970652

Proposal Number:

11.01-4400A

Project Title:

VOC-Compliant Primerless Silicone

Coatings for Corrosion Control

Technical Abstract (Limit 200 words)

A VOC-compliant anticorrosion coating is proposed

for maintaining structural metals such as aluminum

and steel in corrosive field environments. The

proposed research explores the feasibililty of using

an aqueous dispersion of silicone resins stabilized

with novel polymeric surfactants and pigmented

with non-toxic anticorrosive additives to yield

coatings with excellent inherent adhesion to metals

and high corrosion inhibiting ability. The proposed

anticorrosion formulations, although waterborne,

would possess the ability to displace absorbed

water from the surfaces of poorly treated metallic

substrates and adhere strongly without the need for

pre-coat priming. The substitution of multi-function

polymeric surfactants for conventional surfactants

should significantly reduce the emissivity of the

resulting coatings. The interaction of the proposed

coating components and hydrated metal surfaces

will be computer simulated to optimize the unprimed

coating-substrate adhesion and barrier properties.

The VOC-compliant coatings would be tested

against conventional solventborne silicone coatings

for adhesion and corrosion inhibition. The ability to

form inherently adherent, durable barrier coatings

over poorly treated structural metal alloys without

the need for volatile organic solvents would

represent a signficant advancement in corrosion

engineering and aerospace maintenance

technology.

Potential Commercial Applications (Limit 200 words)

The benefits of a waterborne coating for improving

the corrosion resistance of structural metals include

reduced workplace health hazards, lower disposal

costs, greater system reliability, and improved

mission readiness. Potential commercial

applications lie in the manufacture and maintenance

of military, industrial and aerospace vehicles and

equipment.

Name and Address of Principal Investigator (Name,

Organization Name, Mail Address, City/State/Zip)

Francis L. Keohan

Cape Cod Research, Inc.

19 Research Road

East Falmouth , MA 02536

Name and Address of Offeror (Firm Name, Mail Address,

City/State/Zip)

Katherine D. Finnegan

Cape Cod Research, Inc.

19 Research Road

East Falmouth , MA 02536

Form 9.B Project Summary

Chron:

971437

Proposal Number:

11.01-7819A

Project Title:

Self-Priming Silicone Coating

Technical Abstract (Limit 200 words)

Silicone coatings are exceptionally hydrophobic and

stable to most common chemical and weathering

processes, making them excellent anti-corrosion

coatings for materials subjected to extreme

environments. Unfortunately the adhesion of most

silicone coatings to metallic substrates is poor

without the application of a primer coat. To

maximize the adhesion and corrosion protection

afforded by silicone coatings, TDA Research Inc.

(TDA) will develop polymeric additives which will

act as internal priming agents for a wide array of

commercial silicone coatings. These additives are

expected to be effective adhesion promoters even

at concentrations below 1%. Self-priming silicone

coating formulations will save the time and money

associated with application of a separate coating of

primer. Additional potential benefits include the

reduction of volatile organic chemical (VOC)

emissions during the coating process and improved