NASA SBIR 2017 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 171 A2.01-8971
SUBTOPIC TITLE: Flight Test and Measurements Technologies
PROPOSAL TITLE: Tunable Laser for High-Performance, Low-Cost Distributed Sensing Platform

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Sequent Logic LLC
3265 N 1950 E
North Logan, UT 84341 - 2063
(435) 915-4425

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr Ryan Seeley
seeleyr@sequentlogic.com
3265 N 1950 E
North Logan, UT 84341 - 2063
(435) 915-4425

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Ryan Seeley
seeleyr@sequentlogic.com
3265 N 1950 E
North Logan, UT 84341 - 2063
(435) 915-4425

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

Technology Available (TAV) Subtopics
Flight Test and Measurements Technologies is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
Yes

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
The proposed effort will establish technical feasibility of an approach to optimizing a low-cost, fast-sweeping tunable laser for distributed sensing. Multiple approaches for performance optimization will be reviewed, modeled, and simulated. Subsystem prototypes will also be fabricated and analyzed to understand subsystem hardware manufacturing and performance limitations. This Phase I effort will result in selection of an appropriate laser performance optimization approach and will yield estimates of performance, size, weight, power, and cost improvements expected from a Phase II prototype.
The resultant optimized tunable laser module would enable a distributed fiber-optic sensing platform with dramatically-improved performance and significant simultaneous improvement in platform size, weight, power, and cost compared to current commercial offerings.
The technology will considerably improve NASA's flight test measurement and in-situ monitoring capability over the current state of the art, opening up new distributed sensing possibilities for real-time, in-situ airframe/spaceframe measurements. In addition to supporting distributed static strain and temperature measurements, the technology allows for distributed fiber-optic acoustic/vibration sensing allowing for distributed modal analysis, non-destructive evaluation, and identification/characterization of transient events.
With an improved understanding of distributed airframe/spaceframe structural dynamics, the technology will lead to improved airframe and component designs. With improved, integrated real-time feedback control signal generation and structural health monitoring, future aircraft and space-flight vehicles will operate more safely, predictably, and efficiently.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed technology enables acquisition of real-time, in-flight strain and/or temperature data related to structural dynamics analysis and health monitoring of airframes and spaceframes. In addition, the technology enables feedback control signal generation, distributed NDE / modal analysis, and distributed thermal profiling. The technology can be applied to components, structures, aerodynamic surfaces, fixed and morphable flight control surfaces, and electrical propulsion system power sources.
The proposed technology has particular applicability to laboratory and in-flight testing of airframes and spaceframes. Distributed strain measurements can be used to infer distributed loading throughout a structure, and can additionally be used to infer shape of a structure. Most notably, the technology opens up possibilities for distributed modal analysis, distributed resonance mapping, and other sensing modalities. The dramatically-improved sample rate not only leads to a system impervious to vibration effects, but that can fully characterize those vibration effects. As such, the technology is particularly applicable to incredibly harsh shock/vibe environments such as the launch vehicle environment.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Non-NASA commercial applications of the technology include renewable wind energy, commercial aerospace & aviation, oil & gas, automotive, nuclear energy, and perimeter security.
In wind energy, the technology could inform real-time turbine control decisions for enhanced power generation efficiency. In addition, the subject technology could be used to measure deterioration of blades over their operational lifetime and detect adverse conditions or damage events, informing condition-based maintenance schedules.
Commercial aerospace companies would find use for the proposed technology in applications similar to those of NASA. In particular, real-time distributed thermal monitoring of critical propulsion and fuel-storage system components appears to be an excellent application for the technology.
The technology would benefit commercial aviation applications by informing condition-based maintenance schedules to reduce operational cost and improve passenger safety.
In automotive applications, the proposed technology could be used for real-time structural monitoring during road testing and/or crash testing. It could also be applied to thermal monitoring of electric vehicle battery banks.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Acoustic/Vibration
Condition Monitoring (see also Sensors)
Diagnostics/Prognostics
Interferometric (see also Analysis)
Lasers (Measuring/Sensing)
Lifetime Testing
Nondestructive Evaluation (NDE; NDT)
Optical/Photonic (see also Photonics)
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Thermal

Form Generated on 04-19-17 12:59