NASA SBIR 2006 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 06-2 X6.03-9045
PHASE 1 CONTRACT NUMBER: NNM07AA57C
SUBTOPIC TITLE: Material Concepts for Lightweight Structure Technology Development
PROPOSAL TITLE: Lightweight High Temperature Non-Eroding Throat Materials for Propulsion Systems

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Materials Research and Design
300 E. Swedesford Road
Wayne, PA 19087 - 1858
(610) 964-6130

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Joseph Pluscauskis
pluscauskis@m-r-d.com
300 E. Swedesford Road
Wayne, PA 19087 - 1449
(610) 964-9000

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Radiation or passively cooled thrust chambers are used for a variety of chemical propulsion functions including apogee insertion, reaction control for launch vehicles, and primary propulsion for planetary spacecraft. The performance of these thrust chambers is limited by the operating temperature and thermal-chemical response of the available materials. The Phase I efforts focused on performing design and analysis services to address multiple areas related to the development of lightweight high temperature non-eroding materials for liquid propulsion combustion chambers. We showed through theoretical thermal-structural calculations that monolithic HfO2 and ZrO2 are the best performing ceramic thermal barriers for Ir/Re combustion chambers within liquid engines. In the Phase II effort, MR&D proposes to use the lessons learned from the Phase I studies to evaluate material options, optimize the design, demonstrate scale up to and fabrication of a full scale combustion chamber for the NASA 3000-5000 lb LOX/CH4 engine, and ultimately hot-fire the chamber at NASA. This will be in direct support of NASA MSFC Lunar Lander Ascent Stage engine. The Phase II tasks include: 1) Detailed thermal-structural design and analyses; 2) Addressing fabrication stresses/strains; 3) Addressing vibration stresses/strains; 4) Performing material characterization; 5) Performing any design revisions based on the material property characterization as it becomes available; 6) Fabrication of a full scale combustion chamber that reflects the best performing materials and geometry resulting from the thermal-structural design studies; 7) Performing pretest predictions and assisting with instrumentation for the hot-fire test; and 8) Performing posttest data correlation and suggesting design improvements.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The results of this lightweight high temperature non-eroding combustion chamber material study will have broad ranging applications in the telecommunication satellites, civil aerospace, governmental aerospace companies, as well as aircraft jet engine manufactures and power generation equipment manufacturing companies. Potential customers include Boeing, Lockheed Martin, General Electric Power Systems, and ATK-Launch Systems.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The advanced combustion chamber developed in this Phase II effort has a direct application for NASA within the NASA MSFC Lunar Lander Ascent Stage engine. Additionally, the technology developed here can be used for similar combustion chamber designs related to various NASA in-space applications.

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.

TECHNOLOGY TAXONOMY MAPPING
Ceramics
Chemical
Cooling
Database Development and Interfacing
High Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Metallics
Reuseable
Simulation Modeling Environment
Testing Facilities
Thermal Insulating Materials


Form Generated on 08-02-07 14:39