NASA SBIR 2005 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER:05-II X2.01-8308
PHASE-I CONTRACT NUMBER: NNC06CA82C
SUBTOPIC TITLE:Advanced Materials
PROPOSAL TITLE:Lightweight Ultrahigh Temperature CMC-Lined C/C Combustion Chambers, Phase II

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Ultramet
12173 Montague St
Pacoima, CA 91331-2210
(818) 899-0236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Gautham   Ramachandran
gautham.ramachandran@ultramet.com
Ultramet
Pacoima, CA  91331-2210
(818) 899-0236

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
NASA and DoD are seeking high-performance, lightweight liquid rocket combustion chambers with future performance goals that cannot be achieved using state-of-the-art actively cooled metallic liners, silicided C103, or even carbon fiber-reinforced silicon carbide (C/SiC) ceramic matrix composites (CMC). Ultramet has previously developed and successfully demonstrated carbon fiber-reinforced zirconium carbide (C/ZrC) and zirconium-silicon carbide (C/Zr-Si-C) matrix CMCs for use in liquid propellant applications up to 4200oF. In Phase I, Ultramet demonstrated the feasibility of combining the light weight of C/C with the oxidation resistance of ZrC and Zr-Si-C matrix composites in a unique system composed of a C/C primary structure with an integral CMC liner. The system effectively bridges the gap in weight and performance between coated C/C and bulk CMCs. Rapid fabrication was demonstrated through an innovative variant of Ultramet's melt infiltration refractory composite processing technology. In Phase II, Ultramet will team with ATK-GASL for process optimization, component fabrication, and comprehensive testing of lightweight, high-strength, elevated temperature oxidation-resistant liquid rocket combustion chambers. The fully developed system will have strength that is comparable to that of C/C, low density comparable to that of C/SiC, and ultrahigh temperature (>4000oF) oxidation stability.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed project directly targets future launch and exploration vehicle propulsion systems as potential end-use applications. More generally, the versatility of this concept makes it relevant to a variety of hot structures exposed to oxidizing environments including combustion chambers, leading edge, thermal protection system, airframe, and other propulsion components.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed refractory composite material would be directly applicable to a wide rage of aerospace and defense applications that require low-cost material possessing, ultrahigh temperature oxidation stability, high strength, and low mass. These applications include propulsion components such as combustion chambers, rocket nozzles, hot gas generators, and hot gas valves, using both liquid and solid propellants. Defense applications include the high temperature combustion environment of advanced gun barrels, where the use of C/C is desirable if survivability issues can be solved. Non-defense related uses may include components related to energy generation in which use temperature, environmental reactivity, and economy are increasingly demanding.

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
Composites


Form Printed on 07-25-06 17:04