NASA STTR 2007 Solicitation
FORM B - PROPOSAL SUMMARY
|RESEARCH SUBTOPIC TITLE:
||Manufacturing Technologies for Human and Robotic Space Exploration
|| Low Erosion Ceramic Composite Liners for Improved Performance of Ablative Rocket Thrust Chambers
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
||Hyper-Therm High-Temperature Composites
||California St. University, Long Beach
||18411 Gothard Street, Units B&C
||1250 Bellflower Blvd.
||CA 92648 - 1208
||CA 90840 - 0004
PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
18411 Gothard Street, Units B&C
Huntington Beach, CA 92648 - 1208
Expected Technology Readiness Level (TRL) upon completion of contract:
TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Advanced liquid rocket propulsion systems must achieve longer burn times without performance degradation to allow the lowest cost per kilogram access to space. Ablative thrust chambers have an extensive heritage and are the low cost approach to fabricating rocket thrust chambers. However, composite ablative chambers suffer from erosion that typically limits
performance of the engine in terms of burn time and efficiency/performance of the combustion. In the last decade, there has
been significant interest in utilizing fiber-reinforced ceramic composites such as carbon fiber-reinforced silicon carbide (C/SiC) composites. Such composites have demonstrated a low erosion rate in bi-propellant liquid rocket thrust chambers at temperatures approaching 4000F. However insertion of these materials have been limited by complexities associated with required system redesign to accommodate a radiatively-cooled chamber, attachment methods, and addressing chamber
permeability issues. By incorporating a ceramic composite liner within an ablative thrust chamber in critical areas that are subjected to the highest temperatures, a low erosion, high performance chamber is obtained that eliminates costs and complexities that have limited the insertion of ceramic composite thrust chambers. The Phase I effort will produce a ceramic composite lined ablative thrust chamber, identify the degree of film cooling required and conduct a static hot fire test evaluation
of the material to demonstrate the perfromance benefit of a CMC liner within an ablative thrust chamber.
POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
A number of launch systems under consideration for use by NASA can benefit from the improved performance of a low cost ablative thrust chamber obtained by incorporating a CMC liner. Such applications include delivery of cargo to the International Space Station as well as the transporting of crew. The improved performance of these chambers is most suited for upper stage propulsion chambers. Other applications of interest to NASA would include lowering the cost per kilogram launch costs
for satellites and space exploration vehicles. Addtionally co-fabrication of a CMC and an ablative could have advantages for heat shield applications
POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The liner concept can have broad implications across a range of DoD rocket propulsion systems that currently use ablative thrust chambers due to the combined improvement in performance and decreased weight of the thrust chamber. The concept can also be utilized in the near term as an upgrade to existing ablative thrust chambers for an immediate performance benefit.
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
Form Generated on 09-18-07 17:52