NASA SBIR 2006 Solicitation


PROPOSAL NUMBER: 06-2 X10.01-9224
SUBTOPIC TITLE: Ablative Thermal Protection System for CEV
PROPOSAL TITLE: High specific-strength C-Zr(O)C / C-ablator TPS for CEV

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
MATECH Advanced Materials
31304 Via Colinas, Suite 102
Westlake Village, CA 91362 - 4586
(818) 991-8500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
heemann Yun
31304 Via Colinas, Suite 102
Westlake Village, CA 91362 - 4586
(818) 991-8500

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
During the Phase I NASA SBIR, MATECH GSM (MG) has developed and evaluated the world's first ultra-high temperature (UHT) Zr-(O)-C ceramic fiber pre-form / organic ablative matrix composite TPS system. This Phase II NASA SBIR Proposal from MG seeks to expand this technology to the following areas: 1)Microstructural level refinements and optimization of the char- and ablator phases for more reproducible material systems 2)Scaling-up for the fabrication of a larger and more complex-shape geometry 3)TPS design data generation with extensive arc-jet testing for a full TPS Component demonstration in Phase III. In this TPS material concept, the "char" phase is UHT zirconium carbide (Zr(O)C) ceramic fiber pre-forms, which have dual functions of high compressive strength of ligaments and non-recession of fiber components after matrix ablation. MG's ablative TPS are designed to retain their shape, thereby reducing the thickness requirement and lowering the TPS total mass, crucial at high re-entry velocity. MG's new ablator slowly absorbs high levels of energy during high temperature ablation. At the completion of the Phase II-Base and Phase II-Option program, MG will have fabricated a high specific strength C-Zr(O)C / C-ablator (CZOCA) and have demonstrated one TPS component, operational at > 5000oF.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
DoD missile thrusters, Missile hot control-structure insulations, refractory-carbide fibers as a new type of insulation and CMC reinforcements for DOE, DoT, EPA, and the private transportation and filter industries

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
CEV thermal protection systems, Space transportation vehicle thermal insulation and propulsion insulation systems, Hypersonic vehicle and propulsion insulation systems

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.

Thermal Insulating Materials

Form Generated on 08-02-07 14:39