NASA SBIR 2006 Solicitation


PROPOSAL NUMBER:06 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)
This Phase I NASA SBIR Proposal seeks to demonstrate a new zero-erosion ablative thermal protection system (TPS) technology that is based upon an ultra-high temperature (UHT) ceramic fiber pre-form / organic ablative matrix composite structure. In this TPS material concept, the "char" phase is pre-engineered 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. To increase the pre-form ligament strength and stiffness, Zr(O)C fiber reinforcements will be combined with the high-modulus carbon fibers. MG's ablative TPS are designed to retain their shape in extreme environments, thereby reducing the thickness requirement and lowering the TPS total mass, which will be crucial at high re-entry velocity.
MG's new ablator slowly absorbs high levels of energy when ablated at higher temperatures. The ablative carbonaceous phase has been identified by the use of a melamine-formaldehyde and/or polyethylene polymer resin. This selection was based upon its high heat of volatilization and decomposition. At the completion of the Phase I and Phase II program, MG will have fabricated a high specific strength C-Zr(O)C / C-ablator and have demonstrated an completely integrated 5'x5' size TPS with attachment features, operational at > 6000oF.

POTENTIAL 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

POTENTIAL NON-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

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 Printed on 09-08-06 18:19