The Toughened Uni-piece Fibrous Reinforced Oxidation-Resistant Composite (TUFROC) allows for much more affordable and sustainable operations involving Space Launch Services and other systems that utilize Earth re-entry vehicles. TUFROC has an exposed surface design and appropriate materials combination that will allow a space vehicle to survive both the mechanical stresses during launch and the extreme heating and stress of re-entry. It provides a thermal protection tile attachment system that is suitable for not only spacecraft applications, but also could be used where there are extreme heating environments [up to 3100 °F for 5 to 10 minutes and 3600 °F, and possibly higher, for very short time intervals (one-minute or less)].

TUFROC includes an exposed surface cap with a specially formulated coating, and an insulator base adjacent to the cap with another specially formulated coating. The cap and base are integrated together using a direct mechanical attachment of one or more pins made from the insulator material that extends from the cap through the insulator base to tie the cap and base together through ceramic bonding and mechanical attachment. The cap and insulator base have corresponding depressions and projections that mate and allow for differences in thermal expansion of the cap and base. The cap includes a high-temperature, low-density, carbonaceous, fibrous material whose surface is optionally treated with a High Efficiency Tantalum-based Ceramic Composite (HETC) formulation. The insulator base and pin(s) contain similar silica-based materials.

The mechanical design is arranged so that thermal expansion differences in the component materials (e.g., cap and insulator base) are easily tolerated. The technology is applicable to both sharp and blunt leading edge vehicles. This extends the possible application of fibrous insulation to the wing leading edge, fuselage, and/or nose cap on a hypersonic vehicle. The lightweight system comprises a treated carbonaceous cap composed of Refractory Oxidation-resistant Ceramic Carbon Insulation (ROCCI), which provides dimensional stability to the outer mold line, while the fibrous silica-base material provides maximum thermal insulation for the vehicle structure. The composite has graded surface treatments applied by impregnation to both the cap and base. These treatments enable it to survive in an aero-convectively heated environment of high-speed planetary entry. The exact cap and base materials are chosen in combination with modified surface treatments and a specially formulated surface coating, taking into account the duration of exposure and expected surface temperatures for the particular application.

This work was done by Daniel Leiser and David Stewart of Ames Research Center. NASA is actively seeking licensees to commercialize this technology. Please contact Trupti Sanghani at This email address is being protected from spambots. You need JavaScript enabled to view it. or 650-604-6889 to initiate licensing discussions. Follow this link for more information: http://technology.nasa.gov/patent/TOP2-241. ARC-16466-1