[nanoPost] Development of a novel thermal protection system (TPS) concept for spacecraft

Company USA

Recent work has shown that lightweight carbon-carbon (C/C) composites produced by pressure-assisted co-polymerization of carbon fibers, hydrocarbons and fullerenes have excellent mechanical properties and high thermal stability that makes them ideal for thermal protection applications.

Currently used thermal protection systems utilize epoxy for the composite matrix. Epoxy matrices are known to be unstable and consequently can decompose during reentry. Another problem with currently used TP systems is the adhesives that are used to bond the composite to the metal panels of spacecraft. A case in point is the Space Shuttle where adhesives are used to bond refractory tiles over large areas of the exterior surface. These adhesives can degrade and lead to devastating consequences.

Problems solved by the innovative design:

- The carbon-carbon composite structure consists of a three dimensional (3-D) carbon fiber grid and a carbon matrix that is capable of protecting the structural parts of spacecraft from erosion by plasmas in the range of 2000-7000°C.

- The C/C structure is anchored to the perforated metallic substrate (skin of the craft) by Z-directional carbon fibers (or strips). The metallic substrate can be cooled by a heat exchanging fluid.

- For atmospheric application oxidation resistant layers can be applied to the outer surface of the carbon-carbon composite. These optional coatings offer thermal protection for long periods and have application for aircraft and re-entry vehicles. The protective layers prevent carbon from oxidizing when subjected to high temperature in the red-white incandescent heat range at atmospheric air pressure.