Hannah Böhrk , Tina Stäbler , Christian Dittert , Isil Sakraker , Daniel Prokein

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018–1098

Thermal protection of flight vehicles in hypersonic flight is extremely challenging due to the severe aerodynamic heating of external structures. Slender geometries such as a sharp leading edge of the forebody or the wing of low drag vehicles are especially affected by high heat loads. With respect to reusability and availability over the designed life time it is therefore necessary to employ active cooling methods such as transpiration cooling. In this context, porous ceramic matrix composites (CMC) in combination with transpiration cooling become interesting and have recently been investigated with increasing efforts. Transpiration cooling as an active cooling technique is based on two mechanisms: First, the exchange of energy while the coolant gas is flowing through the hot porous material and second, the injection of cool fluid into the boundary layer which decreases the effective heat load. Other aerospace solutions incorporate passive cooling with ablators. The involved physics for both processes are complex. This is especially true for materials such as the ceramic matrix composites (CMC) and recessing ablators developed by DLR Stuttgart which, on the other hand, exhibit promising properties for high-temperature aerospace applications.

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In Categories: HiSST 2018, Thermal and Energy Management Systems, Thermal Protection Systems, Thermal Protection Systems
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