A method of forming a thermal protection system for high speed aircraft is described. The method includes mechanically working an uncured ablator material into a first surface of a felt layer such that the ablator material penetrates a distance into a thickness of the felt layer thereby forming an region that has a mixture of felt and ablator material, adding additional uncured ablator material to the worked ablator material, and curing the combined ablator material.
HYBRID ABLATIVE THERMAL PROTECTION SYSTEMS AND ASSOCIATED METHODS
2016-11-10
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
Hybrid ablative thermal protection systems and associated methods
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