PURPOSE: To provide an abrader structure to be fixed to the skin of a spacecraft, wherein the weight is reduced and the heat resisting and anti-abrasion functions against pneumatic heating are held satisfactorily.
CONSTITUTION: The structure of an abrader 6 consists of a first layer abrader 1 thin and located on the outside and a second layer abrader 2 thick and situated on the inside, in which 1, 2 silica short fibers are included dispersedly in phenol resin in the prepreg. at the time of shaping of them 1, 2, and phenol micro--ballons 3 are dispersed in the second layer abrader 2, wherein the first layer abrader 1 is given a large weight and thermal conductivity and nevertheless a small amount of surface wear, while the second layer abrader 2 has a large amount of surface wear and nevertheless a small weight and thermal conductivity. Besides the functions owned by the second layer abrader 2, the first layer abrader 1 is equipped with the surface wear resisting function against pneumatic heating, while the second layer abrader 2 is equipped with a function to take a large latent heat due to among others pyrolysis and gas generation.
KOMA TETSUO
INATANI YOSHIFUMI
INATANI YOSHIFUMI
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