The thermal protection structure comprises an outer wall and an inner wall, the inner wall is arranged on the outer wall, a cooling channel is formed in the inner wall, a cooling agent is arranged in the cooling channel, a phase-change material storage cavity is formed in the inner wall, and a lattice sandwich structure is arranged in the phase-change material storage cavity. The invention relates to the field of thermal protection structure design, in particular to a component thermal protection structure of a hypersonic aircraft under high heat flux.
本发明公开了一种高超飞行器高热流密度下部件热防护结构,包括外壁和内壁,所述内壁设于外壁上,所述内壁上设有冷却通道,所述冷却通道内设有冷却剂,所述内壁上设有相变材料储存腔,所述相变材料储存腔内设有点阵夹芯结构。本发明涉及热防护结构设计领域,具体是指一种高超飞行器高热流密度下部件热防护结构。
Thermal protection structure for high-heat-flux lower part of hypersonic vehicle
一种高超飞行器高热流密度下部件热防护结构
2024-08-16
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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