The embodiment of the invention provides a reentry vehicle centralized thermal protection device and a control method thereof. The thermal protection device comprises an aircraft body, the aircraft body comprises a load cabin and a protection part, the front end of the protection part forms the head of the aircraft, the tail end of the protection part forms the shoulder of the aircraft, a head jet hole is formed in the head, and a plurality of shoulder jet holes are formed in the shoulder; the spherical gas cylinder is arranged in the aircraft body, the spherical gas cylinder is provided with a first gas outlet hole and a plurality of second gas outlet holes, the first gas outlet hole is selectively communicated with the head jet flow hole, the plurality of second gas outlet holes are in one-to-one correspondence with the plurality of shoulder jet flow holes, and each second gas outlet hole is selectively communicated with the corresponding shoulder jet flow hole; the spherical gas cylinder is used for spraying gas to the head jet hole and/or the shoulder jet hole so that thermal protection can be formed on the head and/or the shoulder. According to the embodiment of the invention, jet flow thermal protection can be formed at multiple positions of the head and the shoulder of the aircraft through the centralized spherical gas cylinder.
本申请实施例提供一种再入飞行器集中式热防护装置及其控制方法。热防护装置包括飞行器本体,飞行器本体包括载荷舱和防护件,防护件前端构成飞行器的头部,防护件的尾端构成飞行器的肩部,其中,头部设置有头部射流孔,肩部设置有多个肩部射流孔;球形气瓶,设置于飞行器本体内,球形气瓶设置有第一出气孔和多个第二出气孔,第一出气孔与头部射流孔可选择连通,多个第二出气孔与多个肩部射流孔一一对应,每个第二出气孔与对应的肩部射流孔可选择连通,球形气瓶用于向头部射流孔和/或肩部射流孔喷射气体,以使头部和/或肩部形成热防护。本申请实施例通过一个集中式的球形气瓶可以对飞行器头部和肩部多位置形成射流热防护。
Centralized thermal protection device of reentry vehicle and control method of centralized thermal protection device
一种再入飞行器集中式热防护装置及其控制方法
2023-06-27
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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