The invention discloses an interstage mixing and separating structure of a carrier rocket. The interstage mixing and separating structure comprises: an upper-stage cabin body and a lower-stage cabin body which are connected end to end, wherein an engine exhaust nozzle with an opening facing the lower-stage cabin body is contained in the upper-stage cabin body; and a heatproof skirt assembly connected to the lower end in the upper-stage cabin body and the outer wall of the engine exhaust nozzle and used for preventing jet flow sprayed out of the engine exhaust nozzle from being turned over intothe upper-stage cabin body. The heatproof skirt assembly is connected between the outer walls of the engine exhaust nozzle at the lower end in the upper-stage cabin body, so that jet flow jetted by the engine exhaust nozzle can be prevented from being turned over into the upper-stage cabin body, and internal instruments and equipment in the upper-stage cabin body are protected against back-roll ablation of the engine exhaust nozzle; interstage separation impulse is provided by adopting the jet flow of the upper-stage engine exhaust nozzle, the rocket body structure can be simplified, and thecost is reduced; and non-pressure-building design reduces the structural weight of the rocket body and improves the carrying efficiency of the rocket body.
本发明公开了一种运载火箭级间混合分离结构,包括:首尾相连的上面级舱体和下面级舱体,所述上面级舱体的内部容纳有开口朝向所述下面级舱体设置的发动机尾喷管;防热裙组件,连接在所述上面级舱体内部下端和所述发动机尾喷管的外壁,用于防止所述发动机尾喷管喷出的喷流翻卷至所述上面级舱体内部。通过在上面级舱体内部下端发动机尾喷管的外壁之间连接防热裙组件,可以防止发动机尾喷管喷出的喷流翻卷至上面级舱体内部,保护上面级舱体的内部仪器设备免受发动机尾喷流的反卷烧蚀;而采用上面级发动机尾喷管喷流提供级间分离冲量,可简化箭体构造简单,降低成本;同时非憋压设计使得降低箭体的结构重量,提高箭体的运载效率。
Interstage mixing and separating structure of carrier rocket
一种运载火箭级间混合分离结构
2020-04-28
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
European Patent Office | 2022
|European Patent Office | 2024
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