一种基于火箭贮箱内推进剂的增压姿控一体化系统
By using an integrated system for pressurizing and controlling the propellant within the rocket's propellant tanks, and utilizing thruster heat exchange devices and actuation mechanisms, the rocket's weight and cost issues have been resolved. This has enabled efficient attitude control and propellant tank pressurization, thereby improving the rocket's mission adaptability and reusability.
CN120946471BActive Publication Date: 2026-07-17BEIJING INST OF ASTRONAUTICAL SYST ENG
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF ASTRONAUTICAL SYST ENG
- Filing Date
- 2025-09-05
- Publication Date
- 2026-07-17
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Figure CN120946471B_ABST
Abstract
本发明涉及一种基于火箭贮箱内推进剂的增压姿控一体化系统，氧过滤器和燃过滤器分别位于从氧化剂贮箱和燃料贮箱输送管引出的分支管路上，氧过滤器和燃过滤器下游分别连接氧电动泵和燃电动泵为推进剂增压；氧电动泵和燃电动泵后的管路与N台并联布置的推力器相连，其中泵后管路连接氧 / 燃电磁阀，随后流入下游氧 / 燃主路文氏管和氧 / 燃辅路文氏管，氧 / 燃主路推进剂随后进入推力器掺混燃烧产生推力，氧 / 燃辅路推进剂经换热器后通过管路引回至贮箱对贮箱增压；作动机构与推力器连接，控制推力器摆动以实现推力矢量调节。实现了减少增压气瓶携带量和结构重量，降低了系统复杂程度、简化了地面操作，提升了火箭任务适应性。
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