一种高可靠轻量化泄压防热装置设计与验证  

Design and Verification of High Reliable and Lightweight Mechanism for Decompression and Thermal Protection

作　　者：殷新喆 罗毅欣[1] 祁玉峰[1] 齐跃 YIN Xinzhe;LUO Yixin;QI Yufeng;QI Yue(Beijing Institute of Spacecraft System Engineering, Beijing 100094, China;Institute of Remote Sensing Satellite, China Academy of Space Technology, Beijing 100094, China)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]中国空间技术研究院遥感卫星总体部,北京100094

出　　处：《航天器工程》2021年第5期38-44,共7页Spacecraft Engineering

摘　　要：针对在轨具有封闭舱体的航天器发射过程中环境气压降低,需要对舱体进行即时泄压和再入过程中舱体气动防热的问题,文章基于杆式压紧释放原理提出了一种集泄压和防热两大功能于一体的高可靠作动装置。该装置在发射入轨段通过预置泄压孔实现舱内外压力平衡,入轨后通过机构作动密闭泄压孔实现气动防热功能,并给出工作到位信号。经仿真分析和试验验证,结果表明:该装置设计合理有效,并具备结构简单、轻量化、泄压效率高、可靠性高的特点,可为后续航天器舱体的主动泄压和热防护的机构产品设计提供参考。Based on principle of hold-down and release of rod,a high reliable mechanism used in decompression and thermal protection is developed,in order to balance the internal and external pressure immediately when the ambient pressure of closed orbit spacecraft lessens in launch environment,and to realize pneumatic heat protection of reentry proceeding later.The mechanism balances the internal and external pressure of spacecraft by a precast hole in launch environment,then closes the hole to realize pneumatic heat protection in orbit,whereafter,the signal detection will achieve.After simulation analysis and test measurements,the mechanism is demonstrated to be logical and effective,which is due to simple structure,lightweight,efficient decompression and high reliability.The mechanism introduced in this paper is a good reference for following spacecraft which need active decompression and thermal protection functions.

关 键 词：航天器 泄压防热 压紧释放 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]