H_(2)O_(2)发动机应用于临近空间球载飞行器投放试验的环境适应性研究  

Environmental Adaptability Study of H_(2)O_(2) Engine Applied in the Launch Test of Near Space Spherical Spacecraft

作　　者：何浚珧 张玉锋 葛逸飞 李腾[1] 魏小林[1] He Junyao;Zhang Yufeng;Ge Yifei;Li Teng;Wei Xiaolin(State Key Laboratory of High-Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Science,Beijing 100190,China;Xi'an Jiaotong University,Xi’an 710049,China)

机构地区：[1]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [2]西安交通大学,陕西西安710049

出　　处：《气动研究与试验》2024年第6期30-36,共7页Aerodynamic Research & Experiment

摘　　要：针对临近空间球载发射飞行器的特殊环境,对以过氧化氢(H_(2)O_(2))为推进剂的发动机试验系统进行了地面测试,同时开展环境适应性研究。结果表明,H_(2)O_(2)作为推进剂的单组元发动机系统方案安全性和环境适应性良好、易于使用,H_(2)O_(2)可作为未来球载发射飞行器动力推进剂选择。测试方案中通过PTC加热片,结合温控开关以及保温材料,将发动机储液罐和喷管壁面的温度维持在38~42℃,满足飞行器真实飞行环境要求,发动机测试后各项性能良好。Ground testing was conducted on an engine test system using hydrogen peroxide(H_(2)O_(2))as the propellant for spherical launch vehicles in the special environment of near space,and environmental adaptability research was also carried out.The results indicate that the single component engine system scheme using H_(2)O_(2) as the propellant has good safety and environmental adaptability,is easy to use,and can be used as a power propellant choice for future spherical launch vehicles.In the testing plan,PTC heating elements,combined with temperature control switches and insulation materials,were used to maintain the temperature of the engine fluid storage tank and nozzle wall between 38~42℃,meeting the requirements of the real flight environment of the aircraft.The engine performance was good after testing.

关 键 词：H_(2)O_(2)单组元 发动机系统 临近空间 环境适应性 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]