H2O2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 H2O2 Engine Applied in the Launch Test of Near Space Spherical Spacecraft
何浚珧 1张玉锋 2葛逸飞 2李腾 2魏小林2
作者信息
- 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;西安交通大学,陕西 西安 710049
- 2. 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
- 折叠
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(H2O2)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,H2O2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,H2O2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.
Abstract
Ground testing was conducted on an engine test system using hydrogen peroxide(H2O2)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 H2O2 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
H2O2单组元/发动机系统/临近空间/环境适应性Key words
H2O2 single component/engine system/near space/environmental adaptability引用本文复制引用
出版年
2024
NETL
NSTL
万方数据