摘要
针对高空模拟舱内逆向布置的推力室点火瞬时过程中舱内压力的变化规律进行了理论和数值仿真分析,推力室高速气流的动能是推力室短程点火过程中舱内压力大幅上升的主要原因。为保证推力室点火时舱内的真空度,需要在推力室出口配置导流装置将燃气导出真空舱。对单台和4台并联推力室进行点火试验,试验表明:采用燃气导流能够较好保持舱内真空度,是整机多推力室高空模拟试验的新思路。
The theoretical and numerical simulation analyses for the pressure variation in the vacuum chamber that simulated high altitude condition during ignition transient of reversely-fixed thrust chamber were performed. Results shows significant pressure increase in the chamber in the working process of rocket nozzle, which is mainly caused by the kinetic energy of high-speed exhaust gas. In order to ensure the vacuum degree in the chamber, a deflector is needed to guide the gas out of the chamber. The numerical analysis and experimental test results show that the pressure rise can be reduced by the configuration of gas deflector tube at exit of the thrust chamber. It indicates that this method is benefit to the vacuum of the test chamber. This research may provide a guide for the test of the attitude and orbit control system in the high altitude simulation test.
出处
《火箭推进》
CAS
2014年第2期77-81,94,共6页
Journal of Rocket Propulsion
基金
中国航天科技集团公司支撑项目(2011JY06)
关键词
高空模拟
推力室逆置
燃气导流
high altitude simulation
reversely-fixed thrust chamber
gas deflecting
