摘要
某低温火箭为减少箭地接口从而提高射前连接器脱落可靠性,舱段吹除系统采用统一供配气模式。为验证该模式中各舱段吹除流量分配的合理性,建立了多级火箭的舱段吹除试验系统,通过试验获得了各舱段流量,同时获得不同进箭温度下各舱段吹除流量的变化。结果表明:采用孔板前压力和温度测试数据计算舱段流量能有效表征实际流量,在满足热环境条件的情况下适当提高吹除温度能有效降低各舱段流量从而减少地面供气系统规模,试验结果与仿真分析结果吻合较好,为后续大型火箭研制提供了参考。
In order to reduce the rocket interface and improve the reliability of connector falling off,the rocket blowing system adopts the unified gas supply mode.In order to verify the rationality of flux for each cabin,a experiment system is established.The flux of each cabin is obtained,and the changes of the flux of each cabin under different inlet temperatures are obtained.The results show that using the pressure and temperature data in front of the orifice to calculate the flux is correct,and appropriately increasing the blowing temperature can effectively reduce the flux of each cabin under the condition of meeting the thermal environment conditions,so as to reduce the scale of the gas supply systems.The test results are in good agreement with the simulation results,which provides a reference for the development of large-scale rocket.
作者
吴姮
丁蕾
税晓菊
贺启林
马方超
Wu Heng;Ding Lei;Shui Xiao-ju;He Qi-lin;Ma Fang-chao(Beijing Institute of Aerospace System Engineering,Beijing,100076)
关键词
火箭
吹除系统
统一供配气模式
rocket
blowing system
unified gas supply mode
