火箭动力试验液氢加注试验研究

Study on the Filling Test of Liquid Hydrogen in Launch Vehicle Stage Propulsion System Test

为了研究运载火箭在靶场发射时液氢加注的流程和进箭参数,需要通过动力试验进行全面的试验考核。从原理上分析了影响液氢加注流量和温度的几个因素,同时对某动力台液氢加注系统设计参数和流程进行介绍;结合中国某型运载火箭芯一级和芯二级模块两次动力试验,对液氢实际进箭过程中的流量变化、温度上升、进箭压力等参数进行详细分析。分析结果表明:液氢加注参数满足设计指标及动力试验要求,对某型运载火箭合练和首飞提供了技术参数和经验参考。

The factors that affect the flow rate and temperature is analyzed,the design parameters and processes of liquid hydrogen filling system about a stage propulsion system test site are introduced.The detailed analysis about the change of flow rate,rise of temperature and pressure of inlet is discussed.It can conclude form the results that the parameters of liquid hydrogen can meet the design targets and the requirements of stage propulsion system test.Further more,the filling of liquid hydrogen in the tests provide parameters of hydrogen and operation experiences for the launch vehicle comprehensive test and virgin flight.