液体火箭舱段热环境保障系统仿真及试验研究

Simulation and Experimental Investigation on Thermal Environment Control System Used in New Generation Launch Vehicle with LO_2/LH_2 Propulsion

新一代运载火箭采用低温推进剂,起飞前低温舱段温度需要通过一定流量热氮维持在舱段设备仪器工作要求范围内,火箭出厂测试中发现部分舱段孔板出口流量不符合理论要求。利用AMESim建立了热环境保障系统仿真模型,得出了理想孔板喉部面积,更换箭上实际孔板后进行了试验验证,结果表明:孔板喉部面积组合能够控制舱段孔板出口流量在要求范围内,为今后工作提供了理论依据。

New generation launch vehicle with LO_2/LH_2 propulsion using heat nitrogen with loop vent pipes in inner cabins to keep the equipment and instrument of low temperature compartment working in operating temperature before departure, the flow-rate of orifice export of some compartment is not suitable in the rocket factory testing. The simulation model of thermal environment control system is established based on AMESim, obtained suitable orifice throat area, change the orifice of launch and making a test for verification. The experimental investigation results show that orifice throat area can control the flow-rate of orifice export of all compartment within the scope of the requirements, provide a theoretical basis for the future work.