火药起动系统对发动机起动性能的影响分析  

Influence of gunpowder start system on starting performance of liquid rocket engines

作　　者：孙海雨[1] 刘志让[2] 

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]航天推进技术研究院,陕西西安710100

出　　处：《火箭推进》2012年第4期32-37,共6页Journal of Rocket Propulsion

基　　金：国家"863"项目(2008AA7050406)

摘　　要：针对采用火药起动器起动的泵压开式循环液体火箭发动机,对其起动系统进行了分析和研究。建立了液体火箭发动机火药起动器计算模型和起动系统燃气管路流场计算模型。将所建立的起动系统模型应用于发动机系统仿真,对发动机火药起动过程进行仿真,分析了起动系统中火药起动器参数和燃气管路参数对发动机起动性能的影响,确定了主要影响参数和影响规律。火药起动器火药药柱内径、火药药柱长度以及燃气管路火药起动器喷管喉部直径为强影响因素;燃气管路涡轮喷嘴喉部直径和管路出口直径在确保发动机火药起动主要工况段燃气管路流场流态为额定工况流态的前提下,为弱影响因素。试验数据验证表明,发动机起动系统的仿真结果正确、可信。Aiming at the pumping pressure open cycle liquid rocket engine which is started by solid start cartridge （SSC）, the performance of the start system is studied in this paper. The simulated model of SSC in the start system and the numerical model of the powder gas pipeline were established to simulate the process of gunpowder start. The influence of SSC and gas pipeline parameters on start performance of engine is analyzed to ensure the main influence parameters and regular patterns. It is found that the powder quantity of SSC and the diameter of the first throat in the powder gas pipeline are the most effective factors to the engine＇s start characteristic. The diameter of the powder gas pipeline＇s second throat and the diameter of the powder gas pipeline＇s outlet are the least ones in the case of that the powder gas pipeline＇s flow field keeps rated condition. The simulated result of the start system was proven in engine hot tests.

关 键 词：液体火箭发动机 起动系统 火药起动器 燃气管路 数值仿真 

分 类 号：V430-34[航空宇航科学与技术—航空宇航推进理论与工程]