带侵蚀效应的三维双燃速装药固体火箭发动机点火过程  

Ignition process of a 3-D dual-burning rate solid rocket motor with erosive burning

作　　者：白涛涛[1] 张泽远[1] 邢国强[1] 王虎干[1] 孙振华[1] BAI Taotao;ZHANG Zeyuan;XING Guoqiang;WANG Hugan;SUN Zhenhua(Key Laboratory of Aviation Science for Airborne Guided Weapons, Propellant System Institute, China Airborne Missile Academy, Luoyang Henan 471009, China)

机构地区：[1]中国空空导弹研究院推进系统研究所航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《航空动力学报》2018年第5期1256-1262,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(11402283)

摘　　要：针对三维双燃速装药固体火箭发动机,采用商用CFD计算软件的用户自定义方程对点火瞬态过程中的侵蚀燃速、燃面温度、质量源项、动量源项、能量源项及点火器入口等进行了二次开发,并进行了考虑侵蚀效应的点火瞬态过程流场仿真计算,与地面点火试验内弹道数据进行了对比分析。结果表明:点火初期发动机头部的气流流动十分复杂,且头部压强随时间变化十分剧烈;堵盖打开会造成头部升压梯度振荡,并产生负升压梯度;仿真与试验结果符合较好,说明采用一维非定常固相传热方程计算三维燃面温度可以满足当前工程要求,计算方法正确有效。Targeting 3-D dual-burning rate solid rocket motor（SRM）,the erosive burning rate,burning surface temperature,mass source,momentum source,energy source and igniter inlet boundary condition were investigated to aid in the ignition transient flow field simulation with erosive burning,using the user defined function module of commercial CFD code.The focus was put on the analysis of simulation results and comparison between simulation and test results indicate that：in the initial stage of ignition,the flow structure is highly complicated and the pressure varies drastically in the head-ending region;the open of nozzle closure leads to a negative pressure gradient and the shake of pressure gradient;the calculated results are consistent with the experiments showing,it is appropriate to compute the 3-D burning surface temperature using 1-D unsteady heat transfer equation for the solid phase,and the calculated approach is accurate and valid.

关 键 词：侵蚀效应 双燃速 固体火箭发动机 点火 二次开发 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]