发射筒/固体发动机复合结构内部温度场随环境温度的变化规律  

Dependence of temperature field inside the composite structure of the launcher/solid rocket motor on the ambient temperature

作　　者：顼则梁 李剑 艾春安 王学仁 刘凯旋 XU Zeliang;LI Jian;AI Chunan;WANG Xueren;LIU Kaixuan(206,Rocket Force University of Engineering,Xi'an 710025,China)

机构地区：[1]火箭军工程大学206室

出　　处：《固体火箭技术》2019年第5期664-672,共9页Journal of Solid Rocket Technology

摘　　要：针对装载在发射筒内的固体发动机装药初温预估问题,基于某型武器装备实际结构建立了"发射筒/固体发动机"多层复合结构传热模型和相应的有限元模型,应用ANSYSAPDL软件对该复合结构在不同环境温度载荷作用下内部温度场分布进行数值仿真计算,得到复合结构瞬时温度场和内部温度随外界环境温度变化的规律曲线。通过与开展的实际装备的环境温度实验比较,结果表明,仿真计算的内部温度随时间变化曲线与装备实验实测曲线基本一致,温度最大误差为4%,在合理误差范围内验证了本文建立的模型及仿真算法的正确性。因此,余弦式周变环境载荷工况下的仿真结果对实际装备作战应用具有一定参考价值。In view of the initial temperature forecast problems of the loaded propellants within SRM,multi- layer composite structure heat transfer model and the corresponding finite element model have been established based on the actual structure of a typical weapon and equipment set up of “launcher/solid rocket motor”.The ANSYS APDL software was used for simulation,where the internal temperature distribution of the composite structure under different environmental temperature loading is obtained by numerical simulation.The transient temperature field and temperature inside the composite structure is obtained with the law of the external environment temperature change curve.With ambient temperature experimental comparison of the actual equipment,the results show that the simulation calculation of the internal temperature change curve over time and measured curve,the maximum error is 4%.It is within the reasonable range of error model and established in this paper is verified the correctness of the simulation algorithm,so the cosine type weeks under variable working condition of environmental loading simulation results of actual equipment operational application is of a certain reference value.

关 键 词：固体火箭发动机 传热 温度场 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]