壳体外防热设计计算及风洞试验研究  

Wind tunnel test and design of external thermal insulation for shell

作　　者：郭运强[1] 王云霞[1] 孙展鹏[1] 史宏斌[1] 甘晓松[1] 高波[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2018年第1期18-22,共5页Journal of Solid Rocket Technology

摘　　要：基于ANSYS/Workbench平台,二次开发了固体火箭发动机壳体外防热计算的一维程序算法,开展某发动机外防热仿真计算,获得了壳体与涂层间界面最高温度,对比相应风洞试验测试结果,验证了算法的正确性。最后,建立了某固体火箭发动机壳体三维参数化模型,应用该算法,选取外防热涂层厚度作为设计变量,以壳体与涂层间界面最高温度为目标函数,联合ANSYS/Workbench中目标驱动优化功能(Goal Driven Optimization-GDO)进行设计计算,实现了壳体外防热涂层厚度设计的自主择优。Based on ANSYS/Workbench platform, secondary arithmetic development was proposed,which has been used to design external thermal insulation of solid rocket motor shell independently A 3D parametric model of solid rocket motor shell was established, the thickness of external thermal insulation coating was selected as designing variable, and the highest outside wall temperature of shell was considered as objective function.The Goal Driven Optimization-GDO of ANSYS/Workbench was used to improve the design and calculation aiming to realize the real-time optimization of shell external thermal insulation coating.At last,by comparing to the experimental results with the wind tunnel test of a certain engine, the correctness and rationality of the calculation method was verified.

关 键 词：壳体 外防热 设计 风洞试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]