新型同心筒自力发射热环境优化设计  

Optimization design for thermal environment of a new roadbed concentric canister launcher

作　　者：杨风波[1] 马大为[1] 任杰[1] 乐贵高[1] 蔡德咏[2] 

机构地区：[1]南京理工大学机械工程学院 [2]72465部队

出　　处：《固体火箭技术》2015年第2期172-178,共7页Journal of Solid Rocket Technology

基　　金：国防基础科研资助项目(B2620110005);国防预研项目(403050102)

摘　　要：针对新型路基同心筒自力发射热环境评估与优化设计问题,依托弹性变形和域动分层结合的动网格技术,求解了二维轴对称N-S方程,分析了"中段导流"同心筒动态热环境特性,确定了热环境评价指标;通过建立以优化拉丁超立方实验设计和四阶响应面为理论基础的近似数学模型,解决了CFD自动建模困难、直接寻优计算量大的难点;利用多岛遗传和梯度优化算法搭建组合优化策略平台,克服了流场在不同热结构条件下的强非线性问题,并构建了支持近似数学模型的热环境优化构架。对比数值结果表明,倒吸进入内筒的低温气体有力改善了同心筒热环境;建立的近似数学模型精度较高,满足工程需求;优化后,热环境特性发生良性变化,导弹总体热环境得到显著改善。Based on dynamic mesh technology with spring based smoothing method,and laying based zone moving method, the axisymmetric N-S equations were solved numerically, the dynamic thermal environment characteristics were obtained to deal with the thermal environment evaluating and optimization design problem of the new “middle diversion” concentric canister launcher （CCL）,and evaluation index of thermal environment was also determined.The approximate mathematic model was established by op-timal latin hypercube design and fourth-order response surface method to solve the automatic modeling problem of CFD and compen-sate for the shortcoming of large amount of calculation for direct optimization. A combinatorial optimization strategy platform based on Multi-Island Genetic Algorithm and Sequential Quadratic Programming was established to overcome the problem of strong nonlin-ear characteristic of the flow field parameters under different thermal structure conditions,and the optimization design system of ther-mal environment for missile which supports approximate mathematic model was also built. The comparison of the numerical results show that thermal environment of internal canister and external cylinder are improved by the cryogenic gas came from the cylinder port;the accuracy of approximate mathematic model is high enough to meet engineering requirements;after optimization, the thermal environment characteristics change positively,and the thermal environment of missile has been improved significantly.

关 键 词：同心筒发射装置 燃气射流 热环境特性 近似数学模型 优化设计 

分 类 号：V553.1[航空宇航科学与技术—人机与环境工程]