固体火箭技术Issue(2)：172-178,7.DOI:10.7673/j.issn.1006-2793.2015.02.005
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
摘要
Abstract
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Key words
concentric canister launcher ( CCL )/missile jet/thermal environment characteristics/approximate mathematic model/optimization design分类
航空航天引用本文复制引用
杨风波,马大为,任杰,乐贵高,蔡德咏..新型同心筒自力发射热环境优化设计[J].固体火箭技术,2015,(2):172-178,7.基金项目
国防基础科研资助项目( B2620110005) （ B2620110005）
国防预研项目(403050102)。 （403050102）
