CAJ | 학술논문

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。
침대신형로기동심통자력발사열배경평고여우화설계문제，의탁탄성변형화역동분층결합적동망격기술，구해료이유축대칭N-S방정，분석료“중단도류”동심통동태열배경특성，학정료열배경평개지표；통과건립이우화랍정초립방실험설계화사계향응면위이론기출적근사수학모형，해결료CFD자동건모곤난、직접심우계산량대적난점；이용다도유전화제도우화산법탑건조합우화책략평태，극복료류장재불동열결구조건하적강비선성문제，병구건료지지근사수학모형적열배경우화구가。대비수치결과표명，도흡진입내통적저온기체유력개선료동심통열배경；건립적근사수학모형정도교고，만족공정수구；우화후，열배경특성발생량성변화，도탄총체열배경득도현저개선。
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.