国防科技大学学报Issue(1)：129-136,8.DOI:10.11887/j.cn.201601021
序列近似优化方法及其在火箭外形快速设计中的应用
Sequential approximate optimization method and its application in rapid design of rocket shape
摘要
Abstract
Sequential approximate optimization method has shortcomings in several respects,such as surrogate model establishing and infill strategy at present.Basing on local density of sampling points,the influence volume concept which is inversely proportional to local density was introduced and then the optimal kernel width of radial basis function was obtained by means of total influence volume optimization,thus,the function approximation needs in sequential approximate optimization process under the conditions of different scales and heterogeneous samples were satisfied.Potential feasible region infill strategy was proposed and potential optimal strategy was applied together,both exploration and exploitation capacity of the algorithm were satisfied.Three-step convergence criterion was set up.The algorithm flow process of sequential approximate optimization was constructed.For Golinski reducer optimization problem,the global optimal solution was solved after calculating original model 42 times,which embodied the good global optimization capacity and searching efficiency of the algorithm.Shape optimization mathematical model was established for TH -II rocket,global optimal shape was gained after 165 times of original model calling using the proposed method.The design efficiency was increased greatly and TH -II rocket aerodynamic shape was proved reliable by flight testing.关键词
序列近似优化/代理模型/采样策略/局部密度/收敛判定准则/“天航二号”火箭/外形优化Key words
sequential approximate optimization/surrogate model/infill strategy/local density/convergence criterion/TH -II rocket/shape optimization分类
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彭科,胡凡,张为华,武泽平..序列近似优化方法及其在火箭外形快速设计中的应用[J].国防科技大学学报,2016,(1):129-136,8.基金项目
国家自然科学基金资助项目 （）
