基于样本映射与动态Kriging的飞行器离散连续优化方法
收稿日期: 2023-03-21
修回日期: 2023-04-25
录用日期: 2023-05-26
网络出版日期: 2023-06-02
基金资助
国家自然科学基金(52272360);北京市自然科学基金(3222019);北京理工大学青年教师学术启动计划(XSQD-202101006);北京理工大学科技创新计划项目(2021CX01013);北京理工大学研究生科研水平和创新能力提升专项计划(2022YCXZ017)
Kriging?based mixed?integer optimization method using sample mapping mechanism for flight vehicle design
Received date: 2023-03-21
Revised date: 2023-04-25
Accepted date: 2023-05-26
Online published: 2023-06-02
针对复杂飞行器系统离散连续混合优化计算成本高、全局收敛性差等问题，提出了一种基于样本映射与动态Kriging的离散连续优化方法（SMDK-DC）。该方法采用Kriging代理模型代替高耗时仿真模型以降低计算成本，并定制一种基于综合曼哈顿距离准则的样本点映射机制，在连续-离散空间内高效生成满足均布性要求的真实样本点。将期望改善度准则与重点采样空间方法相结合，辨识优质新增样本点，持续动态更新Kriging，引导离散连续优化过程快速收敛。标准数值算例测试结果表明，与SOMI、NOMAD等国际同类方法相比，SMDK-DC方法在全局收敛性与鲁棒性方面具有显著优势。使用该方法求解固体火箭发动机多学科设计优化问题，优化方案在满足燃烧室、内弹道等学科约束条件前提下，使得发动机总冲提升12.92%以上，且优化收益较SOMI方法提高1.71%，从而验证了本文工作的有效性与工程实用性。
李昊达 , 龙腾 , 史人赫 , 叶年辉 . 基于样本映射与动态Kriging的飞行器离散连续优化方法[J]. 航空学报, 2024 , 45(3) : 228726 -228726 . DOI: 10.7527/S1000-6893.2023.28726
To deal with the problems of high computational cost and poor global convergence that often exist in discretecontinuous mixed optimization of complex flight vehicle systems， a Sample Mapping and Dynamic Kriging based Discrete-Continuous Mixed Optimization method （SMDK-DC） is proposed. In this method， time-consuming simulation model is replaced by Kriging surrogate model to reduce computational expenses. A sample point mapping mechanism based on generalized Manhattan distance criterion is also proposed to efficiently generate uniformly-distributed real sample points in continuous-discrete domain. Expected improvement criteria is combined with significant sampling space to identify new sample points，update Kriging continuously and dynamically， and guide the rapid convergence of the discrete-continuous optimization process. Benchmark cases show that compared with international methods such as SOMI and NOMAD， SMDK-DC has significant advantages in global convergence and robustness. Finally， SMDK-DC is used for solving a multidisciplinary design optimization problem of solid rocket motor. The method， on the premise of satisfying all the constraints of the combustion chamber and internal ballistic discipline， leads to a total impulse increase of at least 12. 92%， and the optimization yield is 1. 71% higher than that of SOMI， which verifying the effectiveness and engineering practicability of SMDK-DC.
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