CAJ | 학술논문

在复杂工程系统的概念设计优化中,高精度数值分析方法得到广泛应用,将高精度数值分析与优化方法有机结合,对设计空间展开全面搜索与寻优,已经成为现代设计优化方法的重要发展方向.以水下滑翔机的概念设计为研究对象,引入代理模型,控制高精度分析试验的数量,有效地化解精度与效率之间的矛盾.将参数化几何建模、网格划分以及流体数值模拟分析集成为自动分析流程,并以此为基础采用试验设计理论,构建代理模型,解决水下滑翔机机翼的多目标设计优化问题.给出基于代理模型的设计优化过程,并系统地比较几种试验设计方法的适应性,重点讨论多项式响应面和径向基函数代理模型,所得代理模型相对误差小于2%.采用梯度寻优方法与遗传算法在给定设计空间内进行全面搜索,获得机翼的最佳平面构形,水下滑翔机的升阻比提高6.76%,俯仰力矩的绝对值由0.276 0 N·m降低为0.001 5 N·m,提高水下滑翔机的运动性能.
재복잡공정계통적개념설계우화중,고정도수치분석방법득도엄범응용,장고정도수치분석여우화방법유궤결합,대설계공간전개전면수색여심우,이경성위현대설계우화방법적중요발전방향.이수하활상궤적개념설계위연구대상,인입대리모형,공제고정도분석시험적수량,유효지화해정도여효솔지간적모순.장삼수화궤하건모、망격화분이급류체수치모의분석집성위자동분석류정,병이차위기출채용시험설계이론,구건대리모형,해결수하활상궤궤익적다목표설계우화문제.급출기우대리모형적설계우화과정,병계통지비교궤충시험설계방법적괄응성,중점토론다항식향응면화경향기함수대리모형,소득대리모형상대오차소우2%.채용제도심우방법여유전산법재급정설계공간내진행전면수색,획득궤익적최가평면구형,수하활상궤적승조비제고6.76%,부앙력구적절대치유0.276 0 N·m강저위0.001 5 N·m,제고수하활상궤적운동성능.
High precision numerical analysis methods have been extensively used in the conceptual design of complex engineering systems. Combining high precision numerical analysis methods with optimization algorithms to make a systematic exploration of the design space has become an important topic in the modem design method. During the design process of an underwater glider's wing, a surrogate model is introduced to decrease the computation times of high precision analysis. By this means, the contradiction between precision and efficiency is solved effectively. Through integrating the parametric geometry modeling, mesh generation and computational fluid dynamics analysis as an automatic workflow, and adopting the design of experiment (DOE) theory, a surrogate model is constructed to solve the multi-objects design optimization problem of the underwater glider. The procedure of surrogate model construction is presented and several DOE methods are compared systematically, especially the characteristics and applicability of the response surface model and the radial basis functions model. A fast design exploration and optimization is implemented and the optimal plane of the underwater glider is found out based on the surrogate model. Optimization results show that the lift drag ratio improves about 6.76%, and the pitch moment is reduced from 0.276 0 N·m to 0.001 5 N·m.