摘要
以高超声速轴对称进气道为研究对象,对进气道型面进行参数化设计,选取一般二次曲线饱和度、一般二次曲线控制线、过渡圆弧半径、喉道拐角、喉道等直段长高比、中心线控制参数、当量锥角7个参数作为设计变量对进气道进行了多目标优化设计。设计过程中,利用正交试验设计方法确定初始样本点,建立进气道在设计点下总压恢复系数、出口畸变两个优化目标与设计参数之间的Kriging代理模型,采用第二代非劣排序遗传算法(NSGA-Ⅱ)对代理模型进行分析求解。结果表明:进气道型面在经过多目标优化设计后,在设计点下进气道总压恢复性能提升2.63%,出口畸变指数减小27.57%。
Taking the hypersonic axisymmetric inlet as the research object, firstly, parametric design of the inlet profile was carried out, and seven parameters, such as the general conic saturation, the general conic control line, the transition arc radius, the throat corner, the throat straight line to height ratio, the center line control parameter and the equivalent cone angle, were selected as the design variables to carry out the multi-objective design of the inlet. In the design process, the initial sample points were determined by orthogonal test design method, and Kriging surrogate models between two optimization objectives of inlet total pressure recovery coefficient and outlet distortion with design parameters were established. The surrogate model was analyzed and solved by the second generation of Non-Dominated Sorting Genetic Algorithm(NSGA-Ⅱ). The results showed that after multi-objective optimization, the total pressure recovery performance of the inlet increased by 2.63%, and the outlet distortion reduced by 27.57%.
作者
王昌盛
额日其太
丁文豪
WANG Changsheng;Eriqitai;DING Wenhao(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2020年第7期1392-1401,共10页
Journal of Aerospace Power
