飞行器二元变几何进气道调节机构多目标优化设计  

Multi-objective optimization design of binary variable geometry inlet regulating mechanism for aircraft

作　　者：齐海涛[1,2] 刘旭 刘咄[1] 孟浩洋 苏航 QI Haitao;LIU Xu;LIU Duo;MENG Haoyang;SU Hang(School of Mechanical Engineering and Automation,Beihang University,Beijing 100191,China;Engineering Training Center,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学机械工程及自动化学院,北京100191 [2]北京航空航天大学工程训练中心,北京100191

出　　处：《航空动力学报》2025年第1期189-204,共16页Journal of Aerospace Power

基　　金：装备预研重点实验室基金(6142703200201)。

摘　　要：针对高超声速飞行器二元变几何进气道调节机构质量轻、能耗低、精度高的设计需求,对机构开展了多目标优化工作,获得了综合性能最优的设计方案,并验证了方案的可行性。首先通过受力分析与软件ADAMS仿真的手段,得到楔板与喉道板作动所需的最小驱动力;然后建立了机构质量、能耗和刚度的数学模型,确定了机构的设计变量与约束条件,采用NSGA-Ⅱ优化算法进行多目标优化得到帕累托解集,通过层次图的绘制实现了帕累托前沿的可视化,并选取了一组最优解作为设计方案;最后通过机电概念设计模块(MCD)运动学仿真分析对方案的可行性进行验证。结果表明:与优化前相比,机构的质量降低了6.48%,能耗降低了8.35%,并且能够满足调节作动的行程需求。Considering the design requirements of hypersonic aircraft’s binary variable geometry inlet regulating mechanism for light weight,low energy consumption and high accuracy,multi-objective optimization was carried out for the mechanism,the design scheme with the best comprehensive performance was obtained and the feasibility of the scheme was verified.Firstly,through force analysis and ADAMS software simulation,the minimum driving force required for the wedge plate and throat plate was obtained.Then the mathematical model of the mass,energy consumption and stiffness of the mechanism was established,the design variables and constraints of the mechanism were determined,and the Pareto solution set was obtained by multi-objective optimization using NSGA-Ⅱoptimization algorithm.The visualization of Pareto frontier was realized by drawing the level diagram,and a group of optimal solutions were selected for the design scheme.Finally,the feasibility of the scheme was verified by mechatronics concept designer(MCD)kinematics simulation analysis.The results showed that the weight of the mechanism was reduced by 6.48%and the energy consumption reduced by 8.35%compared with that before optimization,and also it can meet the displacement demand of actuation.

关 键 词：高超声速飞行器 二元变几何进气道 调节机构 质量建模 多目标优化 

分 类 号：V231.91[航空宇航科学与技术—航空宇航推进理论与工程]