Multi-objective optimization design of binary variable geometry inlet regulating mechanism for aircraft
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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。
Abstract: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-Ⅱ optimization 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.
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图 15 额定动载荷与丝杠直径拟合曲线
Figure 15. Fitting curve between rated dynamic load and diameter of lead screw
图 20 压缩楔板调节机构运动仿真曲线
Figure 20. Motion simulation curve of compression wedge adjusting mechanism
图 21 喉道板调节机构运动仿真曲线
Figure 21. Motion simulation curve of throat plate regulating mechanism
表 1 进气道结构参数
Table 1. Inlet structure parameters
m 参数 数值 前压缩楔板长度 2.39 后压缩楔板长度 1.21 喉道板长度 1.20 随动板上段长度 0.30 随动板下段长度 0.20 随动板移动长度 0.07 随动板固定端距离 0.40 
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表 2 进气道高速调节规律
Table 2. High speed regulation law of inlet
工作模态编号 前压缩楔板倾角/（°） 喉道板高度/m 1 17.30 0.138 2 15.91 0.193 3 15.61 0.204 4 14.66 0.243 5 10.60 0.299
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表 3 进气道低速调节规律
Table 3. Low speed regulation law of inlet
工作模态编号 楔板倾角/（°） 前压缩 后压缩 6 10.6 24.8 7 5.7 15.3 8 2.5 9.3
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表 4 电机质量计算参数
Table 4. Motor weight calculation parameters
参数 取值 参数 取值 t1/s 0.4 ls/m 0.4 t2/s 5.2 Ds/m 0.025 t3/s 0.4 m/kg 192.4 t4/s 1 p/m 0.005 tf/s 7 F/N 75600 v/（m/s） 0.02 k 2 i 5
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表 5 驱动力计算参数
Table 5. Driving force calculation parameters
参数 数值 $F$/N 87218 ${m_{{\text{plate}}}}$/kg 24.9 ${\theta _1}$/（°） 20 ${\theta _2}$/（°） 14.7 ${l_{\text{r}}}$/m 1.4
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表 6 理想目标函数取值范围
Table 6. Value range of ideal objective function
函数 边界 JiHD JiD JiT JiU JiHD JiHU J1 50.5 51 51.5 52 52.5 53 J2 280 290 300 310 320 330 J3 0.45 0.5 0.55 0.6 0.65 0.7 注：JiHD、JiD、JiT、JiU、JiHD、JiHU分别为确定目标函数取值的边界。HD（highly desirable）, D（desirable）, T（tolerable）, U（undesirable）, HU（highly undesirable）。
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表 7 前压缩楔板调节机构优化设计方案
Table 7. Optimization design scheme of front compression wedge plate adjustment mechanism
参数 数值 连杆轴线长度lr/m 1.326 初始夹角θ1/（°） 5.3 丝杠直径Ds/m 0.030 丝杠长度ls/m 0.76 机构质量mEMA/kg 52.7 机构能耗PEMA/W 287.4 机构刚度KEMA/104 （N/m） 1.1
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表 8 后压缩楔板调节机构优化设计方案
Table 8. Optimization design scheme of back compression wedge plate adjustment mechanism
参数 数值 连杆轴线长度lr/m 0.636 初始夹角θ1/（°） 8.7 丝杠直径Ds/m 0.025 丝杠长度ls/m 0.53 机构质量mEMA/kg 31.2 机构能耗PEMA/W 198.2 机构刚度KEMA/103 （N/m） 7.58
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