Wing Design and Adaptive Optimization of a Compound Drone
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摘要: 随着人类社会的进步和城市物流的兴起, 以复合式无人机为代表的无人机技术进入了快速发展阶段。在复合式无人机的研制周期中, 气动优化设计选型扮演着非常重要的角色。针对基于代理模型的气动优化技术, 对其关键参数自适应筛选和设计空间自适应更新进行了研究, 形成了参数/空间自适应气动寻优平台, 有效提高了气动优化过程中的寻优效率和搜索能力。针对一款复合式无人机提出机翼初步设计方案, 并对其进行自适应气动寻优。优化翼根、翼梢翼型及由此生成的优化三维机翼在设计升力系数为1.0时的升阻比均提高5%以上, 且对应迎角均减小2°以上。无人机机翼失速特性及滚转操控能力均得到有效提升。Abstract: With the growing demand for unmanned transportation, the rise of compound drones is imperative. Aerodynamic optimization design plays a significant role in the development cycle of compound drones. Researches were performed on key parameter adaptive screening and design space adaptive updating of surrogate-based aerodynamic optimization techniques. A parametric/spatial adaptive aerodynamic optimization platform was established, which can improve the optimization efficiency and search capability effectively in the process of aerodynamic optimization. A preliminary design scheme of wing for a compound drone was presented, and adaptive aerodynamic optimization was carried out. The lift-to-drag ratios of the optimized wing root and tip airfoils and the resulting optimized wing were all increased by over 5%, with design lift coefficients equaling to 1.0, and the corresponding angles of attack were also reduced by more than 2°. The stall characteristics and the roll control ability of the wing were improved simultaneously.
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Key words:
- compound drones /
- wing design /
- adaptive optimization /
- parameter screening /
- space updating
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表 1 无人机设计参数
Table 1. Conceptual design parameters of a drone
design parameter value maximum take-off weight/kg 500 wing area/m2 7.5 cruising altitude/m 1 000 cruising speed/(km/h) 130 表 2 无人机机翼设计参数
Table 2. Wing geometry design parameters of a drone
design parameter value wing area/m2 7.5 wing span/m 10 aspect ratio 13.33 taper ratio 0.5 mean aerodynamic chord/m 0.777 angle of sweepback at trailing edge/(°) 0 dihedral angle/(°) 0 表 3 方差分析表
Table 3. Variance analysis
source S df MS F value P value A SA dfA MSA FA PA B SB dfB MSB FB PB … … … … … … error SE dfE MSE total ST dfT 表 4 参数空间更新伪代码
Table 4. Pseudo-code of parameter space updating
Input: original parameter space[xil, old, xiu, old]k,temporary optimal points(x1, opt, x2, opt, …, xk, opt) Process: 1. For i=1, 2, …, k Do: 2. If xi, opt -xil, old ≤ 0.1|xiu, old-xil, old | Then 3. xil, new=(3xil, old-xiu, old)/2, xiu, new=(xil, old+ xiu, old)/2; 4. Else if xiu, old-xi, opt≤ 0.1|xiu, old-xil, old | Then 5. xil, new=(xil, old+ xiu, old)/2, xiu, new=(-xil, old+3xiu, old)/2; 6. Else 7. xil, new=xil, old, xiu, new=xiu, old; 8. End if 9. End for Output: new parameter space[xil, new-xiu, new]k 表 5 网格无关性验证参数
Table 5. Parameters of mesh independence verification
mesh parameter coarse mesh middle mesh dense mesh chord point number 81 121 161 y+ 5.0 1.0 0.5 total mesh number 24 764 36 844 48 924 表 6 计算工况
Table 6. Calculation conditions
H/m V/(km/h) 1 000 130 表 7 翼根翼型设计升阻比的方差分析表
Table 7. Variance analysis of design lift-to-drag ratio of root airfoil
source S df MS F value P value U1, root 14.19 1 14.19 152.00 25.77 U2, root 17.88 1 17.88 191.56 32.47 U3, root 0.95 1 0.95 10.20 1.73 U4, root 0.06 1 0.06 0.62 0.11 U5, root 0.00 1 0.00 0.01 0.00 U6, root 1.03 1 1.03 11.02 1.87 U7, root 1.01 1 1.01 10.81 1.83 L1, root 2.22 1 2.22 23.80 4.03 L2, root 0.73 1 0.73 7.82 1.33 L3, root 6.95 1 6.95 74.49 12.62 L4, root 0.16 1 0.16 1.74 0.29 L5, root 5.86 1 5.86 62.74 10.64 L6, root 0.48 1 0.48 5.13 0.87 L7, root 1.96 1 1.96 21.03 3.56 error 1.59 17 0.09 2.89 total 55.07 31 100.00 表 8 关键参数筛选结果
Table 8. Screening results of key parameters
root design parameters tip design parameters U1, root U2, root U3, root U4, root U1, tip U2, tip U3, tip U4, tip U5, root U6, root U7, root U5, tip U6, tip U7, tip L1, root L2, root L3, root L4, root L1, tip L2, tip L3, tip L4, tip L5, root L6, root L7, root L5, tip L6, tip L7, tip 表 9 翼根翼型参数空间变化情况
Table 9. Parameter space variation of wing root airfoil
parameter original space latest space optimal lower upper lower upper L1, root -0.26 -0.2 -0.14 -0.08 -0.091 L3, root -3.9 -2.9 -1.9 -0.9 -1.404 4 L5, root -3.9 -2.9 -0.9 0.1 -0.001 2 L7, root 0.1 0.13 0.16 0.19 0.184 U1, root 0.23 0.31 0.19 0.27 0.193 6 U2, root 1.8 2.4 1.8 2.4 2.17 U3, root 2.3 3.1 3.5 4.3 4.27 U4, root 5.9 7.9 5.9 7.9 6.03 U6, root 1.4 1.8 3.0 3.4 3.13 表 10 优化翼型气动性能变化情况
Table 10. Aerodynamic performance variation of optimal airfoils
aerodynamic performance original optimal variation root airfoils KCL=1, root 64.83 70.11 +8.14% αCL=1, root 5.38° 3.12° -2.26° αstall, root 14.5° 14.5° +0.0° θstall 0.159 8 0.140 4 -0.019 4 tip airfoils KCL=1, tip 62.61 67.17 +7.28% αCL=1, tip 4.83° 1.93° -2.90° αstall, tip 14.5° 13.0° -1.5° θtip 0.122 0 0.109 9 -0.012 1 -
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