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摘要:
针对模块化可重构机翼结构的优化设计问题，以沿展向分布的3个翼段模块为研究对象，研究了不同翼展方案机翼的载荷相关性，通过在优化迭代过程中自动调整设计空间，解决了模块化可重构机翼优化设计时复杂的变量-约束耦合影响问题，建立了适用于模块化可重构机翼结构的分步补偿优化方法。以某无人机模块化可重构机翼结构优化设计问题为例，建立了优化模型，并分别采用所提分步补偿优化方法和传统单方案优化方法进行了优化设计。结果表明：所提方法能够稳定收敛，与单方案优化结果相比较，所提方法以较小的重量代价满足了3种重构方案的所有设计要求，且优化结果具有较好的工程实用性。
Abstract:For optimization of the modular reconfigurable airfoil structures, three wing modules that distributed along the span direction are taken as research object, and the correlations of load among airfoils with different wingspan are investigated. The complex coupling effects between variables and constraints are resolved by adjusting the design space during iteration automatically. A step-compensation optimization method is proposed for design of the modular reconfigurable airfoil structure. Optimization model of airfoil structures from a modular UAV is established and optimization design is conducted using both the step-compensation method and the traditional single scheme optimization method. The results show that using the proposed method can achieve steady convergence, and compared with the results from single scheme optimization method, the final design in this paper can meet all the design requirements of those three reconfiguration schemes with limited cost of weight, and keep better practicability in engineering.
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Key words:
- modular /
- reconfigurable /
- airfoil structures /
- step-compensation /
- structural optimization
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图 1 三种翼展机翼外观及尺寸
Figure 1. Appearance and dimension of airfoils with three kinds of wingspan
图 2 机翼主要结构件布置和模块划分
Figure 2. Airfoil's main structural component layout and module partition
图 3 考虑载荷相关性的模块化可重构机翼结构补偿优化流程
Figure 3. Modular reconfigurable airfoil's structure compensation optimization flow considering load correlation
表 1 无人机3种重构方案总体设计参数
Table 1. General design parameters of three UAV reconfiguration schemes
飞机参数 重构方案1 重构方案2 重构方案3 起飞重量/kg 680 625 600 实用升限/m 8 000 6 500 5 000 机翼面积/m2 7.5 6.1 5 机翼翼展/m 11 8 6 最大正过载 3.8 3.5 4.5 最大负过载 -2.5 -2.7 -3.5 安全系数 1.3 1.3 1.3 
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表 2 符号及定义
Table 2. Definition of symbols
符号 定义 V1 模块1的结构设计变量 V2 模块2的结构设计变量 V3 模块3的结构设计变量 CON1 机翼重构方案1的约束条件 CON2 机翼重构方案2的约束条件 CON3 机翼重构方案3的约束条件 W1 模块1的重量 W2 模块2的重量 W3 模块3的重量 LC1 机翼重构方案1对应的工况 LC2 机翼重构方案2对应的工况 LC3 机翼重构方案3对应的工况
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表 3 优化目标结果统计
Table 3. Optimization objective result statistics
模块编号 本文方法模块重量/
kg单方案优化重构方案1 单方案优化重构方案2 单方案优化重构方案3 模块重量/kg 比率/
%模块重量/kg 比率
/%模块重量/kg 比率
/%1 49.03 47.16 3.81 46.65 4.85 46.73 4.69 2 8.94 8.33 6.82 7.90 11.63 — — 3 6.64 6.64 0 — — — —
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表 4 模块1上蒙皮厚度设计变量优化结果统计
Table 4. Optimization result statistics of thickness design variables belonging to top skin of Module 1
变量编号 上蒙皮厚度设计变量值/mm 本文方法 单方案优化重构方案1 单方案优化重构方案2 单方案优化重构方案3 TU1 4.22 4.13 4.26 4.05 TU2 4.71 4.66 4.58 4.61 TU3 4.14 3.91 4.11 4.06 TU4 3.75 3.65 3.55 3.71 TU5 3.81 3.77 3.71 3.77 TU6 3.45 3.22 3.42 3.44 TU7 2.84 2.64 2.62 2.71 TU8 3.16 3.04 2.94 2.85 TU9 2.55 2.55 2.45 2.46 TU10 2.54 2.34 2.42 2.34 TU11 2.73 2.62 2.52 2.42 TU12 2.41 2.31 2.38 2.31 TU13 2.31 2.24 2.14 2.05 TU14 2.70 2.56 2.46 2.17 TU15 2.30 2.26 2.23 2.04
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[1] BROWN R B.Low cost innovative design for new commercial transport family: AIAA-2002-5830[R].Reston: AIAA, 2002. [2] FUNK J E, HARBER J R, MORIN L.Future military common aircraft development opportunities: AIAA-2006-1514[R].Reston: AIAA, 2006. [3] DE WECK O L, NADIR W D, WONG J G, et al.Modular structures for manned space exploration: The truncated octahedron as a building block: AIAA-2005-2764[R].Reston: AIAA, 2005. [4] SIMPSON T W.Product platform design and customization:Status and promise[J].Artificial Intelligence for Engineering Design, Analysis and Manufacturing, 2004, 18(1):3-20. doi: 10.1017/S0890060404040028 [5] 雍明培, 余雄庆.一种面向飞机族的结构优化方法[J].航空学报, 2008, 29(3):664-669. doi: 10.3321/j.issn:1000-6893.2008.03.021YONG M P, YU X Q.A structural optimization method for aircraft family[J].Acta Aeronautica et Astronautica Sinica, 2008, 29(3):664-669(in Chinese). doi: 10.3321/j.issn:1000-6893.2008.03.021 [6] ALLISON J, ROTH B, KOKKOLARAS M, et al.Aircraft family design using decomposition-based method: AIAA-2006-6950[R].Reston: AIAA, 2006. [7] WILLCOX K, WAKAYAMA S.Simultaneous optimization of a multiple-aircraft family[J].Journal of Aircraft, 2003, 41(4):616-622. https://www.researchgate.net/publication/228599736_Simultaneous_Optimization_of_a_Multiple-Aircraft_Family [8] 李苏杭.飞机模块化结构优化设计的满约束并行优化方法[D].南京: 南京航空航天大学, 2014. http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=D672751LI S H.Full-constraint parallel optimization method for aircraft modular structure design[D].Nanjing: Nanjing University of Aeronautics and Astronautics, 2014(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=degree&id=D672751 [9] BEVILAQUA P M.Future applications of the JSF variable propulsion cycle: AIAA-2003-2614[R].Reston: AIAA, 2003. [10] FULLER J.The role of manned aircraft in the future: AIAA-2003-2860[R].Reston: AIAA, 2003. [11] PATE D J, PATTERSON M D, GERMAN B J.Optimizing families of reconfigurable aircraft for multiple missions[J].Journal of Aircraft, 2012, 49(6):1988-2000. doi: 10.2514/1.C031667 [12] CETIN O L, SAITOU K.Decomposition-based assembly synthesis for structural modularity[J].Journal of Mechanical Design, 2004, 126(2):234-243. doi: 10.1115/1.1666890 [13] SOUMA C, VICTOR M, WEI Y T, et al.New modular product platform planning approach to design macroscale reconfigurable unmanned aerial vehicles[J].Journal of Aircraft, 2016, 53(2):309-322. doi: 10.2514/1.C033262 [14] 张立丰, 姚卫星, 邹君.模块化飞机结构优化设计的等效多工况法[J].航空学报, 2015, 36(3):834-839. http://d.old.wanfangdata.com.cn/Periodical/hkxb201503015ZHANG L F, YAO W X, ZOU J.Equivalent multi-case optimization architecture for modular aircraft structures[J].Acta Aeronautica et Astronautica Sinica, 2015, 36(3):834-839(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkxb201503015 [15] 范林, 王哲.模块化技术在飞机研制中的应用[J].航空科学技术, 2010(3):19-21. doi: 10.3969/j.issn.1007-5453.2010.03.007FAN L, WANG Z.Application of modularization technology at each development stage of aircraft[J].Aeronautical Science & Technology, 2010(3):19-21(in Chinese). doi: 10.3969/j.issn.1007-5453.2010.03.007 [16] 董云峰, 卫晓娜, 郝朝.引入多Agent协商的协同优化在卫星设计中的应用[J], 北京航空航天大学学报, 2016, 42(5):1055-1064. http://bhxb.buaa.edu.cn/CN/abstract/abstract13744.shtmlDONG Y F, WEI X N, HAO Z.A multi-Agent negotiation based collaborative optimization application in satellite design[J].Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(5):1055-1064(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract13744.shtml [17] 马树微, 李静琳, 陈曦, 等.多级固体运载火箭分级多学科设计优化[J].北京航空航天大学学报, 2016, 42(3):542-550. http://bhxb.buaa.edu.cn/CN/abstract/abstract13387.shtmlMA S W, LI J L, CHEN X, et al.Stage-wise multidisciplinary design optimization for multi-stage solid launch vehicle[J].Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(3):542-550(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract13387.shtml -
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