多相材料机翼前缘柔性机构拓扑优化设计
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摘要
为了实现机翼前缘连续变形及结构轻量化,利用多相材料进行了柔性机翼前缘结构的设计。在轮换主动相变量算法的基础上,以选定前缘初始曲线上9个坐标点的实际位移和目标位移的偏差为目标函数,各相材料的体积分数作为约束,建立多相材料柔性机构拓扑优化模型,采用OC优化准则法进行求解。编写MATLAB程序,计算得到了清晰的两相实体材料前缘结构优化结果。利用CATIA软件对优化结果进行几何模型重构,并将重构后的模型导入HyperWorks软件进行仿真分析,结果表明多相材料机翼前缘柔性机构能够实现最大9.1°的连续偏转。
The multi-phase materials are introduced into the design of the compliant wing's leading edge,for the sake of its continuous deformation and structural lightweight,By means of the alternating active phase-variable algorithm,the topology optimization model of the compliant mechanism is set up,with the deviation between the actual displacement and the target displacement of the nine coordinate points on the selected initial curve as the objective function,and the volume ratios of these materials as the constraint. Then,the model is solved by the OC optimization criterion method. A distinct topology image of the compliant wing's leading edge with two-phase solid materials is obtained by the MATLAB code. The CATIA software is applied to geometrically reconstruct the optimization results,and then the reconstructed model is imported into the HyperWorks software for simulation analysis. The results show that the compliant wing's leading edge based on the multi-phase materials ensures the maximum deflection of 9.1°.
The multi-phase materials are introduced into the design of the compliant wing's leading edge,for the sake of its continuous deformation and structural lightweight,By means of the alternating active phase-variable algorithm,the topology optimization model of the compliant mechanism is set up,with the deviation between the actual displacement and the target displacement of the nine coordinate points on the selected initial curve as the objective function,and the volume ratios of these materials as the constraint. Then,the model is solved by the OC optimization criterion method. A distinct topology image of the compliant wing's leading edge with two-phase solid materials is obtained by the MATLAB code. The CATIA software is applied to geometrically reconstruct the optimization results,and then the reconstructed model is imported into the HyperWorks software for simulation analysis. The results show that the compliant wing's leading edge based on the multi-phase materials ensures the maximum deflection of 9.1°.
引文
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[14] Zuo W,Saitou K. Multi-material topology optimization using ordered SIMP interpolation[J]. Structural&Multidisciplinary Optimization,2017,55(2):477-491.
[15] Tavakoli R,Mohseni S M. Alternating active-phase algorithm for multimaterial topology optimization problems:a 115-line MATLAB implementation[J]. Structural&Multidisciplinary Optimization,2013,49(4):621-642.
[16] Park J,Sutradhar A. A multi-resolution method for 3D multimaterial topology optimization[J]. Computer Methods in Applied Mechanics&Engineering,2015,285(2):571-586.
[17] Tong X X,Ge W J,Sun C et al. Topology optimization of compliant adaptive wing leading edge with composite materials[J]. Chinese Journal of Aeronautics,2014,27(6):1488-1494.
[18] Sigmund O.A 99 line topology optimization code written in Matlab[J]. Structural&Multidisciplinary Optimization,2001,21(2):120-127.
[19] Andreassen E,Clausen A,Schevenels M,et al. Efficient topology optimization in MATLAB using 88 lines of code[J]. Structural&Multidisciplinary Optimization,2011,43(1):1-16.
[20] Podugu P,Ananthasuresh G K. Topology optimization-based design of a compliant aircraft wing for morphing leading and trailing edges[J]. American Society of Mechanical Engineers,2010,21(6):732-738.
[21]占金青,卢清华,张宪民.多相材料的连续体结构拓扑优化设计[J].中国机械工程,2013,24(20):2764-2768.
[2]杨智春,解江.柔性后缘自适应机翼的概念设计[J].航空学报,2009,30(6):1028-1034.
[3] Kota S. Shape control of adaptive structures using compliant mechanisms[R]. Stand From 298(Rev.2-89),Prescribed by ANSI std. Z39. 18,2000:1-7.
[4] Matthew G. Development of a variable camber compliant aircraft tail using structural optimization[D]. Blacksburg:Virginia Polytechnic Institute and State University,2003.
[5] Lu K J,Kota S. An effective method of synthesizing compliant adaptive structures using load path representation[J].Journal of Intelligent Material Systems&Structures,2005,16(4):307-317.
[6]景藜,张永红,葛文杰,等.基于载荷路径法的柔性机翼前缘拓扑优化[J].机械设计,2011,28(1):85-89.
[7]黄杰,葛文杰,杨方.实现机翼前缘形状连续变化柔性机构的拓扑优化[J].航空学报,2007,28(4):988-992.
[8]赵飞,葛文杰,张龙.某无人机柔性机翼后缘变形机构的拓扑优化[J].机械设计,2009,26(8):19-22.
[9]葛文杰,朱鹏刚,刘世丽,等.基于柔性机构的机翼前缘变形多目标优化[J].西北工业大学学报,2010,28(2):211-217.
[10] Thomsen J. Topology optimization of structures composed of one or two materials[J]. Journal of Structural Optimization,1992,5(1/2):108-115.
[11] Zhou S,Wang M Y. Multimaterial structural topology optimization with a generalized Cahn-Hilliard model of multiphase transition[J]. Structural&Multidisciplinary Optimization,2007,33(2):89-111.
[12] Wang M Y,Zhou S W. Synthesis of shape and topology of multi-material structures with a phase-field method[J]. Scientific Modeling and Simulation SMNS,2004,11(2):117-138.
[13] Yin L,Ananthasuresh G K. Topology optimization of compliant mechanisms with multiple materials using a peak function material interpolation scheme[J]. Structural&Multidisciplinary Optimization,2001,23(1):49-62.
[14] Zuo W,Saitou K. Multi-material topology optimization using ordered SIMP interpolation[J]. Structural&Multidisciplinary Optimization,2017,55(2):477-491.
[15] Tavakoli R,Mohseni S M. Alternating active-phase algorithm for multimaterial topology optimization problems:a 115-line MATLAB implementation[J]. Structural&Multidisciplinary Optimization,2013,49(4):621-642.
[16] Park J,Sutradhar A. A multi-resolution method for 3D multimaterial topology optimization[J]. Computer Methods in Applied Mechanics&Engineering,2015,285(2):571-586.
[17] Tong X X,Ge W J,Sun C et al. Topology optimization of compliant adaptive wing leading edge with composite materials[J]. Chinese Journal of Aeronautics,2014,27(6):1488-1494.
[18] Sigmund O.A 99 line topology optimization code written in Matlab[J]. Structural&Multidisciplinary Optimization,2001,21(2):120-127.
[19] Andreassen E,Clausen A,Schevenels M,et al. Efficient topology optimization in MATLAB using 88 lines of code[J]. Structural&Multidisciplinary Optimization,2011,43(1):1-16.
[20] Podugu P,Ananthasuresh G K. Topology optimization-based design of a compliant aircraft wing for morphing leading and trailing edges[J]. American Society of Mechanical Engineers,2010,21(6):732-738.
[21]占金青,卢清华,张宪民.多相材料的连续体结构拓扑优化设计[J].中国机械工程,2013,24(20):2764-2768.