基于脉冲子结构的探测器结构动力学优化设计
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摘要
针对传统结构优化设计中,精细化模型求解复杂结构动响应过于耗时的问题,引入保精度、高效的脉冲子结构方法,提出一种考虑结构动力学响应的优化设计流程,并对月球探测器太阳翼结构进行优化分析,获得了太阳翼结构设计参数,有效地提高了太阳翼动力学特性指标,改善了月球探测器关键位置处的动力学环境。结果表明,脉冲子结构方法可以有效应用于航天器结构动力学优化设计,提高优化设计效率,所得优化结果对实际结构设计具有一定指导意义。
To overcome the shortcomings of using the time-consuming refined model in the dynamic optimum design of the complex structures, the efficient and accurate dynamic responses prediction method named the impulse based substructuring( IBS) method is introduced. Meanwhile,a dynamic optimum design process considering the structural dynamic responses is proposed and the structure of the solar wings of a lunar lander is optimized. After the optimum design process,the structural design parameters of the solar wings are obtained. The dynamic performance of the solar wings and the dynamics environment of the critical locations of the lunar lander are improved. The results indicate that the IBS method can be applied in the optimum design of a spacecraft to improve the dynamic analysis efficiency. This research provides a theoretical basis and technical support for practical structural design.
To overcome the shortcomings of using the time-consuming refined model in the dynamic optimum design of the complex structures, the efficient and accurate dynamic responses prediction method named the impulse based substructuring( IBS) method is introduced. Meanwhile,a dynamic optimum design process considering the structural dynamic responses is proposed and the structure of the solar wings of a lunar lander is optimized. After the optimum design process,the structural design parameters of the solar wings are obtained. The dynamic performance of the solar wings and the dynamics environment of the critical locations of the lunar lander are improved. The results indicate that the IBS method can be applied in the optimum design of a spacecraft to improve the dynamic analysis efficiency. This research provides a theoretical basis and technical support for practical structural design.
引文
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[16]董威利,刘莉,周思达,等.月球探测器软着陆动力学及影响因素分析[J].宇航学报,2014,35(04):388-396.[Dong Wei-Li,Liu Li,Zhou Si-da,et al.Analysis on soft-landing dynamics and influence factors of lunar lander[J].Journal of Astronautics,2014,35(04):388-396.]
[17]Zhou S D,Liu L,Dong W L.Time-domain substructure synthesis with hybrid rigid and nonlinear-elastic joints[J].AIAA Journal,2016,54(08):2545-2551.
[18]赵俊锋,刘莉,周思达,等.月球探测器软着陆冲击力学环境研究[J].振动与冲击,2012,31(03):37-42.[Zhao Junfeng,Liu Li,Zhou Si-da,et al.Dynamic environment research for soft landing for lunar lander[J].Journal of Shock and Vibration,2012,31(03):37-42.]
[19]孔菲.重复折展锁解式太阳翼机构设计及其性能测试[D].浙江:浙江理工大学,2014.[Kong Fei.Design and performance test on repeated fold-unfold and lock-unlock solar arravy[D].Zhejiang:Zhejiang Sci-Tech University,2014.]
[2]马兴瑞.卫星与运载火箭力学环境分析方法及试验技术[M].北京:科学出版社,2014.
[3]Nohmi M,Miyahara A.Modeling for lunar lander by mechanical dynamics software[C].AIAA Modeling and Simulation Techmologies Conference and Exhibit,San Francisco,California,August 15-18,2005.
[4]朱汪,杨建中.月球探测器软着陆机构着陆腿模型与仿真分析[J].宇航学报,2008,29(06):1723-1728.[Zhu Wang,Yang Jian-zhong.Modeling and simulation of landing leg for the lunar landing gear system[J].Journal of Astronautics,2008,29(06):1723-1728.]
[5]万峻麟,聂宏,陈金宝,等.月球着陆器有效载荷着陆冲击响应分析[J].宇航学报,2010,31(11):2456-2464.[Wan Jun-lin,Nie Hong,Chen Jin-bao,et al.Impact response analysis of payloads of lunar lander for lunar landing[J].Journal of Astronautics,2010,31(11):2456-2464.]
[6]董威利,刘莉,周思达.月球探测器加速度响应预测的时域子结构方法[J].航空学报,2015,36(03):848-856.[Dong Wei-li,Liu Li,Zhou Si-da.Acceleration response prediction for lunar lander using time-domain substructure methods[J].Acta Aeronuatica et Astronautica Sinica,2015,36(03):848-856.]
[7]肖岩,叶东,孙兆伟.面向刚柔耦合卫星的有限时间输出反馈姿态控制[J].宇航学报,2017,38(05):516-525.[Xiao Yan,Ye Dong,Sun Zhao-wei.Finite-time output feedback attitude control for rigid-flexible coupling satellites[J].Journal of Astronautics,2017,38(05):516-525.]
[8]刘汉武,张华,王金童,等.考虑柔性多体特征的复杂航天器分离动力学仿真分析[J].宇航学报,2017,38(04):352-358.[Liu Han-wu,Zhang Hua,Wang Jin-tong,et al.Simulation analysis of complex spacecraft separation dynamics considering characteristics of flexible multi-body[J].Journal of Astronautics,2017,38(04):352-358.]
[9]Wamsler M.On the selection of the mode cut-off number in component mode reduction[J].Engineering with Computers,2008,25(02):139-146.
[10]董威利.月球探测器软着陆动力学分析及动态子结构技术研究[D].北京:北京理工大学,2015.[Dong Wei-li.A study on soft-landing dynamics and dynamic substructuring techniques for lunar probe[D].Beijing:Beijing Institute of Technology,2015.]
[11]Rixen D J.Substructuring using impulse response functions for impact analysis[C].Proceedings of the IMAC-XXVIII,Jacksonville,Florida,USA,February 1-4,2010.
[12]Dong W L,Liu L,Zhou S D,et al.Substructure synthesis in time domain with rigid-elastic hybrid joints[J].AIAA Journal,2015,53(02):504-509.
[13]Van Der Valk P L C,Rixen D J.An impulse based substructuring method for coupling impulse response functions and finite element models[J].Computer Methods In Applied Mechanics And Engineering,2014,275(05):113-137
[14]Chen S L,Liu L,Zhou S D,et al.Multi-domain substructures synthesis with general joints for the dynamics of large structures[J].AIP Advances,2017,7(10):105007.
[15]刘莉,陈树霖,周思达,等.脉冲子结构与有限元刚-弹混合连接的子结构方法研究[J].航空学报,2015,36(08):2670-2680.[Liu Li,Chen Shu-lin,Zhou Si-da,et al.A substructure method for coupling impulse response functions with finite element models via rigid-elastic joints[J].Acta Aeronuatica et Astronautica Sinica,2015,36(08):2670-2680.]
[16]董威利,刘莉,周思达,等.月球探测器软着陆动力学及影响因素分析[J].宇航学报,2014,35(04):388-396.[Dong Wei-Li,Liu Li,Zhou Si-da,et al.Analysis on soft-landing dynamics and influence factors of lunar lander[J].Journal of Astronautics,2014,35(04):388-396.]
[17]Zhou S D,Liu L,Dong W L.Time-domain substructure synthesis with hybrid rigid and nonlinear-elastic joints[J].AIAA Journal,2016,54(08):2545-2551.
[18]赵俊锋,刘莉,周思达,等.月球探测器软着陆冲击力学环境研究[J].振动与冲击,2012,31(03):37-42.[Zhao Junfeng,Liu Li,Zhou Si-da,et al.Dynamic environment research for soft landing for lunar lander[J].Journal of Shock and Vibration,2012,31(03):37-42.]
[19]孔菲.重复折展锁解式太阳翼机构设计及其性能测试[D].浙江:浙江理工大学,2014.[Kong Fei.Design and performance test on repeated fold-unfold and lock-unlock solar arravy[D].Zhejiang:Zhejiang Sci-Tech University,2014.]