剪式可展机构的结构动力学建模及实验研究
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摘要
剪式可展机构构件数目多、结构复杂,为了使其展收动作可靠、快速准确,需要对可展机构的结构动力学特性进行研究。首先将剪式单元作为子结构,运用有限元方法,建立了剪式可展机构的结构动力学模型,完成了模态计算、仿真分析,得到其固有频率与振型。然后,构建了可展机构的模态特性实验平台,设计了实验方案,完成了剪式可展机构的结构动力学性能辨识与分析。实验结果和理论计算结果能够较好地吻合,证明了有限元分析的有效性及实验方案的可行性。
Aiming at many components and complicated structure of deployable mechanism,it analyzes its structural dynamics for reliable,quick,accurate expansion and folding behavior. Taking scissor-like unit as a repeat sub-structure,it establishes the structural dynamics model of scissor-like deployable mechanism,simulates the modal,obtains the natural frequency and vibration modes. It sets the experiment platform for modal behavior test,designs the experiment scheme and realizes the modal performance identification. Comparing the experiment results with the date obtained by finite element method,the validity of finite element analysis and the feasibility of the experimental scheme are feasible.
Aiming at many components and complicated structure of deployable mechanism,it analyzes its structural dynamics for reliable,quick,accurate expansion and folding behavior. Taking scissor-like unit as a repeat sub-structure,it establishes the structural dynamics model of scissor-like deployable mechanism,simulates the modal,obtains the natural frequency and vibration modes. It sets the experiment platform for modal behavior test,designs the experiment scheme and realizes the modal performance identification. Comparing the experiment results with the date obtained by finite element method,the validity of finite element analysis and the feasibility of the experimental scheme are feasible.
引文
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[2]Northrop Grumman Corporation.ISIS telescopic mast[EB/OL].(2014-09-02).http://www.northropgrumman.com/Business Ventures/Astro Aerospace/Products/Documents/page Docs/DS-410-ISISTele Mast.pdf.
[3]ZHANG Yiqun,DUAN Baoyan,LI Tuanjie.A controlled deployment method for flexible deployable space antennas[J].Acta Astronautica,2012,81:19-29.
[4]MORTEROLLEA,MAURINB,DUBEB J F,et.al.Modal behavior of a new large reflector conceptual design[J].Aero Space Science and Technology,2015,42:74-79.
[5]李端玲.变胞机构的机构学分析及应用[D].北京:北京航空航天大学,2003.
[6]CHERNIAVSKY A G,GULYAYEV V I,GAIDAICHUK V V,et al.Large deployable space antennas based on usage of polygonal pantograph[J].Journal of Aerospace Engineering,2005,18(3):139-145.
[7]MIRA L A,COELHO R F,THRALL A P,et al.Parametric evaluation of deployable scissor arches[J].Engineering Structures,2015,99:479-491.
[8]STABILE A,LAURENZI S.Coiling dynamic analysis of thinwalled composite deployable boom[J]Composite Structures,2014,113:429-436.
[9]SKELTON Robert E,MAURICIO C de Oliveira.Optimal complexity of deployable compressive structures[J].Journal of the Franklin Institute,2010,347:228-256.
[10]杨毅,丁希仑.剪式铰单元可展结构静力学分析与拓扑优化设计[J].中国机械工程,2010,21(2):184-189.
[11]AVERSENG J,DUBEJ F.Design,analysis and self stress setting of a lightweight deployable tensegrity modular structure[J].Procedia Engineering,2012,40:14-19.
[12]孙远涛,王三民,刘霞.剪式机构线性阵列可展结构的动力学特性研究[J].中国机械工程,2012,23(24):2917-2920.
[13]LI Tuanjie,GUO Jian,CAO Yuyan.Dynamic characteristics analysis of deployable space structures considering joint clearance[J].Acta Astronautica,2011,68:974-983.
[14]刘树青,王兴松.剪式可展机构非线性动力学分析子系统方法[J].振动与冲击,2013,32(7):34-37.
[15]刘树青,王兴松,朱正龙.一种剪式可展机构设计与动力学分析[J].机械设计,2011(10):55-60.