Rigid-flexible coupling dynamics analysis based on deployable mechanism of LS-DYNA folding wing

CHEN Chao; HU Ming; ZHAO De-ming; CHEN Wen-hua; ZHOU Xu-wu

doi:10.3788/OPE.20172514.0095

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Rigid-flexible coupling dynamics analysis based on deployable mechanism of LS-DYNA folding wing

更新时间：2020-08-13

- Rigid-flexible coupling dynamics analysis based on deployable mechanism of LS-DYNA folding wing
- Optics and Precision Engineering Vol. 25, Issue 12z, Pages: 95-102(2017)
- 作者机构：
  
  浙江理工大学机电产品可靠性技术研究浙江省重点实验室,浙江杭州,310018
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20172514.0095
  CLC： TP242;TJ760.1
- Received：20 August 2017，
  
  Revised：06 September 2017，
  
  Published：31 December 2017
- 稿件说明：
移动端阅览
陈超, 胡明, 赵德明等. 基于LS-DYNA的折叠翼展开机构刚柔耦合动力学分析[J]. 光学精密工程, 2017,25(12z): 95-102

CHEN Chao, HU Ming, ZHAO De-ming etc. Rigid-flexible coupling dynamics analysis based on deployable mechanism of LS-DYNA folding wing[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 95-102
陈超, 胡明, 赵德明等. 基于LS-DYNA的折叠翼展开机构刚柔耦合动力学分析[J]. 光学精密工程, 2017,25(12z): 95-102 DOI： 10.3788/OPE.20172514.0095.

CHEN Chao, HU Ming, ZHAO De-ming etc. Rigid-flexible coupling dynamics analysis based on deployable mechanism of LS-DYNA folding wing[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 95-102 DOI： 10.3788/OPE.20172514.0095.

摘要

二次折叠翼在展开过程中的复杂刚柔耦合现象会影响展开的精度和零部件的稳定性，为确定展开机构各零部件在展开过程中的应力状态，本文基于二次折叠翼展开机构的工作原理及结构特征，利用FLUENT软件对导弹折叠翼面进行CFD仿真分析，获得翼面的气动升力系数并确定翼面气动载荷随展开时间的变化规律；采用HyperMesh软件建立展开机构刚柔耦合有限元模型，相比于刚体仿真更加有效地模拟展开过程中零部件的应力应变情况；将气动载荷等效后作用于翼面，通过仿真分析获得中翼展开角度数据及各柔性部件的最大应力云图。仿真结果表明，连杆及翼面铰接处的最大应力分别达到393 MPa和189 MPa。二次折叠翼展开机构的设计可以满足要求，并确定连杆及翼面铰接处为展开机构的危险部件（区域），为后续展开机构失效模式分析提供参考。

Abstract

The deployment accuracy and stability of components of deployable mechanism for twice folding wing were influenced by dynamic behavior which includes rigid-flexible coupling phenomenon in the deploying process. In this paper

in order to determining the stress state of each component during deploying

the lift coefficient of the wing was obtained through CFD simulation by FLUENT software and the relationship between the aerodynamic load and time was determined based on the operating principle and structure features of deployable mechanism for twice folding wing. The rigid-flexible coupling finite element model was developed by HyperMesh software which simulated the stress and strain of components more effective than rigid model. By imposing aerodynamic load which was equalized on the wings

the deployable angle date of the middle wing and the maximum stress contours were obtained through the simulation. The simulation results show that the maximum stress of the link and the area on hinge joint up to 393 MPa and 189 MPa respectively. The design of deployable mechanism for twice folding wing meets the requirements

the link and the area on hinge joint were determined as the hazardous component which offers reference to the FMEA of deployable mechanism.

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references

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