航天用大展收比豆荚结构变形规律模型及其仿真验证

Deformation Law Model and Simulation Verification of Pod Structures with Large Exhibition-to-receive Ratio for Aerospace Applications

豆荚结构又称可盘卷管状伸展臂,是一种具有大展收比的弹性伸展结构,可以被压缩成板状装载在航天器上,需要时自行展开为空心筒,用于展开太阳翼、卫星天线等组件,能够缩小航天器发射时的体积。设计豆荚结构尺寸时需要考虑其力学性能。针对豆荚结构收纳过程中力学特性影响因素变化多、计算量大等问题,利用力学分析设计了一种数值模型,可以计算不同尺寸参数的豆荚结构整个压缩过程中的压缩力变化。利用有限元分析软件ABAQUS对压缩变形进行仿真分析,对比数值模型的计算结果与仿真结果误差小于10%。通过数值模型分析得到了豆荚结构尺寸参数对压缩力的影响。

The pod rod,also named as CTM(collapsible tubular mast),was an elastic stretching structure with large exhibition-to-receive ratio.It might be compressed into a plate and loaded on the spacecraft and self-deployed into a hollow cylinder when needed,which might be used to expand solar wings,satellite antennas and other components,and might reduce the volume of spacecraft during launch.The mechanics properties of pod structure should be considered when designing the structure size.A numerical model was established by means of mechanics analysis in order to solve the problems of large amount of calculation,and frequent variation of the factors that affecting mechanics properties.The numerical model might be applied to calculate the compressive force variation during the entire compression processes for the pod structure with different size parameters.The finite element analysis software ABAQUS was used to simulate and analyze the compression deformation.The deviations between the calculation results and the simulation ones are less than 10%.The influences of size parameters of the pod structure on the compressive force were obtained through numerical model analyses.