Assembly Error Modeling and Sensitivity Analysis for Spatial Deployable Mechanisms with Structural Equivalent Transformation

doi:10.7652/xjtuxb201904003

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Assembly Error Modeling and Sensitivity Analysis for Spatial Deployable Mechanisms with Structural Equivalent Transformation

更新时间：2025-07-09

- Assembly Error Modeling and Sensitivity Analysis for Spatial Deployable Mechanisms with Structural Equivalent Transformation
- Vol. 53, Issue 4, Pages: 15-23(2019)
- 作者机构：
  
  西安交通大学现代设计及转子轴承系统教育部重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201904003
  CLC： TH182
- Online First：10 April 2019，
  
  Published：2019
- 稿件说明：
移动端阅览
Assembly Error Modeling and Sensitivity Analysis for Spatial Deployable Mechanisms with Structural Equivalent Transformation[J]. 2019, 53(4): 15-23.
DOI：

Assembly Error Modeling and Sensitivity Analysis for Spatial Deployable Mechanisms with Structural Equivalent Transformation[J]. 2019, 53(4): 15-23. DOI： 10.7652/xjtuxb201904003.

摘要

为解决空间可展机构装配过程中无法对杆件进行精准定量调整的难题

针对杆件耦合与环约束复杂等特点

提出了一种空间可展机构装配误差建模与灵敏度分析的方法。首先

通过结构等效转换将空间可展机构分为两部分

并分别基于闭环矢量与虚位移法

推导出上述两部分的几何精度模型

然后利用线性叠加

建立了空间可展机构整体装配误差模型。在此基础上

运用偏微分法完成了空间可展机构误差灵敏度分析

实现了关键误差源识别。最后

以星载SAR卫星天线空间可展机构为数值算例进行了计算

结果表明:在杆长误差和铰链安装位置误差范围相同的情况下

单独调整支撑杆件能更好地满足装配精度要求

且星体连接杆尺寸误差对天线面板指向精度的影响尤为显著。

Abstract

The precise and quantitative link adjustment of the spatial deployable mechanism cannot be implemented in the assembly shop nowadays. Considering the characteristics like coupled links and complex loop constraints

an approach of assembly error modeling is proposed and the corresponding sensitivity analysis is carried out. The spatial deployable mechanism is divided into two parts via structural equivalent transformation

and the geometric accuracy models of these two parts are established with the methods of closed-loop vector and virtual displacement respectively. Then the whole assembly accuracy model of the spatial deployable mechanism is derived from the linear superposition

and the error sensitivity is analyzed with partial differential method to accordingly identify the key error source. A spatial deployable mechanism of space borne SAR antenna is taken as a numerical example. If link length deviations and assembly position misalignments of joints are in the same range respectively

it indicates that merely adjusting the support links can better meet the requirement of assembly accuracy

and the link connected with payload module has a particularly significant impact on the pointing accuracy of antenna panels.

关键词

Keywords

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