Research on Digital Assembly Attitude Adjustment Algorithm for Flexible Thin-Walled Large Parts

LI Shujun; LUO Hao; PANG Fangxin; ZHAO Wei; FENG Pujia

doi:10.16080/j.issn1671–833x.2019.08.038

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Research on Digital Assembly Attitude Adjustment Algorithm for Flexible Thin-Walled Large Parts

更新时间：2025-10-30

- Research on Digital Assembly Attitude Adjustment Algorithm for Flexible Thin-Walled Large Parts
- Aeronautical Manufacturing Technology Vol. 62, Issue 8, Pages: 38-43(2019)
- 作者机构：
  
  1. 西北工业大学机电学院,西安,710072
  2. 陕西省凯盛航空装备制造有限公司,汉中,723200
  3. 航空工业陕西飞机工业( 集团) 有限公司部装分厂,汉中,723200
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671–833x.2019.08.038
  CLC：
- Published：2019
- 稿件说明：
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李树军，罗浩，庞放心，赵伟，封璞加. 柔性薄壁大部件数字化装配调姿算法研究[J]. 航空制造技术, 2019, 62(8): 38-43.

LI Shujun, LUO Hao, PANG Fangxin, ZHAO Wei, FENG Pujia. Research on Digital Assembly Attitude Adjustment Algorithm for Flexible Thin-Walled Large Parts. Aeronautical Manufacturing Technology, 2019, 62(8): 38-43.
李树军，罗浩，庞放心，赵伟，封璞加. 柔性薄壁大部件数字化装配调姿算法研究[J]. 航空制造技术, 2019, 62(8): 38-43. DOI： 10.16080/j.issn1671–833x.2019.08.038.

LI Shujun, LUO Hao, PANG Fangxin, ZHAO Wei, FENG Pujia. Research on Digital Assembly Attitude Adjustment Algorithm for Flexible Thin-Walled Large Parts. Aeronautical Manufacturing Technology, 2019, 62(8): 38-43. DOI： 10.16080/j.issn1671–833x.2019.08.038.

摘要

采用定位器托架混合调姿定位平台，提出了一种飞机薄壁柔性大部件数字化调姿方法。首先，采用奇异值分解法（SVD）计算机翼位姿，通过运动学逆解得到定位器各轴的运动状态。其次，根据飞机大部件易变形的特点，提出了一种消除位姿计算误差的建立飞机部件坐标系的方法，实现快速高精度调姿。最后，将该方法应用于飞机机翼的调姿，经测量调姿精度满足装配要求。

Abstract

A locator bracket hybrid attitude positioning platform is adopted

and a digital positioning method for aircraft thin-walled flexible large parts is proposed. Firstly

the singular value decomposition (SVD) computer wing pose is used to obtain the motion state of each axis of the positioner through kinematic inverse solution. Secondly

according to the characteristics of the large deformation of the aircraft

a method for establishing the coordinate system of the aircraft components to eliminate the pose error is proposed to achieve fast and high-precision attitude adjustment. Finally

the method is applied to the attitude of the aircraft wing

and the measured attitude accuracy meets the assembly requirements.

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