Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm

LI Xining; WANG Yueshun; LI Yuhua; WANG Shouchuan

doi:10.16080/j.issn1671–833x.2019.01/02.082

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Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm

更新时间：2025-10-30

- Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm
- Aeronautical Manufacturing Technology Vol. 62, Issue 1/2, (2019)
- 作者机构：
  
  1. 西北工业大学机电学院现代设计与集成制造技术教育部重点实验室,西安,710072
  2. 中航飞机技术装备设计所,西安,710089
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671–833x.2019.01/02.082
  CLC：
- Published：2019
- 稿件说明：
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李西宁, 王悦舜, 李玉华, 王守川. 基于遗传算法的飞机弱刚性件夹持方案优化设计[J]. 航空制造技术, 2019, 62(1/2): 82-86. LI Xining, WANG Yueshun, LI Yuhua, WANG Shouchuan. Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm. Aeronautical Manufacturing Technology, 2019, 62(1/2): 82-86.

LI Xining, WANG Yueshun, LI Yuhua, et al. Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm[J]. Aeronautical Manufacturing Technology, 2019, 62(1/2).
李西宁, 王悦舜, 李玉华, 王守川. 基于遗传算法的飞机弱刚性件夹持方案优化设计[J]. 航空制造技术, 2019, 62(1/2): 82-86. LI Xining, WANG Yueshun, LI Yuhua, WANG Shouchuan. Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm. Aeronautical Manufacturing Technology, 2019, 62(1/2): 82-86. DOI： 10.16080/j.issn1671–833x.2019.01/02.082.

LI Xining, WANG Yueshun, LI Yuhua, et al. Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm[J]. Aeronautical Manufacturing Technology, 2019, 62(1/2). DOI： 10.16080/j.issn1671–833x.2019.01/02.082.

摘要

针对飞机装配过程中零件刚度弱、易变形的特点，提出了一种基于遗传算法的飞机弱刚性薄壁件夹持方案优化方法。该方法以自重等外载引起的薄壁件最大变形量最小为目标，建立夹持布局和夹紧顺序同步优化模型，通过有限元仿真获得夹持方案下薄壁件最大变形量，利用遗传算法和有限元批处理技术实现优化模型求解。以飞机典型零件长桁为例，验证了该方法的可行性和有效性。

Abstract

In view of the characteristics of weak rigidity and easy deformation of parts during aircraft assembly process

an optimization method based on genetic algorithm for the clamping scheme of the weak rigid thin-walled parts of the aircraft is proposed. The objective of this method is to minimize the maximum deformation of thin-walled components caused by gravity external loads. A synchronous optimization model of clamping layout and clamping sequence is established. The maximum deformation of the thin-walled components under the clamping scheme is obtained through finite element simulation

and the optimization model is solved by genetic algorithm and finite element batch technology. Finally

taking the typical aircraft part long truss as an example

the feasibility and effectiveness of the method are verified.

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