Optimization Design of Aircraft Weak Rigid Parts Clamping Scheme Based on Genetic Algorithm
LI Xining1, WANG Yueshun1, LI Yuhua1, WANG Shouchuan2
1. Key Laboratory of Contemporary Design and Integrated Manufacturing Technology, Ministry of Education, Northwestern Polytechnical University, Xi’an 710072, China ;
2. Tooling Design Institute of China Aviation Aircraft Co., Xi’an 710089, China
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.
基金资助:装备预研共用技术项目（41423010202）。
引用本文:
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.
2019, 
