Design optimization of spacecraft hatch deployable mechanism based on digital twin

被引：0

作者：

Zhang Z. ^{[1
]}

Lin W. ^{[1
]}

Cheng H. ^{[2
]}

Fan B. ^{[1
]}

Pi G. ^{[2
]}

Luan H. ^{[2
]}

机构：

[1] School of Mechatronic and Automation Engineering, Shanghai University, Shanghai

[2] Shanghai Aerospace Equipment Manufacturing Co., Ltd., Shanghai

来源：

Jisuanji Jicheng Zhizao Xitong/Computer Integrated Manufacturing Systems, CIMS | 2019年 / 25卷 / 06期

关键词：

Approximate model; Depleyable mechanism; Digital twin; Material parameters; Optimization design; Root-joints clearance; Spacecraft hatch;

D O I：

10.13196/j.cims.2019.06.006

中图分类号：

学科分类号：

摘要：

To improve vibration caused by clearance of root-joints during the process of the spacecraft hatch deployment, a material parameters optimization method using digital twin and Radial Basis Functions (RBF) model was proposed. The dynamic model of clearance was established, and then the digital twin model of hatch was constructed by using digital twin technology. The contact stiffness coefficient, damping coefficient and dynamic friction coefficient of the root-joints' material were taken as the design variables, and the maximum angular acceleration as the optimization objective to build the sample space with the optimal Latin hypercube experiment design. The approximate model was constructed based on radial basis function neural network model. The combined Sequential Quadratic Programming Algorithm (SQP) and Multi-Island Genetic Algorithm (MIGA) was applied to calculate the optimal design. The optimization results indicated that the peak angular acceleration of hatch and the contact force of root-joints were significantly reduced compared to original, and the dynamic performance of the hatch was improved. © 2019, Editorial Department of CIMS. All right reserved.

引用

页码：1371 / 1380

页数：9

共 24 条

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