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Optimal design of space assembly microsatellite structure based on sequential quadratic programming

Yanbo Feng (College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, China and School of Light Industry, Harbin University of Commerce, Harbin, China)
Xiande Wu (College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, China)
Weidong Chen (College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, China)
Yaen Xie (College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, China)
Taihang Yu (School of Light Industry, Harbin University of Commerce, Harbin, China)
Yong Hao (College of Intelligent Systems Science and Engineering, Harbin Engineering University, Harbin, China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 11 August 2022

Issue publication date: 2 January 2023

35

Abstract

Purpose

On-orbit assembly technology is a promising research topic in spaceflight field. For purposes of studying the dynamic performance and reducing weight of an on-orbit assembly satellite structure frame, this paper aims to propose a structural optimization design method based on natural frequency.

Design/methodology/approach

The dynamic stability of the satellite under working condition depends on the mechanical properties of the structure matrix. A global structural optimization model is established, with the objective of mass minimization and the constraints of given natural frequencies and given structure requirements. The structural optimization and improvement design method is proposed using sequential quadratic programming calculation.

Findings

The optimal result of objective function is effectively obtained, and the best combination of structural geometric parameters is configurated. By analyzing the relationship between the structural variables and optimization parameters, the primary and secondary factors to the mass optimization process of the microsatellite satisfying the dynamic performance requirements are obtained, which improves the effectiveness and accuracy of the system optimization design.

Originality/value

This method can coordinate the relation between satellite vibration stability and weight reduction, which provides an effective way for the optimization design of on-orbit assembly microsatellite. It has reference significance for the similar spacecraft framework structure design.

Keywords

Acknowledgements

This research was funded by the Fundamental Research Funds for the Central Universities (No.3072022JC0202), the project D020214.

Citation

Feng, Y., Wu, X., Chen, W., Xie, Y., Yu, T. and Hao, Y. (2023), "Optimal design of space assembly microsatellite structure based on sequential quadratic programming", Aircraft Engineering and Aerospace Technology, Vol. 95 No. 1, pp. 145-154. https://doi.org/10.1108/AEAT-02-2021-0057

Publisher

:

Emerald Publishing Limited

Copyright © 2022, Emerald Publishing Limited

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