Optimized design of primary load-bearing structure for earth observation micro-satellite

Lei, 魏磊 Wei; Guang, 金光 Jin; Xiao-guang, 谢晓光 Xie; Lei, 张雷 Zhang; Lin, 杨林 Yang

doi:10.3788/ope.20152311.3183

Cited by 4 publications

(1 citation statement)

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“…Under the premise of satisfying the structural stiffness, position accuracy and surface shape accuracy of the mirror, the weight of the support structure was removed to the maximum extent, and the structural configuration superior to the quality index was obtained. Wei Lei et al [8] applied the topology optimization method to the micro-satellite main load bearing structure, and obtained a satellite main load bearing structure whose single installation point acceleration response root mean square value meets the index requirements. Pei Yanwei [9] et al optimized the design of the star sensor bracket by using the topology optimization design method to obtain a better structural form and meet the strict index requirements of structural lightweight and pointing accuracy.…”

Section: Introductionmentioning

confidence: 99%

Topological optimization design for support structure under multiple loading conditions

Yan,

Wang,

Chen

et al. 2024

AETR

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In view of the lightweight and high stiffness requirements of a certain type of spacecraft support, combined with the special performance and environment of the support, topology optimization technology is introduced into the optimal design of the support structure in the space field. The topology optimization and design of the support are carried out with the stiffness as the objective function and the quality as the constraint condition, and the design of "space hugging configuration" is proposed, and the simulation verification and experimental verification are carried out. Firstly, different load conditions of the support were analyzed and studied. Secondly, the initial model was established based on the relative position relationship between the support and the mounting surface of the loaded equipment. Finally, a design method of the support structure was established based on the combination of topology optimization under multi-load conditions and size optimization considering the influence of strength. The stiffness and strength of the optimized structure were checked under multiple load conditions, and the fundamental frequency was 2.05 times of the index requirement. The maximum response stress is lower than the yield limit of the material used, which meets the strength requirement. Finally, the vibration test is carried out to verify the support. After the test is completed, the position accuracy of the support interface meets the requirements of the index. The obtained bracket has high structural stability, meets the high performance requirements of the load equipment, verifies the feasibility of the topology optimization method, and provides an effective method for the design of lightweight high-stiffness structures.

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Section: Introductionmentioning

confidence: 99%

Topological optimization design for support structure under multiple loading conditions

Yan,

Wang,

Chen

et al. 2024

AETR

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Multi-objective Structural Optimization and Design of Microsatellite Supporting Legs

Zhao

Yao

et al. 2017

Advances in Structural and Multidisciplinary Optimization

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Multi-objective topology optimization to reduce vibration of micro-satellite primary supporting structure

Tan¹,

Li²,

Gu³

et al. 2017

J. vibroeng.

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We applied multi-objective topology optimization to reduce vibration of the primary supporting structure of video satellites in the frequency domain. The optimal structure is obtained by the multi-objective topology optimization with stiffness and random vibration response as the targets. This is compared with the optimal structure obtained by single-objective topology optimization with stiffness as the target. The dynamic analysis results show that the root mean square values in all three spatial directions of the optimal structure by the multi-objective optimization are smaller than that of the single-objective optimization. The maximal declining value reaches 2.94 g, and the maximal declining degree is 30.6 %. The maximal declining response value on the top of the cylinder reaches 3.87 g with a degree of 33.0 %. The results demonstrate that the multi-objective optimization method significantly improves the vibration response of the base plate, which therefore suppressed the vibration of the satellite. An acceptance condition experiment is performed for the satellite with the optimal base plate from the multi-objective optimization. The dynamic analysis results match well with the experimental data, and verify the applicability of the multi-objective optimization.

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Optimized design of primary load-bearing structure for earth observation micro-satellite

Cited by 4 publications

References 0 publications

Topological optimization design for support structure under multiple loading conditions

Topological optimization design for support structure under multiple loading conditions

Multi-objective Structural Optimization and Design of Microsatellite Supporting Legs

Multi-objective topology optimization to reduce vibration of micro-satellite primary supporting structure

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