Optimization design of satellite's main structure based on Patran/Nastran
Since the satellite's main structure fails to meet the requirement of carrying stiffness when the traditional method of size design is adopted,in this article the Optimization Module of Patran/Nastran is used for size optimization,with the structur-al stiffness as the design constraint and the satellite's total mass as the objective function.The optimized main structure is verified through the finite-element analysis and experiments.The results are as follows.After optimization,the satellite's total mass is 169.4 kg,which is almost the same as that before optimization.However,the main structure's first-order natural frequency after optimization increases by 30％,compared to that before optimization,reaching 59.87 Hz,which is basically consistent with the theoretical value of 57.03 Hz and meets the requirement of carrying stiffness-not less than 55 Hz.After optimization,the main structure successfully passes the overload assessment,which is 2.5 times as much as the appraisal level,which complies with the expected design value.The satellite successfully passes the ground static test,the whole system vibration test,and the active-phase launching flight verification,with desirable stiffness and high-strength structural load-bearing capacity.The study on satel-lite engineering provides reference for optimized structure design of similar small satellites.
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