Research On The Structure Optimization Of A Certain Attitude Control Dynamic System

Attitude control power system is the power system of spacecraft.It provides power for spacecraft to adjust posture and orbit transformation when flying in space.The attitude control power system carries the launch vehicle with the spacecraft to the earth's atmosphere,and some attitude control power systems have to shoulder the mission of the spacecraft to return to the earth.Therefore,the attitude control power system must have enough strength and stiffness to bear the structure without damage when carrying and returning all kinds of load during the launch and return process.As a part of the weight of spacecraft structure,the smaller the weight,the better the attitude control power system.This paper will study the strength,stiffness and structure optimization of a gesture control power system.The research on the structure optimization of the attitude control power system is carried out from two aspects: one is to optimize the structure of the structure and installation board of the attitude control power system,and two to optimize the combined support of the attitude control engine.After the static and random vibration simulation analysis,the configuration plate of the attitude control power system is analyzed by the static and random vibration simulation.The minimum thickness of the installation plate is determined by the size optimization of the mounting plate.The transmission path of the mounting plate force is found through the topology optimization analysis,and the installation position and topology analysis structure of the installation board are based on the installation plate.The reinforcement position of the mounting plate is designed,the size of the reinforcement is optimized and the optimum reinforcement height is determined.By modal analysis and optimization of the mounting plate,the structure that meets the requirements is designed.After analyzing the statics and random vibration of the attitude control engine combination bracket,the structure of the composite support is optimized by topology optimization.Through the analysis of the optimized structure,the position of the stress concentration is found out,and the structure is optimized by the inverted round angle.The maximum stress of the structural mounting plate is reduced by 43%,the maximum strain is reduced by 38.2% and the mass is reduced by 41.9%.The mechanical performance of the optimized mounting plate is verified by the test.The maximum stress of the attitude control engine combined support is reduced by 23.9%,the maximum strain is reduced by 8.6% and the mass is reduced by 12%.The reliability of the structure is verified by the static fatigue analysis and the random vibration fatigue analysis.