A Complex Mechanical System Structure Lightweight

To decrease the weight and to improve the flexibility of the weapon is the need of modern war and the development trend of the weapon investigation. Structure optimization is the mostly way to decrease the weight. The research of this paper, which purpose is to reduce the weight of the gyration body of certain proper motion rocket, has been focused on structure optimization on it.This paper, which focused on the structure optimization theory and method, has finished such studies as follows: The three dimension model has been built, which provide the necessary conditions for the building of the dynamics equivalent model. By the launch dynamics simulation, the loads of the key joints when the rocket is launched has been got, which provide the necessary data for the finite element analysis and the structure optimization. The finite element model of the excess weight parts of the rocket has been built, buy the finite element intension analysis of the model in two conditions, the displacement and the stress of the key points have been got, which make us know the distributing of the stress and the transmogrification of the part. To satisfy the intension and the precision design request and to decrease the weight of the part as many as possible, the part has been topology optimized by the structure optimization theory and method. After that, the new model has been analysis in structure and launch dynamics. The contrast of the character change of the old part and the new part and the influence on the rocket system have been studied. The results show that the intension and the precision of the part satisfy the design request after the topology optimization, the influence on the rocket system is relatively light, the optimization on the part is successfully. The result of this paper has a certain extend reference meaning for the reduce weight of the rocket weapon system for the future.