Rocket Stability Of The Device Lightweight Technology Research

Through studying HyperMesh and OptiStruct software,this thesis builds the FEA model of a straight wing of rocket with three dimension tetrahedron elements. Based on the model,the author studies the static performance of the wing structure. Then seven light weight design structures of the wing are computed by OptiStruct. At last,through comparing seven different structures,the best light weight design structure of the straight wing is obtained. The major research contents and related conclusions of this paper are as follows:(1) The characteristic,user interfaces,data storage structure,CAD interface,solver interface,post processing and geometry cleanup functions of HyperMesh are simply introduced. This thesis also summarizes the meshing technology of HyperMesh and describes the main characteristic and basic functions of OptiStruct. After these studies, the author prepares to use the HyperMesh and OptiStruct software in the next step.(2) In this paper, the author uses SolidWorks and HyperMesh software to build the FEA model of the straight wing of rocket with three dimension tetrahedron elements based on the theory of FEM,and gives out the process of building FEA models. All make base for the static performance of the wing structure.(3) The paper researches on the static performance of the wing,standards the steps of static analysis based on HyperMesh and OptiStruct software. Through the research on the static performance of the wing,including the stress and displacement under pressure,we can know the performance of the wing and evaluate whether the wing design is successful or not. The analysis results supply us with some effective results for the optimization design of the wing structure.(4) At last,based on the further researches of the wing's static performance and the structure of plane wing,the light weight design theory of the wing is introduced. Then seven light weight design structures of the wing are computed by OptiStruct. The analysis results including the stress,displacement and the percent of the wing's weight reduction are obtained. Through combining the optimization design structures and the performance requirements of the wing,the best light weight design structure of the straight wing is obtained.