Research On Analysis Method Of Vibration Boundary Conditions For Rocket Launching Process

This thesis mainly focuses on the rocket launcher system in the marching condition.In order to solve the problems of the lack of boundary conditions in the dynamics analysis of the vibration characteristics and the fatigue failure,this article researched the theoretical basis of the analysis method of vibration boundary condition,and presented a Semi-Physical Simulation method which was suitable for the engineering research of rocket system in vibration and fatigue field.This thesis applied the method to obtain the vibration boundary conditions of Rocket Launcher.The feasibility of this method was verified by the simulation of vehicle bench test.The following assignments were accomplished based on thorough study into the finite element method and the engineering testing theory.Firstly,A verification experiment was designed,which was similar to a rocket launcher driving vibration system,with the application similarity and modeling principle.The vehicle in verification experiment has a similar structure with launching device of the three points supporting structure.The finite element model of the experimental vehicle was established by HyperMesh,and carried the modal analysis of the whole vehicle.Secondly,based on the principle of random road irregularities of sine superposition simulation,the pavement spectrum file was generated with the application of MATLAB programming.Finally,the test bench model with experimental vehicle of rigid flexible coupling was established by Adams.The simulation of the experimental vehicle bench test was done in Adams and the analysis method was applied to the vibration analysis of the experimental vehicle.In conclusion,through the research,a general method for obtaining the model boundary condition in the analysis of vibration characteristics and fatigue failure was explored.This thesis put forward the research method of semi-physical simulation for vibration analysis of the rocket launcher system.The applicability and error range of the research method was also revealed.Confirmed the feasibility of the dynamics analysis of rocket system,as the analysis method was applied to the March condition.The analysis method provided a effective way for Vibration Engineering Research of the rocket launcher.