Research On Optimization Of Launcher Under The Action Of High Frequency Strong Shock And Random Excitation

In order to guard against more and more air strike forces in modern warfare,higher requirements have been put forward to ground mechanized forces.Gun-missile combined vehicle are increasingly valued for their high mobility and greater airspace air defense capabilities.In this paper,a combination of multibody dynamics methods,finite element methods,multi-objective optimization and modern control theory was applied to study the rigid-flexible coupled dynamics modeling of a defensive vehicle during shooting,the optimization of the overall layout of the launching device and the stability of the tracking and targeting during the driving was also studied.The topological analysis of the gun-missile combined vehicle was carried out.The typical three-dimensional road roughness models were reconstructed by using the harmonic superposition method.The flexible deformation of several components were described by using the finite element flexible body technology.Rigid-flexible coupled dynamic model of pavement-tire-suspension-body-launcher was established.The accuracy of the model was verified by comparing the numerical calculation with the experimental data.The launcher's dynamic characteristics were calculated,the vibration response of the launcher was studied under different working conditions.The variations of muzzle disturbance during firing and firing progress of the gun were studied.An approximate model method was used to study the equipment layout optimization of the launcher device,the numerical calculation was performed.The sensitivity of structure layout structure parameters was analyzed.The structural parameters that have a greater impact had been filtered out.The parameter samples were extracted by using Optimal Latin Hypercube Design,based on it,test samples of muzzle disturbance were obtained after dynamic calculation.Then the approximate models were established to optimize the layout of structure on the launcher.The optimization results can significantly reduce the muzzle disturbance.Control models of servo system of vehicle on moving were established by using PID +feedforward composite control method.Compared with the traditional PID control method,the better effect of the composite control was verified.According to the different characteristics of the azimuth and pitch servo systems,two sets of servo systems were set up to control them separately.By introducing road surface and heavy moment compensation,the muzzle stabilization was effectively improved.Accordingly,the stability problem of muzzle tracking and aiming during travel was solved.The work in this thesis can provide an important theoretical reference and engineering application value for the structural design and optimization of the gun-missile combined vehicle's launcher device.