The Study Of Launching Dynamics For Antiaircraft Rocket Launcher System

Some researches on launching response property of antiaircraft rocket launcher were done in the dissertation with intent to improve the launching precision of rockets.In term of the physical characteristics of antiaircraft rocket launcher, the modeling of multi-body system dynamics was investigated for antiaircraft rocket launche by relative coordinate and generalized recursive formulas. Based on the graph theory used to topological structure for antiaircraft rocket launcher system, this recursive formula was applied to compute the partial derivative of the cartesian velocity and force of antiaircraft rocket launcher system with respect to relative coordinates, for example, computation sequence for the cartesian velocity and force was shown.The dynamical model of system was established through the Virtual Prototype(VP) technology, and dynamical simulation was also run after. First, the methods were studies of improving the rocket launching precision, second, the possible launching sequences with respect to launch numerous rockets simultaneously were addressed, and finally, the better firing order of the initial disturbance was determined by the simulation outcomes. The variable interval was firstly applied in antiaircraft rocket launching, applying in Design of Experiments (DOE)-guided, the database of dynamic simulation results was established, the nonlinear relationship between the approximate model of the firing interval, which was constructed by utilizing the previous database, and the initial disturbance variables was determined, this precise approximate model was further improved by introducing the multi-island genetic algorithm method to find the optimal solution of the variable firing intervals. Results showed that the approximate model can significantly reduce the computational expense in searching the best solution of the variable firing intervals, and the reasonable variable firing intervals can effectively improve the firing dispersion.The rigid-flexible coupling Launch dynamics model for a automobile carried antiaircraft rocket launcher was established, in which both the automobile beam and launch tubes were treated as the flexible bodies. Base on the structural characteristics of automobile carried antiaircraft rocket launcher, the flexible automobile beam was created by the modal reduction method, and the flexible launch tubes were generated by means of nodal flexible method with considering the advantages and disadvantages of both modal reduction method and nodal flexible method, the calculation precision and efficiency of model were improved.Based on the rigid-flexible coupling Launch dynamics model for a automobile carried antiaircraft rocket launcher, launching response property in situation of dynamical tracing various target route was studies by co-simulink of dynamics and control, some useful conclusions are obtained. The control model of servo system for antiaircraft rocket launcher was set up, the controllers parameters of which were confirmed through genetic algorithm(GA). The VP technology was used leading, i.e. to integrate dynamical system into control system to realize cooperation simulation, so avoiding the derivation process of complicated dynamics control equations. The simulation showed that the firing response in dynamical tracing situation could be controlled effectively when applying active vibration control and to improve precision.