Study On Dynamics Of Long Range Multiple Launch Rocket System And Its Application

Dynamics of Long Range Multiple Launch Rocket System(LRMLRS) is such kind of theory, technology and test method, which is used in the study on motion pattern, control process of LRMLRS and the force acting on it during launch and flight process in order to control the motion and the forces. How to guarantee its dynamical performance by dynamic design, how to decrease the number of rockets consumption in the LRMLRS test and on condition of guaranteeing the quality of the test, how to predict and improve its dispersion of fire, these theory and engineering problems are urgently needed to be solved in the development, production and test of LRMLRS.From the viewpoint of large system dynamics including rockets, gun, propellant and launch environment, the whole process of LRMLRS from the ignition to level point is deeply studied by three ways, that is theory, computation and experiment, in this paper. By using the transfer matrix method of multibody system(TMM-MM), the hard problem of computation of the vibration characteristics of LRMLRS coupled with rigid bodies and elastic bodies is solved which is very difficult to the ordinary dynamic methods, and the vibration characteristics of LRMLRS which is varied when the number of rockets in the launch device is varied, is obtained conveniently. By developing augmented eigenvectors of the LRMLRS and its orthogonality conditions, the nonorthogonality problem of the multibody system including rigid bodies and elastic bodies is solved and the exact analysis of the dynamics response of the LRMLRS including rigid bodies and elastic bodies is realized. By using the random integer programming method, the hard optimization problem which contains continuous variables, discrete variables and random variables at the same time is solved. This method provides a technology for optimum design with random variables and discrete variables. The dynamic optimum design is realized to decrease the number of rockets consumption in the LRMLRS test. The simulation system of dispersion of fire is established by using the maximum entropy method to estimate dispersion of fire. The dynamical optimum is realized to improve the dispersion of fire of LRMLRS by optimizing the firing orderes and firing interval. The developments are made in the papers as follows:(1) The hard problem of computation of the vibration characteristics of LRMLRS coupled with rigid bodies and elastic bodies is solved, by using TMM-MM.(2) By developing augmented eigenvectors, the orthogonality problem of the LRMLRS including rigid bodies and elastic bodies is solved.(3) The simulation system of random launch and flight dynamics of the LRMLRS isdeveloped, by establishing launch and flight dynamics equations.(4) By using the random integer programming method, the optimum problem decreasing the number of rockets consumption in the LRMLRS test is solved.(5) The theory and technology problem decreasing the number of rockets consumption in the LRMLRS test is solved.(6) The new technology improving the dispersion of fire of LRMLRS is developed. The engineering problem of improving the dispersion of fire of a MLRS is solved.