远程多管火箭动力学及其应用研究
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摘要
远程多管火箭动力学是研究远程多管火箭在发射与飞行过程中的受力及运动规律和控制过程，进而研究控制其受力与运动的理论、技术和试验测试方法。如何进行动态设计以保证远程多管火箭的动态性能，如何在保证试验质量的前提下大幅度减少远程多管火箭的试验用弹量，如何预测并提高远程多管火箭的射击密集度，这些是远程多管火箭研制、生产、试验中亟待解决的理论与工程问题。
本文从弹、炮、药、环境大系统动力学的角度，从理论、计算、试验三大方面，深入研究了远程多管火箭从发动机点火到火箭弹落点的全过程。通过应用多体系统传递矩阵法，解决了刚弹耦合远程多管火箭多体系统振动特性这一通常力学方法不便于解决的计算难题，方便地获得了远程多管火箭振动特性及其随发射架上火箭弹个数变化而变化的情况；通过构造增广特征矢量及其正交性条件，解决了刚弹耦合多体系统特征矢量不具有通常意义下的正交性的难题，实现了对刚弹耦合远程多管火箭动力响应的精确分析；应用随机整数规划法，解决了同时考虑连续、离散和随机变量等多种设计变量的优化设计难题，为含随机和离散变量的优化设计提供了手段，实现了减少远程多管火箭试验用弹量的动态优化设计；建立了应用最大熵法估计的密集度仿真系统，优化射序和射击间隔，实现了提高远程多管火箭射击密集度的动态优化。
本文在以下几方面取得了一定的进展：
(1)通过应用多体系统传递矩阵法，解决了远程多管火箭刚弹耦合多体系统振动特性的计算难题；
(2)通过构造增广特征矢量，解决了远程多管火箭刚弹耦合多体系统特征矢量的正交性难题；
(3)通过建立多管火箭发射与飞行动力学方程，形成了远程多管火箭随机发射与飞行动力学仿真系统；
(4)应用随机整数规划方法，解决了减少远程多管火箭试验用弹量的优化问题；
(5)解决了减少远程多管火箭试验用弹量这一理论与技术问题；
(6)形成了提高远程多管火箭系统密集度新技术，解决了提高某多管火箭系统密集度这一实际工程问题。
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 optimi
zation 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 is
developed, 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.
本文从弹、炮、药、环境大系统动力学的角度，从理论、计算、试验三大方面，深入研究了远程多管火箭从发动机点火到火箭弹落点的全过程。通过应用多体系统传递矩阵法，解决了刚弹耦合远程多管火箭多体系统振动特性这一通常力学方法不便于解决的计算难题，方便地获得了远程多管火箭振动特性及其随发射架上火箭弹个数变化而变化的情况；通过构造增广特征矢量及其正交性条件，解决了刚弹耦合多体系统特征矢量不具有通常意义下的正交性的难题，实现了对刚弹耦合远程多管火箭动力响应的精确分析；应用随机整数规划法，解决了同时考虑连续、离散和随机变量等多种设计变量的优化设计难题，为含随机和离散变量的优化设计提供了手段，实现了减少远程多管火箭试验用弹量的动态优化设计；建立了应用最大熵法估计的密集度仿真系统，优化射序和射击间隔，实现了提高远程多管火箭射击密集度的动态优化。
本文在以下几方面取得了一定的进展：
(1)通过应用多体系统传递矩阵法，解决了远程多管火箭刚弹耦合多体系统振动特性的计算难题；
(2)通过构造增广特征矢量，解决了远程多管火箭刚弹耦合多体系统特征矢量的正交性难题；
(3)通过建立多管火箭发射与飞行动力学方程，形成了远程多管火箭随机发射与飞行动力学仿真系统；
(4)应用随机整数规划方法，解决了减少远程多管火箭试验用弹量的优化问题；
(5)解决了减少远程多管火箭试验用弹量这一理论与技术问题；
(6)形成了提高远程多管火箭系统密集度新技术，解决了提高某多管火箭系统密集度这一实际工程问题。
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 optimi
zation 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 is
developed, 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.
引文
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