【作者】 李增文；

【导师】 贺有智；

【作者基本信息】 燕山大学 ， 制导与控制， 2011， 硕士

【摘要】 本文主要对三轴稳定质量矩控制导弹的模型建立和模型简化问题进行了分析与研究。根据牛顿运动定律建立质心运动和绕质心转动动力学方程,由于模型的非线性、强耦合等特点,为方便控制系统的设计,对模型进行了必要的简化。质心运动方程的简化相对比较简单。绕质心转动动力学方程的简化由于导弹内部质量块的运动而变得相对比较复杂。本文对导弹内部各质量块的位置参数采用正弦输入信号,通过改变正弦输入信号的角频率进行仿真实验,进而分析各质量块运动速度及加速度对系统的影响,仿真结果表明当质量块运动速度及加速度在一定范围内变化时,可以对绕质心转动方程进行简化。在质量矩控制导弹简化模型基础上,利用Lyapunov理论对质量矩控制导弹进行了稳定性分析。应用时标分离方法将系统分成快、慢两个子系统,采用动态逆控制方法对控制导弹的非线性系统进行了设计,仿真结果验证了此方法的可行性。在不同的初始条件下,根据视线坐标系、惯性坐标系及弹体坐标系的转换关系,采用修正的比例导引律对导弹拦截目标进行了空间全弹道仿真,对所给出的简化模型做了进一步的验证,使质量矩控制导弹的工程实现成为可能。更多还原

【Abstract】 The main research contents of this paper are the modeling and model simplification analysis of three-axis stabilized mass moment control missile.Establishing the center of mass movement and rotation around the center of mass kinetic equation according to Newton’s laws of motion.The model is nonlinear, strong coupling and so on, in order to facilitate the design of control system, the model was necessary to be simplified.The simplification of equation of motion of mass is relatively simple. While the simplification of rotating around the center of mass kinetic equations is relatively more complex because the movement of mass within the missile. It is inputted sine signal to the position parameters of the mass moment within the missile, simulation experiment is conducted by changing the angular frequency of sinusoidal, and then analyzes the effect of velocity and acceleration of mass moment on the system. Simulation results demonstrate that when the velocity and mass acceleration changes in a certain range, we can accomplish the simplification of equation around the center of mass.According to the simplified model of the missile, the stability analysis of three-axis stabilized mass moment control missile is done on the support of Lyapunov theory. The system is departed into a fast and a slow subsystem with the application of separation of time scale.The nonlinear system of the control of the missile is designed with the dynamic inversion method, this method is proved feasible by the simulation experiment.In different initial conditions, according to the transformation of vision coordinate system, inertial coordinate system and the body coordinate system,adopt modified proportional guidance law to intercept the missile target in space the whole trajectory simulation on the simplified model given to do further verification, it made the engineering realization of mass moment control missile become possible.更多还原