基于不完备信息的拦截卫星末段轨道机动的分析与综合
发布时间：2018-11-18 20:14
【摘要】：拦截卫星是空天攻防中的重要元素,其末段轨道控制问题是完成攻击任务的关键,伴随着轨道不确定性、噪声以及目标卫星的轨道机动等因素,拦截卫星在进行轨道机动时难以准确获得自己相对于目标卫星的位置以及速度。本文针对轨道信息不完备这一问题,对拦截卫星末段轨道控制系统进行建模分析,并对攻防卫星相互接触和攻防卫星相对位置保持两种情况进行控制器设计。本文主要研究内容为:(1)基于C-W方程建立了拦截卫星相对运动动力学模型,根据攻防卫星相互接触和攻防卫星相对位置保持两种情况进行状态空间表达式的建立,并引入非圆不确定性、能量有界噪声和白噪声等干扰。(2)利用动态输出反馈控制器建立闭环系统,针对系统镇定问题、参数不确定性、能量有界噪声、白噪声和推力有限等限制条件,设计了可以满足极点配置、H2性能指标、H∞性能指标和推力有限约束的多目标动态输出反馈控制器。(3)引入状态观测器,利用状态观测器实现状态反馈。针对系统镇定问题、参数不确定性、能量有界噪声以及白噪声等限制条件,设计了可以满足极点配置、H2性能指标和H∞性能指标的多目标控制器。并基于闭环系统的传递函数分离特性和极点配置分离特性,将原系统分成两个子系统分别进行控制器和观测器的设计。(4)基于拦截卫星采样轨道状态信号,将连续系统转换为采样系统。再利用输入时滞法将采样系统等价变换为时滞系统形式,利用时滞系统的思想设计鲁棒滤波器,并将设计方法拓展应用到拦截卫星以与目标卫星相对位置保持为目标的鲁棒滤波器设计。
[Abstract]:Intercepting satellite is an important element in space and space attack and defense. The control of its terminal orbit is the key to accomplish the attack mission, accompanied by the orbit uncertainty, noise and orbit maneuver of the target satellite, and other factors, such as the orbit uncertainty, the noise and the orbit maneuver of the target satellite, etc. It is difficult to obtain the position and velocity of the interceptor satellite in orbit maneuver. Aiming at the problem of incomplete orbit information, this paper models and analyzes the terminal orbit control system of intercepting satellite, and designs the controller for the contact between attack and defense satellites and the relative position of attack and defense satellite. The main contents of this paper are as follows: (1) based on the C-W equation, the relative motion dynamics model of the interceptor satellite is established, and the expression of the state space is established according to the contact between the attack and defense satellites and the relative position of the attack and defense satellite. The noncircular uncertainty, energy bounded noise and white noise are introduced. (2) the closed-loop system is established by using dynamic output feedback controller to solve the stabilization problem, parameter uncertainty, energy bounded noise, etc. A multi-objective dynamic output feedback controller, which can satisfy the pole assignment, H2 performance index, H 鈭，
本文编号：2341089
[Abstract]:Intercepting satellite is an important element in space and space attack and defense. The control of its terminal orbit is the key to accomplish the attack mission, accompanied by the orbit uncertainty, noise and orbit maneuver of the target satellite, and other factors, such as the orbit uncertainty, the noise and the orbit maneuver of the target satellite, etc. It is difficult to obtain the position and velocity of the interceptor satellite in orbit maneuver. Aiming at the problem of incomplete orbit information, this paper models and analyzes the terminal orbit control system of intercepting satellite, and designs the controller for the contact between attack and defense satellites and the relative position of attack and defense satellite. The main contents of this paper are as follows: (1) based on the C-W equation, the relative motion dynamics model of the interceptor satellite is established, and the expression of the state space is established according to the contact between the attack and defense satellites and the relative position of the attack and defense satellite. The noncircular uncertainty, energy bounded noise and white noise are introduced. (2) the closed-loop system is established by using dynamic output feedback controller to solve the stabilization problem, parameter uncertainty, energy bounded noise, etc. A multi-objective dynamic output feedback controller, which can satisfy the pole assignment, H2 performance index, H 鈭，
本文编号：2341089
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