Model Reference Tracking Control For Jump Systems And Its Applications In Fault Satellites Control

In practical problems,many control systems will be affected by some uncertain factors that cause the change of the systems parameters,for example,the component failures or external interference,etc.In order to consider the effect of these uncertain factors on the systems,we need to use the Markov jump theory on the system modeling.Model reference tracking control plays an important role in control system design and it has many applications in practical engineering problems.On the other hand,many problems in satellite control can be unified into model reference tracking control problem for Markov jump systems.Therefore,the research of model reference tracking control problem for jump systems has important theoretical significance and practical significance.The main work of this dissertation investigates the model reference tracking control problems of jump systems and presented the complete parameteric algorithm for the controller and its applications in fault satellite control.The goal of trajectory tracking control is that the closed-loop system is stable and can track the given command.In this paper,the designed controller includes two parts: the feedback control law and feedforward compensator.The main contributions are listed as follows.The model reference tracking control problem is presented of the satellite with actuator jumping fault.Consider the satellite running along the elliptical orbit,the existence condition of the orbit controller is deduced based on the Lyapunov stability theory.Using the freezing method and optimal control theory,the state feedback control law is designed for the system to achieve the minimum energy consumption index.The feedforward compensator is obtained by solving the varying coefficient nonhomogeneous generalized Sylvester equation.The designed controller contains free parameter matrix and it can be optimized by the matrix.The control algorithm does not need to be augmented or transformation of the system which is easy for engineering application.Finally,the effectiveness of the proposed control algorithm is verified by a numerical simulation example.Consider the satellite running along the circular orbit,when the actuator occurs jumping fault,it is discussed the trajectory tracking control problem of the fault satellite under the system contains stochastic disturbance.It is built the It ?o stochastic disturbance model and conventional stochastic disturbance model respectively.The form of controller and tracking equation are given respectively.Since the thrust cannot be infinite in satellite control,therefore,how to rejection the disturbance is a difficult point in the controller design.Thus a LMI method with maximum input constraints is used to solve the problem,Then the feedback control law is designed to rejection the disturbance respectively.By solving the tracking equation,the parameteric expression form of the controller is obtained.Simulation results show that the designed controller not only can complete the hovering and flyingaround mission,and can also tracking the marginal stable reference signal.This validates the effectiveness and superiority of the proposed controller.Consider the satellite running along the circular orbit similarly,In consideration of the state of the satellite sometimes can not be measured completely,the observer-based model reference tracking controller is designed.The general mathematical description is given of the problem.The satellite tracking equation is given in the form of inference.The observer-based state feedback control law is designed by using the iterative algorithm under the minimum energy consumption index.In the same way,the feedforward compensator can be obtained by solving the tracking equation and also the obtained controller contains the free parameter matrix.The effectiveness of the proposed controller is verified by a numerical simulation example.The integrated relative orbit and attitude control problem of non-cooperative rendezvous is studied.The mathematical model is derived,then we focus on the case the rotation inertia occurs the jumping.The problem that integrated relative orbit and attitude tracking control is unified into the tracking control problem for Markov jump systems.The controller that contains rotation inertia jumping is designed.The controller and the tracking equation are derived directly under the second-order jump system model,and the highest order of the tracking equation is two order.The controller contains the feedback term,the feedforward term and the nonlinear compensation term.Consider simultaneously the case that the value that the orbital thrust and attitude torque are finite,by using the linear matrix inequality method,it is designed the state feedback control law.By solving the tracking equation of the integrated relative orbit and attitude control system,it is obtained the general complete parametric expression for the controller.The effectiveness of the proposed controller is verified by the numerical simulation example for satellite rendezvous.