272 results about "Fault tolerant controller" patented technology

The invention relates to a quadrotor unmanned aerial vehicle attitude control system modeling and finite time attitude tracking control method, in particular to a quadrotor unmanned aerial vehicle finite time attitude tracking control method. Disturbance torque with which a quadrotor unmanned aerial vehicle is confronted is comprehensively analyzed, rotating inertia is unknown, output saturation and actuator failure and other factors are controlled, a passive fault-tolerant controller is designed on the basis of a parameter adaptive method, and the finite time stabilizing function is achieved. The method comprises the steps of 1 building a quadrotor unmanned aerial vehicle attitude tracking kinematic model, 2 building a quadrotor unmanned aerial vehicle attitude tracking kinetic model, 3 defining quadrotor unmanned aerial vehicle attitude smoothing errors, 4 designing a finite time integral sliding mode surface, and 5 designing a quadrotor unmanned aerial vehicle finite time attitude tracking controller. The method is used for the field of unmanned aerial vehicle flight control.

The invention presents a design method of a four-rotor fault-tolerant controller based on a nonlinear observer. The method includes the following steps: establishing a dynamic model of a four-rotor unmanned aerial vehicle (UAV), and dividing the UAV system into an attitude subsystem and a position subsystem; for the attitude subsystem, establishing a fault model, designing a nonlinear fault observer, carrying out real-time detection and online estimation on an unknown actuator fault, and designing a fault-tolerant controller based on a fast non-singular terminal sliding mode method by using the obtained fault estimation information; and for the position subsystem, inversely solving the control rate and the desired attitude angle of the position subsystem by combining a backstepping methodand a sliding mode method and designing an intermediate virtual quantity. A four-rotor UAV is enabled to track the desired position and yaw angle even when the actuator fails, so as to ensure the stability of the pitch angle and roll angle.

The invention discloses a four-rotor aircraft fault-tolerant control method and belongs to the field of aerocraft control. According to the method, first, based on a mathematical model of an aircraft, an attitude model under the condition of system faults of the aircraft is established; then, according to the attitude model, an adaptive law of fault estimation of an aircraft system is brought out, and a transfer function of loss of actuator effectiveness of the aircraft is also established; an adaptive law of fault estimation of loss of actuator effectiveness is put forward based on the loss of actuator effectiveness; and at last, based on the fault estimation of the system and the fault estimation of loss of actuator effectiveness, a fault-tolerant controller of an aircraft attitude system is designed. Thus, fault-tolerant control of four-rotor aircrafts is realized. By means of the method, probability of air crashes of four-rotor aircrafts is remarkably reduced, and flying reliability and safety of aircrafts are improved.

The invention discloses a near spacecraft fault diagnosis and fault-tolerant control method. Firstly, a dynamical model of an attitude control system of a reentry phase of a near spacecraft is established and the dynamical model of the attitude control system is transferred to a nonlinear equation in a general type through coordinate transformation; secondly, a fault model with actuator invalidation and actuator dynamic damage existing simultaneously is established; thirdly, real-time online estimation of self-adaption estimation observer to actuator dynamic damage factors and actuator invalidation factors is respectively established; and finally a sliding module fault-tolerant controller is designed through the estimated actuator dynamic damage factors and the estimated actuator invalidation factors and parameters of the controller is updated in real time. According to the near spacecraft fault diagnosis and fault-tolerant control method, in the condition that when the actuator dynamic damage and the actuator invalidation occur simultaneously in a flight control system, fault information can be estimated rapidly and accurately, strong fault-tolerant capacity is achieved and an expected requirement of the flight control system is reached.

The invention relates to the technical field of satellite fault diagnosis and fault-tolerant control, and proposes a fault diagnosis method, which has very good robustness to external interference, isfree of influence of external interference in a fault diagnosis process, prevents generation of misinformation and missing report, and can effectively estimate fault severity. According to the satellite fault diagnosis and fault-tolerant control method based on a self-adaptive observer, first a satellite kinematics and dynamics model under an actuator fault and external interference influence isestablished to analyze influence of fault effective factors on a system; secondly, an observer is designed for a satellite fault system, a residual error evaluation function is established based on observer output and system actual output, an evaluation threshold value is obtained, and the purpose of fault detection is achieved; then, when occurrence of a fault is detected, a self-adaptive observer is designed to complete a fault diagnosis task; and finally, based on an estimated value of the fault, a finite time self-adaptive fault-tolerant controller is designed. The satellite fault diagnosis and fault-tolerant control method based on a self-adaptive observer is mainly applied to fault diagnosis and fault-tolerant control occasions.

The invention discloses a vertical take-off and landing airplane robust fault-tolerant control system and method based on cascaded observers, and belongs to the technical field of aircraft control. A vertical take-off and landing airplane dynamical model taking external disturbance and actuator faults into consideration is built, the dynamical model is converted into a non-linear model in a standard form, the disturbance, the faults and state variables are estimated in real time by using the disturbance observer and the fault diagnosis observer which is in cascade connection with the disturbance observer, the non-linear model is decoupled into two subsystems, the control rate of each subsystem is determined, and the fault-tolerant control rate is determined according to the control rates and fault estimation values of the two subsystems. Under the action of a fault-tolerant controller, the system taking effects of the external disturbance and the faults into consideration compensates for the faults and the disturbance in real time, influence of the faults and the disturbance is reduced rapidly, and robustness of the control system is improved.

The invention relates to a satellite fault diagnosis and fault-tolerant control method based on a T-S fuzzy model and a learning observer. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and the learning observer is used for solving the problems that a conventional fault diagnosis method cannot be used for effectively treating the influence caused by space disturbance torque and ensuring the robustness of a fault diagnosis method, and a conventional fault-tolerant control method has a poor fault-tolerant property. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and the learning observer comprises the following steps: step 1. establishing a mathematical model of a non-linear satellite attitude control system; step 2. establishing the T-S fuzzy model of the satellite attitude control system by using results obtained in the step 1; step 3. designing a T-S fuzzy learning observer by using the results obtained in the step 2 so as to realize the robust fault detection, isolation and fault reconstruction of a satellite attitude angular velocity estimation and executing mechanism; 4. designing a state feedback fault-tolerant controller by using the results obtained in the step 3 so as to ensure that a closed loop of a satellite attitude control T-S fuzzy system is stable. The satellite fault diagnosis and fault-tolerant control method based on the T-S fuzzy model and learning observer can be applied to an aerospace field.

The invention discloses a non-affine non-linear flight control system robust adaptive fault-tolerant control system used for a non-linear system with parameters in a non-affine mode. An observer has relatively idea robustness on the situation that the parameters change in a large range. Fault information and disturbance information are implied in the observer, and then a fault-tolerant controller is dynamically designed on the basis of the observer. Due to the non-affine non-linear system, the controller is not easy to design, the non-affine non-linear system approximates to an affine non-linear system with time-varying parameters, and the parameters needing to be known are estimated online through a filter. By means of the non-linear flight control system, effectiveness of a method is verified, and robust adaptive fault-tolerant control of the non-affine non-linear flight control system can be achieved. Robust adaptive fault-tolerant control of the non-affine non-linear flight control system is achieved and applied in the flight control system, and a simulation result displays effectiveness of the method.

Provided is a fault tolerant control method for a spacecraft equipped with a flywheel based on robust adaptation. The method comprises five steps of: 1, establishing a spacecraft kinematical equation; 2, establishing a spacecraft kinetic equation; 3, performing desired angular velocity locus design; 4, performing controller output torque design; and 5, performing numerical simulation. Under the circumstance that a FDD device is not used, the method online estimates a triaxial torque fault factor and designs a robust adaptive fault tolerant controller. The research aims at enriching spacecraft PFTCS methods and providing technical support for spacecraft attitude control in the future.

The invention relates to a four-rotor unmanned aerial vehicle tolerant control method, and provides a tolerant controller. When an actuator is partially failed, a four-rotor unmanned aerial vehicle is still stable. According to the technical scheme provided by the invention, a tolerant control method for partial failure of the four-rotor unmanned aerial vehicle actuator comprises the steps that the principle of the action of the actuator on the four-rotor unmanned aerial vehicle is analyzed; an unknown diagonal matrix is used to represent the influence of the failed actuator on the dynamics characteristic; by taking into account the disturbance of external unknown disturbance torque, a nonlinear dynamics model of the partially failed four-rotor unmanned aerial vehicle actuator is acquired; and an analysis method based on Lyapunov is used to prove that the whole closed-loop system shown by a formula (12) is asymptotically stable, namely when time tends to be infinite, an attitude angle eta tends to a target attitude angle eta d. The method provided by the invention is mainly used for four-rotor unmanned aerial vehicle tolerant control.

The invention discloses a tracking fault-tolerant control method for a linear multi-agent system based on sliding mode control. A fault-tolerant control method based on the sliding mode control methodand adaptive control is proposed for the actuator fault of the linear multi-agent tracking system with external disturbance. Aiming at the actuator partial failure fault that may occur in the agent,the state error variable is defined according to the communication topology between multi-agents, the integral sliding mode surface is designed based on the error variable and sufficient conditions for sliding mode asymptotic stability are given. Then the unknown upper bound of the actuator fault is estimated by the adaptive method, and a sliding mode fault-tolerant controller is proposed to guarantee the tracking stability of the multi-agent system. The integral sliding mode surface is designed according to the state error variable between the multi-agents and the robustness of the system isenhanced, and the fault-tolerant control law having good fault-tolerant ability when the system has partial actuator failure fault and external disturbance is put forward and the tracking stability ofthe multi-agent system is improved. The fault-tolerant control method is used for fault tolerant control of the linear multi-agent system with the actuator failure fault and the external disturbance.

A fault tolerant controller system includes a first controller and a second controller. One of the first and second controllers designated as a primary controller for generating control signals intended to control actuation devices on a vehicle under non-fault operating conditions, and the other of the first and second controllers designated as a secondary controller generating control signals intended to control actuation devices on the vehicle. The actuation devices are responsive only to the designated primary controller. An error is detected in the primary controller and a message is transmitted from the faulty controller to the non-faulty controller identifying the error. The non-faulty controller is subsequently designated as the primary controller. The control signals including an identifier that identifies the non-faulty controller as the designated primary controller. In response to detecting the error, the faulty controller is reset to operate in a safe operating mode as the secondary controller.

The invention discloses a rigid spacecraft performer multi-fault diagnosis and fault tolerance control method. According to the method, the kinetic and dynamic model of a rigid spacecraft attitude control system is put forward, a fault model for existing of both the performance failure fault and the deviation fault of a rigid spacecraft is established, and then a fault detection observer adopting the adaptive threshold technology and a fault estimation observer based on the adaptive technology are respectively established so that online real-time detection and estimation of the fault time and the concrete situation of the fault can be realized, and finally a backstepping sliding mode fault tolerance controller is designed according to fault information established by the fault estimation observer. Attitude stabilization control of the rigid spacecraft under the condition of the performer efficiency damage and the deviation fault can be realized, and the influence of external disturbance on the system and the observers can also be considered in the design process. Besides, the fault detection observer and the fault estimation observer can be independently designed so that the engineering application can be more easily implemented.

The invention discloses a polyphase motor fault-tolerant control method and system based on a multi-neural-network inverse model in the field of motor control. The polyphase motor fault-tolerant control method comprises the following steps of: respectively acquiring a normal state inverse model and a fault state inverse module of a motor by adopting a neural network inverse model; selecting a corresponding inverse module and a current converter to be serially connected in front of a hysteresis current comparer by a current detection magnetic-chain observation inverse model switching module under a normal state or a fault state to obtain a constant pseudo-linear system; only considering to convert current of d axis and q axis of a stator, inversely output by the neural network after circuit-opening into four phases of reference current, and only adjusting phase relationships of the rest four phases of current; and when motor model parameters changes because the motor has a fault, approaching to a motor inverse system still accurately without the need of correcting control parameters of additional controllers again. According to the polyphase motor fault-tolerant control method and system disclosed by the invention, the adaptability of a fault-tolerant controller to the winding fault of the motor is improved, and the requirements and the circuit cost of an inverter power device are reduced; and the polyphase motor fault-tolerant control method and system have stronger fault tolerance and robustness.

The invention discloses a dynamic-actuator aircraft attitude distributed type fault-tolerant control system. The system comprises an actuator fault detection and identification unit, an auxiliary system based on an observer and an inversion fault-tolerant control algorithm based on order filtering. According to the distributed type fault-tolerant control system, the actuator fault detection and identification unit is used for obtaining fault information of actuators in real time, the self-adaptive sliding-mode observer is obtained according to an attitude angular speed ring, the observer has strong robustness, an undetermined or interference upper bound does not need to be known, and control surface damage fault information an interference information are both hidden in the observer; a fault-tolerant controller is obtained based on an observer model. Robustness fault-tolerant control over various faults of different types under the multi-fault condition is achieved, the fault-tolerant control system is applied to near-space vehicle attitude stable control and tracking control under the condition of faults of the actuators and the control surface, flying attitude robustness fault-tolerant control is achieved, and good control performance and effect are achieved.

The present invention relates to a spacecraft attitude fault-tolerant control method based on an iterative-learning disturbance observer. In order to solve the problem that actuator faults and external disturbances might occur during the attitude control process of the on-orbit operation of a spacecraft in the prior art, the invention provides an active fault-tolerant control method based on the iterative-learning observer. The method comprises the steps of firstly, establishing a dynamic model for the attitude control system of a spacecraft in considering the fault of an actuator in the attitude control system of the spacecraft and the external disturbance in the space of the spacecraft; secondly, estimating and designing a generalized disturbance torque of the iterative-learning disturbance observer composed of the actuator fault information and the external disturbance; finally, based on the estimated generalized interference, designing an active fault-tolerant controller. Based on the method, the stability of the attitude control system of the spacecraft, when the actuator of the spacecraft has a fault and the external disturbance exists in the space of the spacecraft, can be ensured. Meanwhile, the precision requirement of an actual control system is met. The method is strong in fault-tolerant ability and good in robustness for the external disturbance.

The invention provides a low-cost double-redundancy switch value PLC control system reliable fault-tolerant controller realization method which ensures continuous and reliable operation of the whole system when a main PLC controller fails, and adopts two conventional PLC controllers and a diagnosis decision logic module to form a double-redundancy reliable fault-tolerant controller. The first PLC controller serves as the main controller, and the second PLC controller serves as a standby controller; during normal operation, the main controller controls actual operation action of a controlled object, and the standby controller serves as a hot-standby redundant controller and outputs actual operation action not actually controlling the controlled object and is only used for monitoring the operation of the main controller; when the first PLC controller and an I / O pathway have severe faults, the second PLC controller is switched to be the main controller to maintain the normal operation of the controlled object; and after the PLC controllers having the severe fault recovers, a control flow is switched to serve as the hot-standby redundant controller of the current main controller to monitor the operation of the current main controller.

A method for fault tolerant controller readiness. Executing functions by a first controller operating in a primary status mode. Operating in a hot standby status mode by a second controller and mirroring the first controller by executing functions to operate as a redundant controller. Operating in a cold standby status mode by at least one backup controller under normal operating conditions. The second controller is reconfigured while operating under normal operating conditions from the hot standby status mode to the primary standby status mode if a failure occurs in the first controller. Reconfiguring the at least one backup controller operating under normal operating conditions from cold standby status mode to hot standby status mode to operate as a redundant controller in response to the reconfiguring the second controller from the hot standby status mode to the primary status mode.

A computer system includes a plurality of systems configured to be connected to each other by links and to operate synchronously each other. Each of said plurality of systems includes a fault tolerant controller, a CPU, a baseboard management controller and a plurality of hardware modules. The CPU is connected with the fault tolerant controller. The baseboard management controller is connected with the fault tolerant controller. The plurality of hardware modules is connected with the fault tolerant controller. When receiving a trouble which occurs in any of the plurality of systems, the fault tolerant controller outputs an interrupt regarding the trouble to at least one of the CPU and the baseboard management controller predetermined correspondingly to the trouble.

The invention provides a heterogeneous vehicle team fault-tolerant control method based on actuator fault and saturation. The method comprises the following steps: carrying out stress analysis on longitudinal movement of vehicles, and by combining actuator fault and saturation models, building a vehicle longitudinal dynamics model under the actuator fault and saturation; according to information of the vehicles, constructing a variable time interval strategy with fault information and a saturation index; and based on the constructed variable time interval strategy, establishing a proportional integral differential sliding mode surface and a coupling sliding mode surface; and selecting a proper Lyapunov function, designing a fault-tolerant controller and an adaptive updating rate, and proving the limited time stability of a system. Compared with a traditional variable time interval strategy, the variable time interval strategy with the fault information and the saturation index not only can solve the problem of non-zero initial interval error but also can expand critical traffic capacity.

The invention designs an actuator fault detection and identification unit based on multiple observers and a decentralized fault-tolerant control framework for a near space aircraft with disturbances and parameter uncertainty by considering the problem of robust fault-tolerant control after the aircraft has actuator and control surface faults. A system can acquire the fault information of an actuator in real time. A self-adaptive sliding mode observer is designed for an attitude angular velocity loop. A designed observer has strong robustness, does not need to know the upper bound of the uncertainty or the disturbances. The information of a control surface damage fault and the disturbance information are fully implied. A fault-tolerant controller is designed based on an observer model. Through a designed fault-tolerant control system, robust fault-tolerance control is realized under the conditions of various different types of faults and multiple faults. The designed method is respectively applied to posture stabilization control and tracking control of the near space aircraft in the presence of actuator and control surface faults, and flight posture robust fault-tolerant control is realized.

The invention relates to a robust fuzzy predictive fault-tolerant control method for an interval time-varying-delaying system. The robust fuzzy predictive fault-tolerant control method includes the following steps that firstly, a T-S fuzzy model of a nonlinear system is constructed; secondly, the constructed T-S fuzzy model is converted into an expanded T-S fuzzy model; thirdly, according to the constructed expanded T-S fuzzy model, a fault-tolerant controller that satisfies a control law is designed; and fourthly, a gain of the fault-tolerant controller is solved in a form of linear matrix inequality and the robust fuzzy predictive fault-tolerant control law is calculated. According to the robust fuzzy predictive fault-tolerant control method for the interval time-varying-delaying system,the robust fuzzy predictive fault-tolerant control method with time-delay dependence is provided according to the fact that a type of the industrial process has the characteristics such as nonlinearity, uncertainty, unknown disturbance, interval time-varying-delaying and partial actuator failure, thus the industrial process operates more smoothly and efficiently, the performance of a system is improved, and the fault tolerance of the system is increased.

The invention discloses a sliding-mode-based adaptive fault-tolerant control method for an uncertain time delay system. Considering that a quadrotor has an actuator fault under the conditions of inputtime delay and external disturbance, the fault-tolerant control method is proposed by combining adaptive control and sliding mode control. A time delay early predictor is designed to process the input time delay of the system; a matrix full-rank decomposition method and a sliding mode surface design method are adopted to solve the actuator fault problem; an adaptive sliding mode controller replaces a fault detection and isolation mechanism to automatically update and compensate for the actuator fault influence; the asymptotic stability of a closed-loop system is guaranteed with adaptive H2 performance. According to the method, by designing the adaptive sliding mode controller, the online adjustment of controller gain can be achieved, so that the proposed control law is optimal, the control precision and response speed of flight of the quadrotor are effectively improved, and a fault-tolerant controller design basis can be provided for the complex quadrotor with the actuator fault. Themethod is used for performing fault-tolerant control on the quadrotor with input time delay.

The invention discloses a fault-tolerant control method for a networked control system with time-varying delay. In view of conditions of parameter perturbation, time-varying delay, external disturbance and random failure happening to an actuator, a discrete time closed-loop nonlinear networked control system model is firstly built, a Lyapunov-Krasovskii function with the delay information is then built, a Lyapunov stability theory and a linear matrix inequality analysis method are used, sufficient condition for asymptotic stability of the nonlinear networked control system and existence of an H-infinity fault-tolerant controller are obtained, a Matlab LMI toolbox is used for solution, and a gain matrix for a non-fragile fault-tolerant controller is: K=K<->P; and conditions for optimizing the minimum disturbance rejection rate gamma is given, and the controller gain matrix K<*> optimized under the minimum disturbance rejection rate gammamin= square root of e is acquired. The condition of time-varying delay existing in the system is considered, the time-varying delay is analyzed and processed based on a free-weighting matrix method, and the conservation is reduced.

The invention discloses a non-linear multi-unmanned-aerial-vehicle-system fault-tolerance formation control method with consideration of random disturbance. The method comprises the following steps that: a non-linear random dynamic model of an unmanned aerial vehicle is constructed and output measurement data of each unmanned aerial vehicle are obtained based on the model as well as reference track given information and information interaction between neighboring unmanned aerial vehicles; on the basis of the data, a distributed state observer and an adaptive fault estimator are designed for each unmanned aerial vehicle and on-line estimation is carried out on state information and fault information of the unmanned aerial vehicle; a fault-tolerant controller is designed by using the real-time state and the fault estimation information, so that a system formation error, a state estimation error, and a fault estimation error are converged to a controllable error bound; and then correlated parameters of the distributed state observer, the adaptive fault estimator, and the fault-tolerant controller are determined. According to the invention, a problem of fault estimation and fault-tolerance formation control of a non-linear unmanned aerial vehicle group with existence of interference, noises and channel disturbance can be solved effectively.

The invention provides a heterogeneous fleet fault tolerance control method based on a variable time interval strategy. The method comprises the following steps of carrying out force analysis on longitudinal motion of vehicles and combining an actuator fault model to establish a vehicle longitudinal dynamics model under an actuator fault; constructing the variable time interval strategy with a lower boundary of fault information according to information of the vehicles; based on the constructed variable time interval strategy, establishing a proportional integral differential sliding mode surface and a coupled sliding mode surface; and selecting an appropriate Lyapunov function to design a fault-tolerant controller and an adaptive update rate, and proving finite time stability of a system.Traffic flow stability is proved based on the variable time interval strategy with the lower boundary of the fault information. Queue stability is proved based on the proportional integral differential sliding mode surface and the coupled sliding mode surface. Compared with a traditional variable time interval strategy, by using the technical scheme of the invention, a problem of a non-zero initial spacing error can be solved, and a critical traffic capacity can be increased.

The invention uses the idea of hierarchical structure control optimization to provide a manipulator actuator fault tolerant control system based on a double-layer structure and a method thereof, which belongs to the technical field of automatic control. In order to reduce the computational complexity and improve the instantaneity, a discrete system model under an actuator fault is established in an expansion manner through Taylor series. An FDD unit is designed to initiatively deal with a fault problem. The estimated fault information is introduced into a fault model to realize active fault tolerance. Uncertainties of the actual system are considered. A feedback correction mechanism is used for compensation. A manipulator fault tolerant controller is composed of a trajectory planning layer and a tracking control layer. According to different control objectives of each layer, a controller is designed separately, which is more specific to the problem. The fault tolerant control of the double-layer structure can deal with the existing system constraints, has strong robustness, can effectively solve the problem of the constant deviation fault of a complex manipulator actuator, and ensures the stability and the control performance of the whole system.

The invention discloses a double-layer Kalman filter-based intermittent failure diagnosis and active fault-tolerant control method. The method includes the following steps that: a linear discrete timesystem model on which an intermittent failure occurs is established; double-layer Kalman filter-based intermittent failure diagnosis is performed; and fault-tolerance control for the intermittent failure is performed. The invention provides the above method for one type of linear discrete time systems on which intermittent failures occur. With the method adopted, the occurrence time and disappearance time of the intermittent failure can be accurately and effectively detected under the condition of noise disturbance, and the solving problem of the intermittent failure is converted into the optimization problem of minimum variance unbiased estimation under an intermittent failure gain constraint, so that an optimal estimation value can be obtained accurately; and a failure diagnosis processis combined with the design process of a fault-tolerant controller, so that the real-time performance and rapidity of fault-tolerant control can be ensured. The active fault-tolerant controller is simple in structure and is easy to implement, and can ensure the stable operation of the system even when the intermittent failure occurs.

The invention discloses a fault tolerant control method for a multi-agent system based on adaptive sliding mode control. The failure of the actuator in the second-order nonlinear multi-agent system isconsidered, combined with adaptive control and sliding mode control, a fault-tolerant control method is proposed. The consistency error variable is defined according to the relative state informationbetween the agents, and the sliding mode surface is designed based on the consistency error variable, and the sufficient conditions for the asymptotic stability are given. The method based on adaptive boundary estimation estimates the upper bound of the fault, which ultimately constitutes a complete sliding mode fault-tolerant controller. The method simplifies the complexity of the problem by designing a sliding surface based on the consistency error variable; combined with the advantages of adaptive control and sliding mode control, the designed fault-tolerant control law has good fault tolerance. The method is used for fault tolerant control of a multi-agent system with actuator partial failure.

The invention discloses a spacecraft adaptive fault-tolerant attitude tracking control method with specified tracking performance. The method comprises steps: a kinematic model and a dynamic model ofthe spacecraft are built based on a certain amount of external disturbance on the spacecraft; based on the dynamic model of the spacecraft and based on unknown system fault on a spacecraft executor, an unknown actuator fault system model is built; based on the unknown actuator fault system model, a conversion error and a performance function are designed, and thus, the tracking error of the spacecrafts tends to be arbitrarily small minimum residual set under the specified tracking performance and the maximum overshoot; and the effects of the fault are compensated by estimating the boundary offault uncertainty, an adaptive fault-tolerant controller is designed, and the system tends to asymptotic stability. The method of the invention realizes high-precision system attitude tracking controlon the premise of ensuring the robustness of the system.