Robust fault-tolerant attitude control of spacecraft using hybrid actuators

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yiqi Xu
Keyword(s):  
Attitude Control ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
Spacecraft Attitude Control ◽  
External Disturbances ◽  
Content Type ◽  
Virtual Control ◽  
Smooth Switching ◽  
High Level ◽  
Hybrid Actuator

Purpose This paper aims to address the spacecraft attitude control problem using hybrid actuators in the presence of actuator saturation, uncertainties and faults, inertia uncertainties and external disturbances. Design/methodology/approach A hybrid actuator configuration is used where thrusters are engaged for rapid attitude maneuvers, while reaction wheels (RWs) are used for fine pointing. Findings The key advantages are two-fold: a finite-time high-level controller is designed to produce the three-axis virtual control torques; an online robust control allocation (RobCA) scheme is proposed to redistribute virtual control signals to the actuators with taking into account the actuator saturation, uncertainties and faults; and the RobCA scheme allows a smooth switch between thrusters and RWs, which handles the inaccuracy problem of thrusters and saturation problem of RWs. Practical implications An online RobCA algorithm is designed that maps the total control demands onto individual actuator settings and allows a smooth switch between thrusters and RWs. Simulation results show the effectiveness of the proposed control strategy. Originality/value This work may be used on modern space missions, which impose higher requirements on smooth switching of spacecraft thrusters and RWs.

Spacecraft attitude control with mutating orbital rate and actuator fading under Markovian jump framework

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Chengxi Zhang ◽  
Hui-Jie Sun ◽  
Jin Wu ◽  
Zhongyang Fei ◽  
Yu Jiang ◽  
...  
Keyword(s):  
Control Problem ◽  
Attitude Control ◽  
Algorithm Design ◽  
Control Policy ◽  
Spacecraft Attitude ◽  
Actuator Faults ◽  
Spacecraft Attitude Control ◽  
Dynamics Model ◽  
Markovian Jump ◽  
Content Type

Purpose This paper aims to study the attitude control problem with mutating orbital rate and actuator fading. Design/methodology/approach To avoid malicious physical attacks and hide itself, the spacecraft may irregularly switch its orbit altitude within a specific range, which will bring about variations in orbital rate, thereby causing mutations in the attitude dynamics model. The actuator faults will also cause changes in system dynamics. Both factors affect the control performance. First, this paper determines the potential switching orbits. Then under different conditions, design controllers that can accommodate actuator faults according to the statistical law of actuator fading. Findings This paper, to the best of the authors’ knowledge, for the first time, introduces the Markovian jump framework to model the possible unexpected mutating of orbital rate and actuator fading of spacecraft and then designs a novel control policy to solve the attitude control problem. Practical implications This paper also provides the algorithm design processes in detail. A comparative numerical simulation is given to verify the effectiveness of the proposed algorithm. Originality/value This is an early solution for spacecraft attitude control with dynamics model mutations.

Reset and prescribed performance approach to spacecraft attitude regulation

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Chengxi Zhang ◽  
Peng Dong ◽  
Henry Leung ◽  
Jin Wu ◽  
Kai Shen
Keyword(s):  
Attitude Control ◽  
Control Policy ◽  
Parameter Tuning ◽  
High Gain ◽  
Performance Tuning ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Content Type ◽  
Exogenous Disturbances ◽  
Reset Control

Purpose This paper aims to investigate the attitude regulation for spacecraft in the presence of time-varying inertia uncertainty and exogenous disturbances. Design/methodology/approach The high gain approaches are typically used in existing researches for theoretical advantages, bringing better performance but sensitive to parameter selection, making the controller conservative. A reset-control policy is presented to achieve the spacecraft attitude control with easy control parameter tuning. Findings The reset-control policy guarantees satisfying control performance despite using performance tuning function and saturation function besides reducing the conservativeness of the controller, thus reducing the effort in tuning control parameters. Originality/value Notably, the adaptive function owns a reset mechanism, which is reset to a preset condition when the controlled variable crosses zero. The mathematical analysis also shows the system trajectory can converge to a set centered at the origin.

Distributed robust H∞ adaptive fault-tolerant control of amorphous and flat air-to-ground wireless self-organizing network system

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Zhifang Wang ◽  
Jianguo Yu ◽  
Shangjing Lin ◽  
Junguo Dong ◽  
Zheng Yu
Keyword(s):  
Flight Control ◽  
Control Algorithm ◽  
Ad Hoc ◽  
Fault Tolerant ◽  
Fault Tolerant Control ◽  
Integrated System ◽  
External Disturbances ◽  
Content Type ◽  
Actuator Failures ◽  
Wireless Signal

Purpose The paper takes the air-ground integrated wireless ad hoc network-integrated system as the research object, this paper aims to propose a distributed robust H∞ adaptive fault-tolerant control algorithm suitable for the system to distribute to solve the problem of control and communication failure at the same time. Design/methodology/approach In the paper, the authors propose a distributed robust H∞ adaptive fault-tolerant control algorithm suitable for the air-ground integrated wireless ad hoc network-integrated system. Findings The results show that the integrated system has good robustness and fault tolerance performance indicators for flight control and wireless signal transmission when confronted with external disturbances, internal actuator failures and wireless network associated failures and the flight control curve of the quadrotor unmanned aerial vehicle (UAV) is generally smooth and stable, even if it encounters external disturbances and actuator failures, its fault tolerance performance is very good. Then in the range of 400–800 m wireless communication distance, the success rate of wireless signal loop transmission is stable at 80%–100% and the performance is at least relatively improved by 158.823%. Originality/value This paper takes the air-ground integrated wireless ad hoc network-integrated system as the research object, based on the robust fault-tolerant control algorithm, the authors propose a distributed robust H∞ adaptive fault-tolerant control algorithm suitable for the system and through the Riccati equation and linear matrix inequation method, the designed distributed robust H∞ adaptive fault-tolerant controller further optimizes the fault suppression factor γ, so as to break through the limitation of only one Lyapunov matrix for different fault modes to distribute to solve the problem of control and communication failure at the same time.

Modelling and robust attitude trajectory tracking control of 3-DOF four rotor hover vehicle

2017 ◽  
Vol 89 (1) ◽  
pp. 87-98 ◽  
Author(s):  
Rooh ul Amin ◽  
Aijun Li
Keyword(s):  
Robust Stability ◽  
Trajectory Tracking ◽  
Attitude Control ◽  
Tracking Control ◽  
Robust Performance ◽  
External Disturbances ◽  
Trajectory Tracking Control ◽  
Content Type ◽  
Uncertainty Model ◽  
And Performance

Purpose The purpose of this paper is to present μ-synthesis-based robust attitude trajectory tracking control of three degree-of-freedom four rotor hover vehicle. Design/methodology/approach Comprehensive modelling of hover vehicle is presented, followed by development of uncertainty model. A μ-synthesis-based controller is designed using the DK iteration method that not only handles structured and unstructured uncertainties effectively but also guarantees robust performance. The performance of the proposed controller is evaluated through simulations, and the controller is also implemented on experimental platform. Simulation and experimental results validate that μ-synthesis-based robust controller is found effective in: solving robust attitude trajectory tracking problem of multirotor vehicle systems, handling parameter variations and dealing with external disturbances. Findings Performance analysis of the proposed controller guarantees robust stability and also ensures robust trajectory tracking performance for nominal system and for 15-20 per cent variations in the system parameters. In addition, the results also ensure robust handling of wind gusts disturbances. Originality/value This research addresses the robust performance of hover vehicle’s attitude control subjected to uncertainties and external disturbances using μ-synthesis-based controller. This is the only method so far that guarantees robust stability and performance simultaneously.

Fault-tolerant control of spacecraft attitude regulation: a concise adaptive dual-mode scheme

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yu Lu ◽  
Pengpeng Ye ◽  
Ming-Zhe Dai ◽  
Jin Wu ◽  
Chengxi Zhang
Keyword(s):  
Fault Diagnosis ◽  
Attitude Control ◽  
Control Algorithm ◽  
Fault Tolerant ◽  
Spacecraft Attitude ◽  
Attitude Control System ◽  
Dual Mode ◽  
Content Type ◽  
Control Scheme ◽  
Adaptive Backstepping Design

Purpose This paper aims to address the spacecraft attitude regulation problem in the presence of extrinsic disturbances and actuator faults. Design/methodology/approach Based on adaptive backstepping design technique, a new concise adaptive dual-mode control scheme is proposed, which can either use the fault information detected by fault diagnosis mechanisms or switch to the fault-unknown mode when the fault diagnosis information is non-existent for control signal generation. These two modes share an adaptive mechanism that reduces the complexity of the algorithm. Findings The new fault-tolerant attitude control algorithm can accommodate both modes with and without fault diagnosis mechanisms. Originality/value The proposed algorithm in this paper can be applied to both cases when the attitude control system is equipped with or without fault diagnosis capability. This also enhances the robustness of attitude control algorithm. This study performs numerical simulations and verifies that the algorithm could effectively adapt to both modes.

Adaptive fault-tolerant attitude control for reentry vehicle involving actuator saturation

2018 ◽  
Vol 233 (11) ◽  
pp. 3968-3982
Author(s):  
Ming-Zhou Gao ◽  
Jian-Yong Yao
Keyword(s):  
Attitude Control ◽  
Control Method ◽  
Actuator Saturation ◽  
Fault Tolerant ◽  
Time Varying ◽  
Actuator Fault ◽  
Control Methods ◽  
Attitude Control System ◽  
Reentry Vehicle ◽  
Unknown Disturbances

Many control methods are used in attitude control of reentry vehicle, such as optimal control and classical control methods. However, those control laws may not work effectively if the attitude system is confronted with actuator faults and saturation. This paper proposes an adaptive fault tolerant attitude control method for the reentry vehicle's attitude control system, by combining the radial basis function network technology with adaptive fault tolerant control method. We simultaneously considered actuator fault, actuator saturation, time varying unknown disturbances and uncertainties when designing the control method. First, we set up the reentry attitude dynamic model concerning actuator fault; second, a finite-time H∞ adaptive fault-tolerant attitude controller is introduced to deal with the actuator fault, saturation, unknown disturbances and uncertainties of the reentry vehicle system; we proved the stability of our proposed adaptive attitude fault-tolerant controller through the Lyapunov function and the linear matrix inequality method. Finally, the effectiveness of such adaptive fault-tolerant control method has been identified by numerous simulation results. The simulation results show that our proposed method can not only effectively deal with actuator fault in the attitude control system, but also has very good robustness for actuator saturation, time varying unknown disturbances and uncertainties.

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