scholarly journals Vibration Suppression and Fault-Tolerant Attitude Control for Flexible Spacecraft with Actuator Faults and Malalignments

2021 ◽  
pp. 107290
Author(s):  
Muhammad Noman Hasan ◽  
Muhammad Haris ◽  
Shiyin Qin
Keyword(s):  
Attitude Control ◽  
Vibration Suppression ◽  
Fault Tolerant ◽  
Flexible Spacecraft ◽  
Actuator Faults

Robust constrained fault-tolerant attitude control for flexible spacecraft

2017 ◽  
Vol 232 (16) ◽  
pp. 3011-3023 ◽  
Author(s):  
Haihui Long ◽  
Jiankang Zhao
Keyword(s):  
Attitude Control ◽  
Fault Tolerant ◽  
External Disturbance ◽  
Input Saturation ◽  
Flexible Spacecraft ◽  
Disturbance Attenuation ◽  
Actuator Faults ◽  
Partial Loss ◽  
Unknown Parameters ◽  
Disturbance Model

In this paper, robust constrained fault-tolerant attitude controllers are proposed for flexible spacecraft subjected to external disturbance, model uncertainty, input saturation, and actuator faults. Three types of actuator faults of spacecraft, i.e. partial loss of effectiveness, stuck fault, and outage fault, are modeled explicitly. To handle these actuator faults, a significant lemma is proposed and rigorous proof is conducted at length. By introducing two e-modification parameter update laws to online estimate the unknown parameters caused by actuator faults, constrained fault-tolerant attitude controllers of flexible spacecraft are designed to accommodate these faults without the need of any prior information about these faults. The proposed controllers can achieve the disturbance attenuation in the sense of [Formula: see text] gain. The effectiveness of the proposed algorithms is assessed through numerical simulations.

Active Control Comparison of Vibration in Flexible Spacecraft Using Different Active Friction Joints

2013 ◽  
Vol 446-447 ◽  
pp. 1160-1164
Author(s):  
Sahar Bakhtiari Mojaz ◽  
Hamed Kashani
Keyword(s):  
Energy Dissipation ◽  
Attitude Control ◽  
Vibration Suppression ◽  
Excitation Amplitude ◽  
Step Function ◽  
Flexible Spacecraft ◽  
Control Effort ◽  
Stick Slip ◽  
Control Comparison ◽  
Frictional Joints

Vibration properties of most assembled mechanical systems depend on frictional damping in joints. The nonlinear transfer behavior of the frictional interfaces often provides the dominant damping mechanism in structure and plays an important role in the vibratory response of it. For improving the performance of systems, many studies have been carried out to predict measure and enhance the energy dissipation of friction. This paper presents a new approach to vibration reduction of flexible spacecraft with enhancing the energy dissipation of frictional dampers. Spacecraft is modeled as a 3 degree of freedom mass-spring system which is controlled by a lead compensator and System responses to step function evaluated. Coulomb and Jenkins element has been used as vibration suppression mechanisms in joints and sensitivity of their performance to variations of spacecraft excitation amplitude and damper properties is analyzed. The relation between frictional force and displacement derived and used in optimization of control performance. Responses of system and control effort needed for the vibration control are compared for these two frictional joints. It is shown that attitude control effort reduces, significantly with coulomb dampers and response of system improves. On the other hand, due to stick-slip phenomena in Jenkins element, we couldn’t expect the same performance from Jenkins damper.

Nonlinear Attitude Control of Flexible Spacecraft With Scissored Pairs of Control Moment Gyros

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Jixiang Fan ◽  
Di Zhou
Keyword(s):  
Attitude Control ◽  
Vibration Suppression ◽  
Large Angle ◽  
Singularity Analysis ◽  
Flexible Spacecraft ◽  
Attitude Motion ◽  
Nonlinear Feedback ◽  
Nonlinear Controller ◽  
Control Moment ◽  
Steering Law

Dynamic equations describing the attitude motion of flexible spacecraft with scissored pairs of control moment gyroscopes are established. A nonlinear controller is designed to drive the flexible spacecraft to implement three-axis large-angle attitude maneuvers with the vibration suppression. Singularity analysis for three orthogonally mounted scissored pairs of control moment gyros shows that there exists no internal singularity in this configuration. A new pseudo-inverse steering law is designed based on the synchronization of gimbal angles of the twin gyros in each pair. To improve the synchronization performance, an adaptive nonlinear feedback controller is designed for each pairs of control moment gyros by using the stability theory of Lyapunov. Simulation results are provided to show the validity of the controllers and the steering law.

Adaptive fault tolerant attitude control of flexible satellites based on Takagi-Sugeno fuzzy disturbance modeling

2020 ◽  
Vol 42 (9) ◽  
pp. 1712-1723
Author(s):  
Songyin Cao ◽  
Bin Hang
Keyword(s):  
System Reliability ◽  
Attitude Control ◽  
Disturbance Observer ◽  
Fault Tolerant ◽  
Actuator Faults ◽  
Attitude Control System ◽  
Fault Accommodation ◽  
Modeling Technology ◽  
Takagi Sugeno ◽  
Fuzzy Disturbance Observer

This paper investigates the fault tolerance problem of flexible satellites subject to multiple disturbances and actuator faults. An adaptive fault tolerant control (FTC) approach based on disturbance observer is presented for attitude control system (ACS) with actuator faults, elastic modal, modeling error and environmental disturbance torque in this paper. Different from some existing disturbance observer-based control (DOBC) approaches, Takagi-Sugeno (T-S) fuzzy modeling technology is applied to describe the elastic modal. A fuzzy disturbance observer and a fault diagnosis observer are constructed to estimate the elastic modal and actuator fault, respectively. Then, based on fault accommodation and DOBC, a new adaptive FTC strategy is designed to achieve the anti-disturbance performance and improve the system reliability. Finally, the efficiency of the proposed FTC scheme is verified by simulation results.

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