Attitude stabilization of a rigid spacecraft with actuator delay and fault

Abstract

Time delays and actuator faults are phenomena which are frequently encountered in practical control systems and are found to have significant effects on the performance of operation and control. It is shown that even a very small delay may destabilize the spacecraft system. Therefore, besides considering the effects of modelling uncertainties and external disturbances, time delay and actuator fault effects should be properly handled in the spacecraft to achieve reliable and accurate control. This paper describes a simple and effective method to attitude stabilize a spacecraft. The proposed method works by augmenting a backstepping controller with a modified extended state observer-based feedforward control law. The backstepping control is used to compensate for an unknown delay in the inputs, while the feedforward term attenuates the effects of modelling uncertainties, external disturbances and actuator faults. In particular, actuator faults, modelling uncertainties and external disturbances are viewed as unknown nonlinear functions of the measurable state variables, estimated using a modified extended state observer, and then compensated for. The effectiveness of the proposed control algorithm is analytically authenticated and verified via simulation studies.

Adaptive neural fault-tolerant control for output-constrained attitude tracking of unmanned space vehicles

“…The first method is the adaptive control by using the adaptation mechanism to accommodate the actuator faults (Cai et al, 2008; Han et al, 2016; Shen et al, 2015; Smaeilzadeh and Golestani, 2019). The second method is the robust control by using the disturbance observer or extended state observer to estimate the actuator faults (Guo and Chen, 2019; Li et al, 2017, 2019; Qiao et al, 2018; Safa et al, 2018; Xiao et al, 2014, 2015). The third method is the intelligent control by using the NNs or fuzzy logic systems to approximate the actuator faults (Alsaade et al, 2022; Hu et al, 2020; Huo et al, 2015; Lu et al, 2019; Song et al, 2019; Zou and Kumar, 2011).…”

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

“…In Cao et al (2016), an adaptive FTC based on DOBC was studied for a rigid satellite with both time-varying actuator faults and multiple disturbances. In Safa et al (2018), an attitude control scheme was proposed for a rigid spacecraft with actuator delay and fault by augmenting a backstepping controller with a modified extended state observer-based controller. For flexible spacecraft with faulty thrusters, an adaptive fault-tolerant sliding mode controller was investigated with application to attitude maneuvering Mirshams et al (2014).…”

Velocity pointing error reduction for symmetric spinning spacecraft via a two-burn scheme

“…Spin stabilized control is a simple structural method for use in orbital maneuvers of spacecraft (Kong et al, 2016; Morozov et al, 2016; Yang et al, 2017). The criteria in the spinning thrusting problem have been less energy utilization and optimum maneuver execution (McDonald et al, 2014; Safa et al, 2018). In this regard, with a higher spin rate, more energy is used for increasing the spin rate and controlling the spin axis; conversely, with a lower spin rate, the satellite attitude will be more affected by transverse torques arising from the misaligned thrust (Hu et al, 2017; Javorsek et al, 2003; Longuski et al, 2005; Slavinskis et al, 2014).…”