A novel learning observer-based fault-tolerant attitude control for rigid spacecraft

Cao, Teng; Gong, Huajun; Cheng, Peng; Xue, Yixuan

doi:10.1016/j.ast.2022.107751

Cited by 20 publications

(8 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For simulation, the initial values of indicator function and failure parameter estimates are chosen as: χ 1i ð0Þ = 1, i = 1, 2, 3, 4, χ 2i ð0Þ = 0, χ 3i ð0Þ = 0, i = 1, 2, 3; θ 1ðiÞ ð0Þ = ½0, 0 T , andθ 4ðiÞ ð0Þ = ½0, 0 T . Basis functions of failure model (10) and disturbance model ( 4) are ϖ 1 ðtÞ = ϖ 4 ðtÞ = ½1, sin ð0:25tÞ T ∈ R 2 and ϖ d1 = ϖ d2 = ϖ d3 = ½1, sin ð0:01tÞ, cos ð0:01tÞ T ∈ R 3 .…”

Section: Simulation Conditionsmentioning

confidence: 99%

“…Excellent overviews were provided by the survey papers [8,9] to make FTC designs for spacecraft control system. In [10], a fault tolerant control scheme was proposed for spacecraft attitude stabilization by integrating learning observer and backstepping control design. A novel adaptive event-triggered controller was designed to handle disturbances, model uncertainties, actuator failures, and limited communication, simulta-neously [11].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

A Modified Robust Adaptive Fault Compensation Design for Spacecraft with Guaranteed Transient Performance

Yao

Yang

2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

A modified, robust adaptive fault compensation design is proposed for rigid spacecraft systems with uncertain actuator failures and unknown disturbances. The feedback linearization method is first introduced to linearize the nonlinear dynamics, and a model-reference adaptive controller is designed to suppress the unknown external disturbances and stabilize the linearized system. Then, a composite adaptive controller is developed by integrating multiple controllers designed for the corresponding actuator failure conditions, which can handle the essentially multiple uncertainties (failure time, values, type, and failure pattern) of actuator failures simultaneously. To further improve the transient performance problem in the failure compensation control, an H∞ compensator is introduced as an additional item in the basic controller to attenuate the adverse effects on tracking performance caused by parameter estimation errors. From the theoretical analysis and simulation results, it is obvious that the designed scheme can not only guarantee the stability of the closed-loop system is stable and asymptotical tracking properties for a given reference signal but also greatly improve the transient performance of the spacecraft system during the process of failure compensation.

show abstract

Section: Simulation Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Modified Robust Adaptive Fault Compensation Design for Spacecraft with Guaranteed Transient Performance

Yao

Yang

2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…Inspired by the previous learning observer design [24], we designed an improved learning observer design scheme for the efficiency factor of the actuator. The actuator loss of effectiveness fault E(t) is a diagonal matrix, and E(t)u in Equation ( 2) can be written as…”

Section: Design Of Learning Observermentioning

confidence: 99%

Observer-Based Predefined-Time Attitude Control for Spacecraft Subject to Loss of Actuator Effectiveness

Cao¹,

Gong²,

Han³

2022

Processes

Self Cite

View full text Add to dashboard Cite

The predefined-time tracking problem of spacecraft attitude systems with loss of actuator effectiveness and lumped disturbance including the external disturbance and system uncertainty is studied. In order to obtain the estimation of the actuator efficiency factor more quickly and accurately, a robust learning observer is designed. Based on the fault reconstruction information of the learning observer and the predefined-time stability lemma, a predefined-time tracking fault-tolerant control scheme is proposed for the faulty spacecraft attitude system. The stability of the learning observer and the whole control system is verified by the Lyapunov stability theory. Finally, the effectiveness and advantages of the proposed scheme are illustrated by simulation results including comparisons with existing works.

show abstract

“…Moreover, by combining the adaptive algorithms with the sliding mode controllers, fast convergence of the FTC in finite time has been achieved (Sadigh et al., 2023; Xia et al., 2019), and the performances of the closed‐loop FTC were correspondingly enhanced. In addition to the above methods, fault estimation observers such as augmented observer (Qian et al., 2020), learning observer (Cao et al., 2022), and extended state observer (B. Li et al., 2017), have combined with the adaptive finite time controllers to implement the adaptive finite time composite FTC (Ali et al., 2023). These finite time control methods provide excellent FTC performance for ACSs of satellites but still need to be improved.…”

Section: Introductionmentioning

confidence: 99%

Neuro‐Adaptive Finite Time Composite Fault Tolerant Control for Attitude Control Systems of Satellites

Wang,

Liang,

Yang

et al. 2023

Radio Science

View full text Add to dashboard Cite

An adaptive finite time composite fault tolerant control strategy based on an optimized neural network for Attitude control systems (ACSs) of satellites is proposed considering the state time‐varying delays, concurrent actuator and sensor faults, system uncertainties, modelable external disturbance and operating noise. An uncertain time‐varying state space model for ACSs of satellites is established, and sensor faults are equivalent to actuator‐like faults. A disturbance observer is designed for estimating the modelable external disturbance, and an improved dwarf mongoose optimization (DMO) algorithm based on the Levy flight distribution is utilized to optimize the basis function of hyperbasis function neural networks to better estimate the augmented actuator faults that include the actuator fault and the actuator‐like fault. Furthermore, an adaptive finite time composite fault‐tolerant controller is proposed, which includes the delay‐dependent feedback control law, disturbance estimation based‐disturbance compensation law and the adaptive fault compensation law based on the augmented fault estimation using the improved DMO‐hyper basis function neural network. The finite time boundness of the close‐loop dynamics to the uncertainties, operating noise, and augmented actuator faults and the robustness of the measurement to the uncertainties, operating noise and augmented actuator faults are analyzed, and the observer and controller design is formulated as the linear matrix inequalities. Simulation examples for ACSs in different working conditions are considered to exhibit the proposed method's effectiveness.

show abstract

A novel learning observer-based fault-tolerant attitude control for rigid spacecraft

Cited by 20 publications

References 38 publications

A Modified Robust Adaptive Fault Compensation Design for Spacecraft with Guaranteed Transient Performance

A Modified Robust Adaptive Fault Compensation Design for Spacecraft with Guaranteed Transient Performance

Observer-Based Predefined-Time Attitude Control for Spacecraft Subject to Loss of Actuator Effectiveness

Neuro‐Adaptive Finite Time Composite Fault Tolerant Control for Attitude Control Systems of Satellites

Contact Info

Product

Resources

About