Adaptive super twisting vibration control of a flexible spacecraft with state rate estimation

Malekzadeh, Maryam; Karimpour, Hossein

doi:10.1016/j.jsv.2018.02.037

Cited by 12 publications

(19 citation statements)

References 26 publications

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“…The numerical simulation is conducted by using MATLAB software. In this simulation, the system parameters are selected as follows Malekzadeh and Karimpour (2018)…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The initial attitudes of spacecraft are θ=[10,20,30]T , and the desired attitudes of the spacecraft are given through boldθd=[110,80,130]T The disturbance torques acting on the spacecraft are assumed as follows Malekzadeh and Karimpour (2018)…”

Section: Simulation Resultsmentioning

confidence: 99%

“…For comparison, the combined control of the second method in this study is compared with the designed STA control of the same method in Malekzadeh and Karimpour (2018), where the system parameters are arranged similar to those of Malekzadeh and Karimpour (2018), expressed as…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Flexible spacecraft is made of a rigid body with attached appendages of length l i at a distance a i from the main body. (Subtitle i varies from 1 to n, where n is the total number of panels) The flexible spacecraft dynamic equation is obtained by implementing Lagrange’s formulation, Malekzadeh and Karimpour (2018) as followswhere ω , η , and τ are the angular velocity, the modal coordinates, and the control torque, respectively. The further details of (1) are expressed in Appendix A.…”

Section: Spacecraft Dynamic Equationmentioning

confidence: 99%

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Finite-time disturbance observer based-control of flexible spacecraft

Hajnorouzali

Malekzadeh

Ataei

2021

Journal of Vibration and Control

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This paper aims to design an attitude controller for a flexible spacecraft under external disturbance and uncertainty. The spacecraft’s attitude is controlled by a super twisting controller based on a disturbance observer. This paper’s spacecraft system is non-minimum phase since mode-shapes are included in the output; thus, the following four methods are designed to compensate for the constraint: (1) The output redefinition method, where outputs are redefined as a combination of mode-shapes and quaternions. (2) The flexible spacecraft is controlled without measuring the mode-shapes, and only the quaternion parameters are selected as the output. (3) An advanced sliding surface is proposed, in which the mode-shapes are considered in the sliding surface. (4) The difference between flexible and rigid spacecraft dynamics is considered as disturbance, and its effect on the system is compensated. The finite-time stability of the closed-loop system is proved by leveraging the Lyapunov theory. The numerical simulation illustrates the closed-loop system’s effectiveness in terms of robustness compared to the existing controller and the four mentioned methods.

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“…The numerical simulation is conducted by using MATLAB software. In this simulation, the system parameters are selected as follows Malekzadeh and Karimpour (2018)…”

Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Spacecraft Dynamic Equationmentioning

confidence: 99%

See 2 more Smart Citations

Finite-time disturbance observer based-control of flexible spacecraft

Hajnorouzali

Malekzadeh

Ataei

2021

Journal of Vibration and Control

Self Cite

View full text Add to dashboard Cite

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“…The STA is also applied in the hypersonic vehicle in [27] and [28]. An adaptive super-twisting algorithm is incorporated with its observer counterpart on the system under consideration to get reliable attitude and vibration control in the presence of sensor noise and momentum coupling [29]. An adaptive twisting algorithm is proposed for systems subject to disturbances with unknown bounds and it can also avoid the aggressive chattering [30].…”

Section: Introductionmentioning

confidence: 99%

Finite-Time Super-Twisting Controller Based on SESO Design for RLV Re-Entry Phase

Chen

Peng

et al. 2019

IEEE Access

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In this paper, an improved extended state observer (ESO) based on sigmoid function and a finite-time convergence attitude controller are designed for reusable launch vehicle (RLV) in the re-entry phase. First, a control-oriented model (COM) of the RLV is established. According to the singular perturbation theory, the RLV control system is divided into an outer-loop and inner-loop subsystems. Second, a sigmoid function ESO (SESO) is proposed to estimate the model uncertainties and external disturbance caused by the large attitude maneuver and complicated external environment during the RLV re-entry phase. The continuous differentiable sigmoid function has the significant ability in noise suppression. By selecting the proper Lyapunov function, the stability of the SESO is proved. Then, based on the sliding mode control (SMC) theory, an improved multivariable super-twisting high-order sliding mode controller is designed. The finite-time convergence for the whole system is proven by the Lyapunov function technology. Finally, a 6-degree-of-freedom (6-DOF) RLV model is utilized to simulate to verify the effectiveness and robustness of the proposed control scheme. INDEX TERMSReusable launch vehicle, extended state observer, sliding mode control, super-twisting, re-entry phase.

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A novel output redefinition method for nonlinear H_∞ attitude stabilization of a flexible spacecraft

Majid Esmaeilzadeh,

Sadegh Zeyghami

2023

Asian Journal of Control

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This paper addresses a novel output redefinition method for the nonlinear attitude stabilization problem of a flexible spacecraft. As an idea, the flexible appendage tip‐point can be selected as attitude output which may improve attitude pointing accuracy. However, it makes the system non‐minimum phase. The output redefinition method is an effective method to make the system minimum phase. In this paper, a novel output redefinition is proposed to overcome the non‐minimum phase property such that it improves the attitude control system performance. Then, a nonlinear controller is designed based on back‐stepping approach and a modal observer. The simulation results show the effectiveness of the proposed method in the presence of model uncertainties and environmental disturbances.

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Adaptive super twisting vibration control of a flexible spacecraft with state rate estimation

Cited by 12 publications

References 26 publications

Finite-time disturbance observer based-control of flexible spacecraft

Finite-time disturbance observer based-control of flexible spacecraft

Finite-Time Super-Twisting Controller Based on SESO Design for RLV Re-Entry Phase

A novel output redefinition method for nonlinear H_∞ attitude stabilization of a flexible spacecraft

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Adaptive super twisting vibration control of a flexible spacecraft with state rate estimation

Cited by 12 publications

References 26 publications

Finite-time disturbance observer based-control of flexible spacecraft

Finite-time disturbance observer based-control of flexible spacecraft

Finite-Time Super-Twisting Controller Based on SESO Design for RLV Re-Entry Phase

A novel output redefinition method for nonlinear H∞ attitude stabilization of a flexible spacecraft

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A novel output redefinition method for nonlinear H_∞ attitude stabilization of a flexible spacecraft