Global saturated velocity‐free finite‐time control for attitude tracking of spacecraft

Xia, Yuquan; Su, Yuxin

doi:10.1049/iet-cta.2018.5952

Cited by 5 publications

(8 citation statements)

References 42 publications

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“…Consequently, the simulation results reveal that the developed controller is capable of fulfilling the exact and rapid attitude stabilization of spacecraft even without using angular velocity measurements and subject to inertia uncertainties and disturbances, and thus ensuring the normal operations of the given space tasks. Developed controlle r Controller in [33] Controller in [35] F I G U R E 6 Energy consumption.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The existing finite‐time velocity filters were mainly designed based on the homogeneous system theory. In References 33 and 34, a velocity‐free finite‐time control approach was proposed for the attitude tracking based on the homogeneous control and a finite‐time velocity filter. In Reference 35, a finite‐time output feedback control scheme was developed for the attitude stabilization by utilizing the adding a power integrator technique with a finite‐time velocity filter.…”

Section: Introductionmentioning

confidence: 99%

“…Specifically, the controller in Reference 35 can only guarantee the attitude and angular velocity stabilize to the bounded fields around zero in finite time under disturbances. Moreover, in References 33 and 34, the disturbances were only included in the simulated studies but not taken account in the stability evaluation. From this point of view, the filter‐based output feedback attitude control of spacecraft with strong robustness against inertia undertainties and disturbances is still a challenging issue worthy of profound investigation.…”

Section: Introductionmentioning

confidence: 99%

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Extended state filter‐based velocity‐free finite‐time attitude control of spacecraft

Yao,

Li,

et al. 2024

Intl J Robust & Nonlinear

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This brief presents a finite‐time output feedback control scheme for the velocity‐free attitude stabilization of rigid spacecraft under inertia uncertainties and disturbances. Note that either the finite‐time velocity observer or the finite‐time extended state observer contains the control torques, which makes the transient performance of the observer‐based output feedback control difficult to be regulated. Alternatively, the filter‐based output feedback control can overcome such problem naturally since the finite‐time velocity filter does not involve the control torques in its structure. Different from the existing finite‐time velocity filters, a finite‐time extended state filter is introduced in this work to estimate the pseudo angular velocity and total uncertain item simultaneously. Then, the developed controller is synthesized based on the recovered information, which does not require the angular velocity for feedback and has the excellent uncertainty and disturbance compensation capability. The global finite‐time stability of the resultant closed‐loop system is evaluated through the Lyapunov direct methodology and homogeneous system theory. Lastly, comparative simulations are carried out to examine the efficiency and superiority of the presented control scheme.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Extended state filter‐based velocity‐free finite‐time attitude control of spacecraft

Yao,

Li,

et al. 2024

Intl J Robust & Nonlinear

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“…For the commonly used SPD control, they are chosen as k p = 0.6 and K d = diag 1.39, 1, 1 in accordance with the constraint (18). The velocities and quaternion are illustrated in Figs.…”

Section: Comparison With Spd Controlsmentioning

confidence: 99%

“…This assumption obviously contradicts with the fact that all actual spacecraft has an allowable maximum torque amplitude. Extensive works show that control system design approaches that do not incorporate actuator constraints directly into the design may suffer from deteriorated performance limitations such as degraded or unpredictable motion and thermal or mechanical failure resulted from excessive torque over the actuators can supply [16][17][18]. This observation is supported by several saturated PD (SPD) controls for spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Single saturated PD control for asymptotic attitude stabilisation of spacecraft

Chen

2020

IET Control Theory & Appl

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This study revisits the problem of attitude stabilisation for rigid spacecraft with actuator constraints in the framework of non-linear proportional-derivative (PD) control methodology. A simple single saturated PD (SSPD) control is proposed. The most appealing features of the proposed SSPD control are that it completely embeds the control action within only a single saturation function for every actuator and omits the elaborate discrimination of the terms that shall be bounded for the commonly-used saturated control and hence it is easy for practical implementation with an improved performance. Lyapunov's direct method is employed to show asymptotic attitude stabilisation. Two illustrative examples are presented to demonstrate the improved performance of the proposed approach.

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Robust Fixed-Time Attitude Stabilization of Flexible Spacecraft via Active Disturbance Rejection Method

Wang

Jia

2021

Lecture Notes in Electrical Engineering

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Global saturated velocity‐free finite‐time control for attitude tracking of spacecraft

Cited by 5 publications

References 42 publications

Extended state filter‐based velocity‐free finite‐time attitude control of spacecraft

Extended state filter‐based velocity‐free finite‐time attitude control of spacecraft

Single saturated PD control for asymptotic attitude stabilisation of spacecraft

Robust Fixed-Time Attitude Stabilization of Flexible Spacecraft via Active Disturbance Rejection Method

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