Anti-Unwinding Attitude Control with Fixed-Time Convergence for a Flexible Spacecraft

Pukdeboon, Chutiphon; Jitpattanakul, Anuchit

doi:10.1155/2017/5018323

Cited by 12 publications

(8 citation statements)

References 41 publications

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“…A disadvantage of the proposed controller lies in that the convergence time depends on the initial states of the spacecraft system, to solve this problem, future work will include extending the result in this paper to fixed‐time control [49]. Because numerical simulations are usually inadequate for verifying the practical ACS of spacecraft, hardware‐in‐the‐loop experiments will be conducted to increase the credibility.…”

Section: Resultsmentioning

confidence: 99%

Finite‐time adaptive fault‐tolerant control for rigid spacecraft attitude tracking

Gao

Jing

Liu

et al. 2020

Asian Journal of Control

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This paper provides a new solution for the finite‐time attitude maneuvers of rigid spacecraft. Uncertainties involving unknown inertial parameters, external disturbances and actuator failures are taken into account. With an effort to achieve attitude tracking despite the impact of uncertainties, a non‐singular terminal sliding mode (NTSM) manifold consisting of attitude errors and angular velocity errors is first constructed. After that, a simple but efficient adaptive updating law is derived to estimate the upper bound of the lumped unknown function in the derivative of sliding surface. Combining NTSM technology and pure adaptive control, a chattering‐free fault‐tolerant controller is presented. The premise assumptions on uncertainties in most of the existing achievements are eliminated, which makes the controller less constrained and more practical. The rigorous proof of finite‐time stability is provided and the convergent regions of tracking errors are explicitly expressed. Finally, numerical simulation is conducted to verify the effectiveness of the proposed control scheme and the comparison experiments with relevant literature demonstrate the satisfactory performances.

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Section: Resultsmentioning

confidence: 99%

Finite‐time adaptive fault‐tolerant control for rigid spacecraft attitude tracking

Gao

Jing

Liu

et al. 2020

Asian Journal of Control

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“…The inertia matrix J of the spacecraft is time-varying quantity owing to mass variations on account of fuel consumption, onboard solar arrays rotation and payload motion, and out-gassing, etc. (Pukdeboon and Jitpattanakul 2017). Therefore, J comprises of a nominal component given as J 0 ∈ R 3 × 3 and an uncertain component Δ J ∈ R 3 × 3 , wherein the term Δ J can be written as Δ J = J − J 0 (Zhu et al, 2011).…”

Section: System Modeling Of a Flexible Spacecraftmentioning

confidence: 99%

Attitude stabilization of flexible spacecraft under limited communication with reinforced robustness

Amrr

Nabi

2019

Transactions of the Institute of Measurement and Control

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This paper proposes a robust event-driven control for attitude regulation in flexible spacecraft affected by inertial parametric uncertainties and external disturbances. The bandwidth constraint of the communication channel between controller and system requires an event-based control design. Under the action of proposed control law, the system trajectories are ensured to be uniformly ultimately bounded (UUB) in a small vicinity of their equilibrium points. Apart from the boundedness of states, the proposed event-triggered controller also satisfies bandwidth restrictions by achieving a substantially low control usage. The results obtained from numerical simulations are indeed encouraging. It demonstrates the proposed controller as a potential alternative to the periodically sampled data controllers. Moreover, the proposed control strategy successfully eludes the unwanted unwinding phenomenon encountered in quaternion based attitude control of the spacecraft.

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“…The spacecraft undergoes various operations like fuel consumption, onboard solar arrays rotation, payload motion, and out-gassing, etc. which leads to mass variations [33]. Therefore, the inertia matrix J consists of a nominal component J 0 ∈ R 3×3 and an uncertain component J ∈ R 3×3 .…”

Section: A Flexible Spacecraft Modelingmentioning

confidence: 99%

An Event-Triggered Robust Attitude Control of Flexible Spacecraft With Modified Rodrigues Parameters Under Limited Communication

2019

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The attitude regulation of spacecraft using continuous time execution of the control law is not always affordable for the low-cost satellites with limited wireless resources. Of late, within the ambit of control of systems over networks, event-triggered control has proved to be instrumental in ensuring acceptable closed-loop performance while respecting bandwidth constraints of the underlying network. Aligned with these design objectives, a robust event-triggered attitude control algorithm is proposed to regulate the orientation of a flexible spacecraft subjected to parametric uncertainties, external disturbances, and vibrations due to flexible appendages. The control law is developed using a state-dependent single feedback vector, which further assists in obeying the constrained network. The current information of this vector is updated to the onboard controller only when the predefined triggering condition is satisfied. Thus, the control input is updated through communication channel only when there is a need, which ultimately helps in saving the communication resources. The system trajectories, under the proposed approach, are guaranteed to be uniformly ultimately bounded (UUB) in a small neighborhood of origin by using a high gain. Moreover, the practical applicability of the proposed scheme is also proved by showing the Zeno free behavior in the proposed control, i.e., it avoids the accumulation of the triggering sequence. The numerical simulations results are indeed encouraging and illustrate the effectiveness of the designed controller. Moreover, the numerical comparative analysis shows that the proposed approach performs better than periodically sampled data technique and sliding mode-based event-triggered technique.INDEX TERMS Flexible spacecraft, attitude regulation control, limited data transmission, communication constraints, event-trigger, robust control, Zeno behavior, modified Rodrigues parameters (MRP).

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Anti-Unwinding Attitude Control with Fixed-Time Convergence for a Flexible Spacecraft

Cited by 12 publications

References 41 publications

Finite‐time adaptive fault‐tolerant control for rigid spacecraft attitude tracking

Finite‐time adaptive fault‐tolerant control for rigid spacecraft attitude tracking

Attitude stabilization of flexible spacecraft under limited communication with reinforced robustness

An Event-Triggered Robust Attitude Control of Flexible Spacecraft With Modified Rodrigues Parameters Under Limited Communication

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