Finite-time output feedback attitude control for spacecraft using “Adding a power integrator” technique

Jiang, Boyan; Li, Chuanjiang; Ma, Guangfu

doi:10.1016/j.ast.2017.03.026

Cited by 71 publications

(35 citation statements)

References 30 publications

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“…Moreover , the residual set of the solution of system (3) can be given by

\{\underset{t \to T}{normallim} x |V (bold-italicx) \leq \min \{α^{- 1 / p} {([], ϑ false/ ((), 1 - θ^{k}))}^{1 / (italickp)}, β^{- 1 / p} {([], ϑ false/ ((), 1 - θ^{k}))}^{1 / (italickg)}\}\}

, where θ is a scalar and satisfies 0 < θ ≤ 1. The time needed to reach the residual set is bounded by

T \leq \frac{1}{α^{k} θ^{k} (1 - pk)} + \frac{1}{β^{k} θ^{k} (gk - 1)} .

Lemma (). For any x i ∈ R, i = 1, 2.…”

Section: Background and Preliminariesmentioning

confidence: 99%

“……, n , if p ∈ (0, 1) and g > 1, then we have

{((), \sum_{i = 1}^{n} (||, x_{i}))}^{p} \leq \sum_{i = 1}^{n} {(||, x_{i})}^{p} \leq n^{1 - p} {((), \sum_{i = 1}^{n} (||, x_{i}))}^{p}

and

\sum_{i = 1}^{n} {(||, x_{i})}^{g} \leq {((), \sum_{i = 1}^{n} (||, x_{i}))}^{g} \leq n^{g - 1} \sum_{i = 1}^{n} {(||, x_{i})}^{g}

. Lemma . For any x ∈ R , y ∈ R , c > 0, d > 0, we have

{(||, x)}^{c} {(||, y)}^{d} \leq c {(||, x)}^{c + d} / (c + d) + d {(||, y)}^{c + d} / (c + d) .

Lemma . If a real number p satisfies p ∈ (0, 1), then |sig( x ) p − sig( y ) p | ≤ 2 1 − p | x − y | p , ∀ x , y ∈ R.…”

Section: Background and Preliminariesmentioning

confidence: 99%

“…Compared with the existing results of finite‐time attitude control, the main theoretical contributions of this study can be briefly outlined as follows. In comparison with most of the finite‐time attitude controllers that are based on the conventional concept of finite‐time stability, such as the homogeneous attitude controllers, the terminal sliding mode attitude controllers, and the “AAPIC” attitude controllers, two novel attitude controllers are designed based on the concept of “fixed‐time stability,” which can be seen as a special case of finite‐time stability Compared with most of the existing fixed‐time attitude controllers that are designed based on the TSMC, such as those in References , the two proposed fixed‐time controllers are designed based on the AAPIC. In comparison with the research results related to finite‐time attitude control, such as those in , this study further considers the case where external disturbance and thruster faults exist.…”

Section: Introductionmentioning

confidence: 99%

“…(1) In comparison with most of the finite-time attitude controllers that are based on the conventional concept of finite-time stability, such as the homogeneous attitude controllers, [28][29][30] the terminal sliding mode attitude controllers, 13,14,31,32 and the "AAPIC" attitude controllers, 12,33 two novel attitude controllers are designed based on the concept of "fixed-time stability," which can be seen as a special case of finite-time stability. 23 (2) Compared with most of the existing fixed-time attitude controllers that are designed based on the TSMC, such as those in References 24-27, the two proposed fixed-time controllers are designed based on the AAPIC.…”

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confidence: 99%

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Fixed‐time attitude tracking control for spacecraft based on adding power integrator technique

Jiang

Hou

et al. 2020

Intl J Robust & Nonlinear

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Summary In this article, the fixed‐time attitude tracking problem for rigid spacecraft is investigated based on the adding‐a‐power‐integrator control technique. First, a fixed‐time attitude tracking controller is designed to guarantee fixed‐time convergence of tracking errors. Then, by considering the presence of random disturbance and actuator faults, an adaptive fault‐tolerant attitude tracking controller is designed to guarantee tracking errors converge to a residual set of zero in a fixed time. The complete bounds on settling time are derived independently of initial conditions. The simulation results illustrate the highly precise and robust attitude control performance obtained by using the proposed controllers.

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“…Moreover , the residual set of the solution of system (3) can be given by

\{\underset{t \to T}{normallim} x |V (bold-italicx) \leq \min \{α^{- 1 / p} {([], ϑ false/ ((), 1 - θ^{k}))}^{1 / (italickp)}, β^{- 1 / p} {([], ϑ false/ ((), 1 - θ^{k}))}^{1 / (italickg)}\}\}

, where θ is a scalar and satisfies 0 < θ ≤ 1. The time needed to reach the residual set is bounded by

T \leq \frac{1}{α^{k} θ^{k} (1 - pk)} + \frac{1}{β^{k} θ^{k} (gk - 1)} .

Lemma (). For any x i ∈ R, i = 1, 2.…”

Section: Background and Preliminariesmentioning

confidence: 99%

“……, n , if p ∈ (0, 1) and g > 1, then we have

{((), \sum_{i = 1}^{n} (||, x_{i}))}^{p} \leq \sum_{i = 1}^{n} {(||, x_{i})}^{p} \leq n^{1 - p} {((), \sum_{i = 1}^{n} (||, x_{i}))}^{p}

and

\sum_{i = 1}^{n} {(||, x_{i})}^{g} \leq {((), \sum_{i = 1}^{n} (||, x_{i}))}^{g} \leq n^{g - 1} \sum_{i = 1}^{n} {(||, x_{i})}^{g}

. Lemma . For any x ∈ R , y ∈ R , c > 0, d > 0, we have

{(||, x)}^{c} {(||, y)}^{d} \leq c {(||, x)}^{c + d} / (c + d) + d {(||, y)}^{c + d} / (c + d) .

Lemma . If a real number p satisfies p ∈ (0, 1), then |sig( x ) p − sig( y ) p | ≤ 2 1 − p | x − y | p , ∀ x , y ∈ R.…”

Section: Background and Preliminariesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Fixed‐time attitude tracking control for spacecraft based on adding power integrator technique

Jiang

Hou

et al. 2020

Intl J Robust & Nonlinear

Self Cite

View full text Add to dashboard Cite

show abstract

“…In a finite‐time controller is proposed and shown that the desired attitude can be tracked in finite time only in the absence of disturbances while it is verified that in the presence of external disturbances the tracking errors can only reach a region around the origin in finite time. More recently, a finite‐time output feedback controller has been proposed in . Compared to the other works, these approaches only require the attitude measurements rather than full state measurements.…”

Section: Introductionmentioning

confidence: 99%

Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

Bayat

Javaheri

2018

Asian Journal of Control

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This paper addresses the global stability and robust attitude tracking problem of a near polar orbit satellite subject to unknown disturbances and uncertainties. It is assumed that the satellite is fully actuated by a set of reaction wheels (RW) as control actuators because of their relative simplicity, versatility and high accuracy. The terminal sliding mode control (TSMC) approach is utilized in a two-level architecture to achieve control objectives. In the lower layer a detumbling-like controller is designed which guarantees the finite-time detumbling and tracking of the desired angular velocities and based on this result a robust attitude tracking controller is designed in the upper layer to achieve 3-axis attitude tracking in the presence of unknown disturbances and bounded uncertainties. Robust stability and tracking properties of designed controllers are proved using the Lyapunov theory. Finally, a set of numerical simulation results are provided to illustrate the effectiveness and performance of the proposed control method.

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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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Finite-time output feedback attitude control for spacecraft using “Adding a power integrator” technique

Cited by 71 publications

References 30 publications

Fixed‐time attitude tracking control for spacecraft based on adding power integrator technique

Fixed‐time attitude tracking control for spacecraft based on adding power integrator technique

Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

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

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