Robust adaptive attitude control for flexible spacecraft in the presence of SGCMG friction nonlinearity

Wang, Lu; Zhong, Chenxing; Guo, Yu; Wu, Yifei; Guo, Jian

doi:10.1002/rnc.4079

Cited by 13 publications

(6 citation statements)

References 24 publications

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“…Since 𝜔 and 𝜔̇ are decaying, it follows from (20) that 𝜎 converge to the residual set |𝜎 𝑖 | ≤ 𝛥 𝜎 given by…”

Section: Remarkmentioning

confidence: 99%

“…For these reasons, achieving high accuracy attitude control for spacecraft system has become a challenging problem. Over the past few years, the demanding issue of spacecraft attitude control has attracted profound attention and numerous control laws are available; for instance, backstepping method [9], eventtriggered control [10,11], model predictive control (MPC) [12,13], sliding mode control (SMC) [14][15][16][17], non-fragile output-feedback control [18,19], adaptive control [20], fuzzy control [21], fault-tolerant control [22], disturbance observer-based control [23][24][25][26][27], etc.…”

Section: Introductionmentioning

confidence: 99%

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A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

et al. 2022

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The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.

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“…Since 𝜔 and 𝜔̇ are decaying, it follows from (20) that 𝜎 converge to the residual set |𝜎 𝑖 | ≤ 𝛥 𝜎 given by…”

Section: Remarkmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

et al. 2022

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“…Assumption 3: (Wang et al, 2018) It is supposed that magnitudes of elastic vibration and its derivatives are bounded during the whole attitude maneuver, and coupling effect term − δ T χ ·· − ω × δ T χ · satisfies ‖ − δ T χ ·· − ω × δ T χ · ‖ ≤ b 3 + b 4 ‖ ω ‖ 2 with b 3 , b 4 > 0 .…”

Section: Problem Formulationmentioning

confidence: 99%

Fault-tolerant attitude control for flexible spacecraft subject to input and state constraint

Golestani

Esmaeilzadeh

Xiao

2020

Transactions of the Institute of Measurement and Control

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This paper considers the problem of fault-tolerant attitude control for a flexible spacecraft subject to input and state constraint. Particularly, a new sliding mode-based attitude control with fixed-time convergent for the flexible spacecraft is developed in which the convergence rate of the system state is improved both far from and at close range of the origin. In contrast to the existing complicated prescribed performance controls (PPC), the proposed PPC possesses a much simpler structure due to the use of a novel constraint concept without employing error transformation. It also introduces a modified prescribed performance function (MPPF) to explicitly determine the settling time. It is rigorously proved that the attitude variable is kept within the predefined constraint boundaries even when the actuator saturation is taken into account. Moreover, the proposed controller is inherently continuous and the chattering is effectively reduced. An adaptive mechanism is developed in which no prior knowledge of the lumped uncertainties is required. Finally, numerical simulations are presented to demonstrate that the proposed controller is able to successfully accomplish attitude control with high attitude pointing accuracy and stability. More specifically, it provides faster convergence (improvement percentage of convergence time (IP_CT) is about 18%) and more accurate control (improvement percentages of MRPs (IP_MRPs) and angular velocity (IP_AV) are about 60% and 80%, respectively) under healthy actuators. Values of IP_CT, IP_CT, and IP_AV are 50%, 99.9% and 99.9% under faulty actuators, respectively.

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“…4 Numerous studies on the attitude tracking control have been conducted in which the intended path is only to evaluate the proposed control law. [5][6][7][8][9] Therefore, the success of this law has not been evaluated in an operational path and with application in remote sensing. In Ref.…”

Section: Introductionmentioning

confidence: 99%

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

Zarourati

Mirshams

Tayefi

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper addresses the attitude path design of a remote sensing satellite in various imaging modes. The novel path design algorithm is based on local polynomial regression, which produces a smooth attitude path by receiving the size and timing of maneuvers in each axis according to the desired imaging mode. This algorithm is described for stereo and snapshot modes in an imaging operation. The adaptive robust tracking control (ARTC) law is designed using quaternion algebra to perform the required maneuvers in an attitude path. The ARTC structure includes a sliding mode strategy, a projection-based adaptive model compensation, and a linear feedback term. Suitable conditions for imaging in each mode and the time of taking the image are determined by defining and evaluating the attitude control indices. These indices are defined by the half-cone error along the payload line of sight and relative performance error as a jitter with a 3-sigma confidence level. Despite the challenges in the path design, such as smoothness, system agility, and finite time realization of indices, in a conventional stereo imaging mode, taking an image in the nadir-pointing attitude is neglected. As a result, our work provides suitable conditions for taking the image in this attitude with an interval of 1.2 s. Finally, numerical simulations and verification are performed using multidisciplinary simulation, indicating the effectiveness of the proposed algorithm and model-based ARTC law.

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Robust adaptive attitude control for flexible spacecraft in the presence of SGCMG friction nonlinearity

Cited by 13 publications

References 24 publications

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

Fault-tolerant attitude control for flexible spacecraft subject to input and state constraint

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

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