Neural network‐based adaptive attitude tracking control for flexible spacecraft with unknown high‐frequency gain

Hu, Qinglei

doi:10.1002/acs.1140

Cited by 16 publications

(6 citation statements)

References 34 publications

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“…Spacecraft attitude maneuvering and measurement are affected by micro-vibrations in space, and vibration suppression becomes more difficult when the bandwidth of vibration is high [1,2]. A VSMSCSG [3] is a novel inertial device for spacecraft attitude control and measurement.…”

Section: Introductionmentioning

confidence: 99%

Spacecraft Attitude Measurement and Control Using VSMSCSG and Fractional-Order Zeroing Neural Network Adaptive Steering Law

Li,

Ren,

Wang

et al. 2024

Sensors

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In order to improve the accuracy and convergence speed of the steering law under the conditions of high dynamics, high bandwidth, and a small deflection angle, and in an effort to improve attitude measurement and control accuracy of the spacecraft, a spacecraft attitude measurement and control method based on variable speed magnetically suspended control sensitive gyroscopes (VSMSCSGs) and the fractional-order zeroing neural network (FO-ZNN) steering law is proposed. First, a VSMSCSG configuration is designed to realize attitude measurement and control integration in which the VSMSCSGs are employed as both actuators and attitude-rate sensors. Second, a novel adaptive steering law using FO-ZNN is designed. The matrix pseudoinverses are replaced by FO-ZNN outputs, which solves the problem of accuracy degradation in the traditional pseudoinverse steering laws due to the complexity of matrix pseudoinverse operations under high dynamics conditions. In addition, the convergence and robustness of the FO-ZNN are proven. The results show that the proposed FO-ZNN converges faster than the traditional zeroing neural network under external disturbances. Finally, a new weighting function containing rotor deflection angles is added to the steering law to ensure that the saturation of the rotor deflection angles can be avoided. Semi-physical simulation results demonstrate the correctness and superiority of the proposed method.

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Section: Introductionmentioning

confidence: 99%

Spacecraft Attitude Measurement and Control Using VSMSCSG and Fractional-Order Zeroing Neural Network Adaptive Steering Law

Li,

Ren,

Wang

et al. 2024

Sensors

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show abstract

“…Similarly, the new multi-positive feedback control proposed by Omidi et al (2016) effectively shortened the vibration time without limiting the control output. Hu (2010) prescribed an attenuation level for different disturbance. Although the control torque could be small when the disturbance is slight, the control torque is still very large when the disturbance is severe.…”

Section: Introductionmentioning

confidence: 99%

Vibration suppression for large-scale flexible structures based on cable-driven parallel robots

Sun

Tang

Hou

et al. 2020

Journal of Vibration and Control

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Specific satellites with ultralong wings play a crucial role in many fields. However, external disturbance and self-rotation could result in undesired vibrations of the flexible wings, which affect the normal operation of the satellites. In severe cases, the satellites would be damaged. Therefore, it is imperative to conduct vibration suppression for these flexible structures. Utilizing fuzzy-proportional integral derivative control and deep reinforcement learning (DRL), two active control methods are proposed in this article to rapidly suppress the vibration of flexible structures with quite small controllable force based on a cable-driven parallel robot. Inspired by the output law of DRL, a new control method named Tang and Sun control is innovatively presented based on the Lyapunov theory. To verify the effectiveness of these three control methods, three groups of simulations with different initial disturbances are implemented for each method. Besides, to enhance the contrast, a passive pretightening scheme is also tested. First, the dynamic model of the cable-driven parallel robot which comprises four cables and a flexible structure is established using the finite element method. Then, the dynamic behavior of the model under the controllable cable force is analyzed by the Newmark-ß method. Finally, these control methods are implemented by numerical simulations to evaluate their performance, and the results are satisfactory, which validates the controllers’ ability to suppress vibrations.

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“…However, undesirable vibration caused by the flexible property is a thorny problem. Thus, a number of approaches have been proposed for designing controllers to suppress the vibration, such as positive position control [16], neural network control [17], optimal control [18], sliding mode control [8], [19], linear quadratic regulator control [20], etc. Most of these studies are based on finite dimensional ordinary differential equations (ODEs) models [21], [22].…”

Section: Introductionmentioning

confidence: 99%

Vibration Control of a Flexible Spacecraft System With Input Backlash

Lin

et al. 2019

IEEE Access

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In this paper, we deal with the vibration control problem of a flexible spacecraft system with unknown external disturbance and uncertain input backlash nonlinearity. The considered system is described by two partial differential equations and an ordinary differential equation as governing equations, and by ordinary differential equations as boundary conditions. The backlash nonlinearity is reformulated into the desired control input associated with an extra input nonlinear error. This input error and the external disturbance are combined into an unknown ''disturbance-like'' item. Two boundary control inputs are designed at the center body of the spacecraft, compensating for the unknown upper-bound of such items by applying proper online updating laws. As a result, the vibration of both solar panels of the flexible spacecraft is suppressed and their angle positions are regulated in the desired region. The numerical simulations are provided to verify the control performance of the proposed controls by the choice of proper parameters.INDEX TERMS Vibration control, adaptive control, flexible satellite, input backlash.

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Neural network‐based adaptive attitude tracking control for flexible spacecraft with unknown high‐frequency gain

Cited by 16 publications

References 34 publications

Spacecraft Attitude Measurement and Control Using VSMSCSG and Fractional-Order Zeroing Neural Network Adaptive Steering Law

Spacecraft Attitude Measurement and Control Using VSMSCSG and Fractional-Order Zeroing Neural Network Adaptive Steering Law

Vibration suppression for large-scale flexible structures based on cable-driven parallel robots

Vibration Control of a Flexible Spacecraft System With Input Backlash

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