scholarly journals Adaptive Fuzzy Control for Attitude Stabilization of Spacecraft with Deployable Composite Laminated Solar Array

Complexity ◽  
2020 ◽  
Vol 2020 ◽  
pp. 1-26
Author(s):  
Wei Zhang ◽  
Weibing Zhu ◽  
Shijie Zhang ◽  
Xiangtian Zhao
Keyword(s):  
Dynamic Model ◽  
Differential Algebraic Equations ◽  
Solar Array ◽  
Main Body ◽  
Pd Controller ◽  
Attitude Stabilization ◽  
Adaptive Fuzzy ◽  
Control Scheme ◽  
Deployment Dynamics ◽  
Fuzzy Pd

Modern spacecraft are often equipped with large-scale, complex, and lightweight solar arrays whose deployment involves a highly dynamic movement. This paper proposed a novel adaptive proportional-derivative typed fuzzy logic control scheme for the attitude stabilization of a flexible spacecraft during the deployment of a composite laminated solar array. First, a constrained rigid-flexible coupling spacecraft model consisting of a rigid main body and a flexible solar array was proposed. The solar array, which is composed of composite laminated shells, was described by the absolute nodal coordinate formulation. Then, the detailed derivation of the adaptive fuzzy PD controller for attitude stabilization of the spacecraft was discussed. In addition, the spacecraft dynamic model which integrated the adaptive fuzzy PD controller was derived as a set of differential-algebraic equations. Several simulations were developed to investigate the solar array deployment dynamics and to verify the effectiveness of the proposed adaptive fuzzy PD controller. The results suggested that the proposed dynamic model is able to exactly describe the deployment dynamics of the composite laminated solar array. The solar array deployment causes obvious translational and rotational motions of the spacecraft. The proposed adaptive fuzzy PD control scheme has better performance in terms of the control precision and time response in stabilizing spacecraft during the deployment of the composite laminated solar array, comparing with that of the conventional PD controller.

Dynamic Modeling for a Flexible Spacecraft With Solar Arrays Composed of Honeycomb Panels and Its Proportional–Derivative Control With Input Shaper

2016 ◽  
Vol 138 (8) ◽  
Author(s):  
Lun Liu ◽  
Dengqing Cao
Keyword(s):  
Dynamic Model ◽  
Vibration Suppression ◽  
Hybrid Control ◽  
Flexible Spacecraft ◽  
Solar Array ◽  
Pd Controller ◽  
Pd Control ◽  
Solar Arrays ◽  
Attitude Maneuver ◽  
The One

A high-precision dynamic model of a flexible spacecraft installed with solar arrays, which are composed of honeycomb panels, is established based on the nonconstrained modes of flexible appendages (solar arrays), and an effective cooperative controller is designed for attitude maneuver and vibration suppression by integrating the proportional–derivative (PD) control and input shaping (IS) technique. The governing motion equations of the system and the corresponding boundary conditions are derived by using Hamiltonian Principle. Solving the linearized form of those equations with associated boundaries, the nonconstrained modes of solar arrays are obtained for deriving the discretized dynamic model. Applying this discretized model and combining the IS technique with the PD controller, a hybrid control scheme is designed to achieve the attitude maneuver of the spacecraft and vibration suppression of its flexible solar arrays. The numerical results reveal that the nonconstrained modes of the system are significantly influenced by the spacecraft flexibility and honeycomb panel parameters. Meanwhile, the differences between the nonconstrained modes and the constrained ones are growing as the spacecraft flexibility increases. Compared with the pure PD controller, the one integrating the PD control and IS technique performs much better, because it is more effective for suppressing the oscillation of attitude angular velocity and the vibration of solar array during the attitude maneuver, and reducing the residual vibration after the maneuver process.

Adaptive fuzzy Jacobian control of spacecraft combined attitude and Sun tracking system

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Yew-Chung Chak ◽  
Renuganth Varatharajoo ◽  
Nima Assadian
Keyword(s):  
Attitude Control ◽  
Tracking System ◽  
Solar Array ◽  
The Sun ◽  
Solar Panels ◽  
Content Type ◽  
Adaptive Fuzzy ◽  
Control Scheme ◽  
Adaptation Law ◽  
Pointing Control

Purpose The paper aims to address the combined attitude control and Sun tracking problem in a flexible spacecraft in the presence of external and internal disturbances. The attitude stabilization of a flexible satellite is generally a challenging control problem, because of the facts that satellite kinematic and dynamic equations are inherently nonlinear, the rigid–flexible coupling dynamical effect, as well as the uncertainty that arises from the effect of actuator anomalies. Design/methodology/approach To deal with these issues in the combined attitude and Sun tracking system, a novel control scheme is proposed based on the adaptive fuzzy Jacobian approach. The augmented spacecraft model is then analyzed and the Lyapunov-based backstepping method is applied to develop a nonlinear three-axis attitude pointing control law and the adaptation law. Findings Numerical results show the effectiveness of the proposed adaptive control scheme in simultaneously tracking the desired attitude and the Sun. Practical implications Reaction wheels are commonly used in many spacecraft systems for the three-axis attitude control by delivering precise torques. If a reaction wheel suffers from an irreversible mechanical breakdown, then it is likely going to interrupt the mission, or even leading to a catastrophic loss. The pitch-axis mounted solar array drive assemblies (SADAs) can be exploited to anticipate such situation to generate a differential torque. As the solar panels are rotated by the SADAs to be orientated relative to the Sun, the pitch-axis wheel control torque demand can be compensated by the differential torque. Originality/value The proposed Jacobian control scheme is inspired by the knowledge of Jacobian matrix in the trajectory tracking of robotic manipulators.

A composite anti-disturbance control scheme for attitude stabilization and vibration suppression of flexible spacecrafts

2015 ◽  
Vol 23 (15) ◽  
pp. 2470-2477 ◽  
Author(s):  
Zhen Wang ◽  
Zhong Wu ◽  
Lijun Li ◽  
Jun Yuan
Keyword(s):  
Attitude Control ◽  
Disturbance Observer ◽  
Vibration Suppression ◽  
Disturbance Attenuation ◽  
Pd Controller ◽  
Parameter Uncertainties ◽  
Performance Simulation ◽  
Attitude Stabilization ◽  
Multiple Disturbances ◽  
Control Scheme

Abstract: There exist multiple disturbances resulting from the structural vibrations of flexible appendages, unknown external and internal disturbances, and parameter uncertainties, which affect the attitude control performance seriously. To enhance the disturbance attenuation performance and vibration suppression ability, a composite anti-disturbance control scheme (CADCS) based on disturbance observer is proposed for attitude stabilization and vibration reduction of flexible spacecraft. The CADCS combines a composite disturbance observer (CDO) and a PD controller with feedforward. The multiple disturbances are equivalent to slowly varying disturbance and harmonic disturbance. The CDO can estimate two types of disturbance and compensate for them through feedforward. The PD controller realizes the asymptotic convergence by compensating the disturbance from CDO. The CADCS based on CDO and PD controller is not only simple and easy to realize, but also yields better vibration suppression and anti-disturbance performance. Simulation results of a certain spacecraft demonstrate the effectiveness of the proposed CADCS.

Position Tracking and Attitude Stable Control for an Unmanned Quadrotor Vehicle

2013 ◽  
Vol 645 ◽  
pp. 492-496
Author(s):  
Hui Bai ◽  
Hong Yu Wang ◽  
Shi Huang Shao
Keyword(s):  
Dynamic Model ◽  
Control Strategy ◽  
Dynamic Inversion ◽  
Position Tracking ◽  
Attitude Stabilization ◽  
Control Scheme ◽  
Channel Control ◽  
Stable Control

A simplified dynamic model of the quadrotor is established. A multi-channel control scheme based on PID and dynamic inversion is proposed. Four channels are designed to achieve the position tracking and attitude stabilization of the quadrotor. A simulation shows the validity and good features of the control strategy.

scholarly journals High Precision Roll/Yaw Attitude Stabilization for Flexible communication satellite

2018 ◽  
Vol 3 (2) ◽  
pp. 81-88
Author(s):  
J. E Benmansour ◽  
B. Khouane ◽  
R. Rima
Keyword(s):  
High Precision ◽  
Pd Controller ◽  
Extended State ◽  
Model Uncertainties ◽  
Environmental Disturbances ◽  
Attitude Stabilization ◽  
Communication Satellite ◽  
Control Scheme ◽  
Yaw Attitude ◽  
Flexible Vibrations

The aim of this paper is to realize high-precision attitude stabilization for roll/yaw axes of flexible communication satellite while attenuate the effects of the elastic vibrations and multiple disturbances such as solar radiation and model uncertainties. a composite control has been designed which is comprise two part an anti-disturbance proportional-derivative (PD) controller is designed to stabilize the attitude while rejecting the effects of flexible vibrations, environmental disturbances, and unmodelled dynamics, whose are assumed as an extended state. This controller comprises two parts, i.e. an extended state observer and a PD controller with feedforward. First, flexible vibrations, environmental disturbances and unmodelled dynamics are regarded as an extended state, which can be estimated by the proposed observer. The estimated extended state can be compensated by feedforward where the attitude can be stabilized by the PD controller. Numerical simulation results are presented to demonstrate the effectiveness of the control scheme.

scholarly journals Finite-Time Adaptive Fuzzy Control for Nonlinear Systems with Unknown Backlash-Like Hysteresis

2021 ◽  
Author(s):  
Shuzhen Diao ◽  
Wei Sun ◽  
Le Wang ◽  
Jing Wu
Keyword(s):  
Fuzzy Control ◽  
Finite Time ◽  
Fuzzy Systems ◽  
Tracking Error ◽  
Adaptive Fuzzy Control ◽  
Finite Time Stability ◽  
Adaptive Fuzzy ◽  
Intermediate Variable ◽  
Control Scheme ◽  
Theoretical Results

AbstractThis study considers the tracking control problem of the nonstrict-feedback nonlinear system with unknown backlash-like hysteresis, and a finite-time adaptive fuzzy control scheme is developed to address this problem. More precisely, the fuzzy systems are employed to approximate the unknown nonlinearities, and the design difficulties caused by the nonlower triangular structure are also overcome by using the property of fuzzy systems. Besides, the effect of unknown hysteresis input is compensated by approximating an intermediate variable. With the aid of finite-time stability theory, the proposed control algorithm could guarantee that the tracking error converges to a smaller region. Finally, a simulation example is provided to further verify the above theoretical results.

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