Output feedback control of Lorentz-augmented spacecraft rendezvous

Huang, Xu; Yan, Ye; Zhou, Yang; Yu, Jinlong

doi:10.1016/j.ast.2015.01.022

Cited by 11 publications

(3 citation statements)

References 21 publications

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“…Thus, the uncertainties in aerodynamic model and geomagnetic model should be accounted for. Additionally, for Lorentz-augmented and atmospheric-actuated spacecraft, cost/ weight constraints may limit the use velocity sensors (Huang et al, 2015). It is desirable to develop an output feedback controller to handle the relative motion control without relative velocity measurements.…”

Section: Introductionmentioning

confidence: 99%

Spacecraft formation control using aerodynamic and Lorentz force

Sun

Shan

Zhang

et al. 2020

AEAT

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Purpose This paper aims to investigate the feasibility of using the combination of Lorentz force and aerodynamic force as a propellantless control method for spacecraft formation. Design/methodology/approach It is assumed that each spacecraft is equipped with several large flat plates, which can rotate to produce aerodynamic force. Lorentz force can be achieved by modulating spacecraft’s electrostatic charge. An adaptive output feedback controller is designed based on a sliding mode observer to account for unknown uncertainties and the absence of relative velocity measurements. Aiming at distributing the control input, an optimal control allocation method is proposed to calculate the electrostatic charge of the Lorentz spacecraft and control commands for the atmospheric-based actuators. Findings Numerical examples are provided to demonstrate the effectiveness of the proposed control strategy in the presence of J2 perturbations. Simulation results show that relative motion in a formation can be precisely controlled by the proposed propellantless control method under uncertainties and unavailability of velocity measurements. Research limitations/implications The controllability of the system is not theoretically investigated in the current work. Practical implications The proposed control method introduced in this paper can be applied for small satellites formation in low Earth orbit. Originality/value The main contribution of the paper is the proposal of the propellantless control approach for satellite formation using the combination of Lorentz force and aerodynamic force, which can eliminate the requirement of the propulsion system.

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Section: Introductionmentioning

confidence: 99%

Spacecraft formation control using aerodynamic and Lorentz force

Sun

Shan

Zhang

et al. 2020

AEAT

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“…However, it is still a challenging work to construct such kind of controllers owing to the complexity of the external disturbance, unknown system dynamics and unexpected actuator faults. Despite of these difficulties, researchers have developed numerous strategies for spacecraft tracking control, including adaptive control [1][2][3][4][5], backstepping control [11][12][13], output feedback control [25,26] and sliding mode control [4,18,19,[31][32][33].…”

Section: Introductionmentioning

confidence: 99%

Minimum-Learning-Parameter-Based Fault-Tolerant Control for Spacecraft Rendezvous With Unknown Inertial Parameters

Liu

Zhang

et al. 2020

IEEE Access

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In this paper, robust control strategies are explored to solve the problem of rendezvous maneuver for rigid spacecraft exposed to the external disturbance, actuator faults and unknown inertial parameters. To pursue the control objective, two adaptive controllers are constructed via the sliding mode control (SMC) technology. Firstly, a basic control scheme is designed in the event of unknown inertial parameters and external disturbance, where the Minimum-learning-parameter (MLP) algorithm is adopted for approximating the unknown system dynamics. Though effective, the basic controller is not applicable in the actuator fault scenarios. Considering this drawback, adaptive laws are designed in the second controller to tackling the actuator faults. It is illustrated that the proposed controllers will endow tracking errors with asymptotic stability and strong robustness to actuator faults. Finally, the effectiveness of the control strategies is verified by numerical simulations.

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“…Nevertheless, active modulation of the surface charging level could still perform effective orbital control. In view of the compelling advantages over traditional space vehicles in propellantless orbital maneuvers, a series of potential applications of Lorentz spacecraft has been proposed, including drag compensation, 1 orbital inclination control, 2 proellantless rendezvous, [3][4][5][6] spacecraft hovering, [7][8][9] formation flying, [10][11][12][13][14] and so on.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fast nonsingular terminal sliding mode control of Lorentz-augmented spacecraft relative motion

Huang

Yan

Zhou

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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An electrostatically charged spacecraft is subject to Lorentz force as it moves through the planetary magnetic field. The induced Lorentz force could be used as propellantless electromagnetic propulsion for orbital maneuvers. Such vehicle is referred to as Lorentz spacecraft. By modeling the Earth’s magnetic field as a tilted dipole that corotates with Earth, a nonlinear dynamical model is developed to characterize the orbital motion of a Lorentz spacecraft relative to an arbitrary Earth orbit. A fast nonsingular terminal sliding mode control law is then proposed, based on which an adaptive controller is designed for Lorentz-augmented spacecraft relative motion to deal with the uncertain parameters and perturbations. Due to the constraint that the direction of Lorentz force is naturally perpendicular to the local magnetic field and the vehicle’s velocity relative to the magnetic field, which does not necessarily coincide with the direction of the required control force, thus, the Lorentz force works as auxiliary propulsion to reduce the fuel consumption in most cases. Then, a fuel-optimal distribution law of Lorentz force and traditional chemical propulsion is proposed. Furthermore, the stability of the closed-loop control system is proved via a Lyapunov-based approach. Numerical simulations substantiate the feasibility and validity of the proposed controller for Lorentz-augmented relative orbital control.

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Output feedback control of Lorentz-augmented spacecraft rendezvous

Cited by 11 publications

References 21 publications

Spacecraft formation control using aerodynamic and Lorentz force

Spacecraft formation control using aerodynamic and Lorentz force

Minimum-Learning-Parameter-Based Fault-Tolerant Control for Spacecraft Rendezvous With Unknown Inertial Parameters

Adaptive fast nonsingular terminal sliding mode control of Lorentz-augmented spacecraft relative motion

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