Self-docking analysis and velocity-aimed control for spacecraft electromagnetic docking

Zhang, Yuanwen; Lee, Yang; Zhu, Yanbo; Ao, Hou-jun; Qi, Dawei

doi:10.1016/j.asr.2016.03.022

Cited by 15 publications

(3 citation statements)

References 8 publications

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“…Shi et al [22], [23] proposed two observer-based controllers for electromagnetic docking in an elliptical orbit in the presence of external disturbances, fault signals and input constraints and good performance are achieved. Zhang et al systematically researched many aspects of electromagnetic docking such as self-docking capability analysis [24], angular momentum management [25] and proposed some control strategies [26]. In [6], the ground experiment of microsatellite docking is conducted to validate the applications to microsatellite electromagnet-based in-orbit assembly, where each docking satellite is equipped with a single coil and the relative attitude maintains aligned along the docking direction.…”

Section: Introductionmentioning

confidence: 99%

Underactuated Microsatellite Electromagnetic Docking Control Using Disturbance Observer-Based Sliding Mode Controller

et al. 2020

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This paper presents a novel control method that combines sliding mode controllers, disturbance observers and an exact robust differentiator to solve the underactuated microsatellite electromagnetic docking control problem, in which each docking satellite is equipped with only one single electromagnetic coil. The far-field model of electromagnetic force/torque is given and its model error is analyzed; and a six-degree-offreedom (6-DOF) docking dynamics model using the far-field model is established. The generation method of the desired trajectory and desired attitude in the docking process is presented; and then an improved exact robust differentiator based on the 3rd-order sliding mode is proposed to produce the desired angular velocity and angular acceleration. In the presence of model uncertainties, external disturbances and input constraints, a disturbance observer-based sliding mode control scheme for underactuated microsatellite electromagnetic docking is developed. The whole closed-loop control system contains an inner-loop attitude controller and an outer-loop position controller. Numerical simulation results are presented to validate the effectiveness and the superior properties of the proposed control scheme. INDEX TERMS Electromagnetic docking control, underactuated microsatellite, sliding mode control, disturbance observer, exact robust differentiator.

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Section: Introductionmentioning

confidence: 99%

Underactuated Microsatellite Electromagnetic Docking Control Using Disturbance Observer-Based Sliding Mode Controller

et al. 2020

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“…Electromagnetic spacecraft docking utilizes inter-craft magnetic force/torque to control relative position and attitude between the docking spacecraft pair. Many organizations, including NASA (National Aeronautics and Space Administration) [13], NUDT (National University of Defense Technology) [14][15][16], CIT (California Institute of Technology) [17], SU (Stanford University) [18], and TMU (Tokyo Metropolitan University) [19] have researched corresponding technologies, and preliminary dynamics and controller have been verified by ground experiments. The dynamics of electromagnetic spacecraft docking are highly nonlinear and coupled with respect to relative motion among magnetic dipoles.…”

Section: Introductionmentioning

confidence: 99%

“…Although existing control laws may nominally provide suitable dynamics to the docking requirements, they fail to consider the dynamics properties of magnetic dipoles interaction. Actually, inter-craft magnetic dipoles actuation satisfies three kinds of dynamics conservation, including linear momentum, angular momentum, and the mechanical energy of the docking spacecraft pair [14,16] . In addition, these dynamics conservation requirements determine the evolvement laws of relative position and attitude between the docking spacecraft pair, which could be exploited to improve control precision, reduce demands of relative motion measurement, and simplify controller design.…”

Section: Introductionmentioning

confidence: 99%

Piece‐wise control of constant electromagnetic moments for spacecraft self‐ and soft‐docking exploiting dynamics conservation

Zhang

2020

Asian Journal of Control

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Inter-spacecraft electromagnetic proximity operation has many potential advantages, such as no propellant consumption and plume contamination, while providing high-precision, continuous, reversible, synchronous, and noncontacting control capability. In addition, with constant magnetic moment actuation, the inter-spacecraft electromagnetic force is, in essence, a kind of conservative force and has dynamics conservation. This yields specific and targeted evolvement laws of relative motion among these actuated magnetic dipoles. Exploiting these properties, spacecraft self-and soft-docking could be achieved with proper piece-wise constant magnetic moments design, which not only improves control precision, but also reduces the demand of relative motion measurement and simplifies docking controller design. Aiming at electromagnetic spacecraft self-and soft-docking controller design, this paper uses dynamic modeling and dynamics conservation analysis to derive the specific evolvement laws of relative motion between the actuated magnetic dipoles first, and then utilize these laws and corresponding dynamics conservation to design the piece-wise constant electromagnetic moments.

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Spacecraft Electromagnetic Docking Control Using Nonsingular Terminal Sliding Mode

Zhang

Zeng

Gao

2021

Lecture Notes in Electrical Engineering

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Self-docking analysis and velocity-aimed control for spacecraft electromagnetic docking

Cited by 15 publications

References 8 publications

Underactuated Microsatellite Electromagnetic Docking Control Using Disturbance Observer-Based Sliding Mode Controller

Underactuated Microsatellite Electromagnetic Docking Control Using Disturbance Observer-Based Sliding Mode Controller

Piece‐wise control of constant electromagnetic moments for spacecraft self‐ and soft‐docking exploiting dynamics conservation

Spacecraft Electromagnetic Docking Control Using Nonsingular Terminal Sliding Mode

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