Fixed-time terminal sliding mode control of spinning tether system for artificial gravity environment in high eccentricity orbit

Li, Aijun; Tian, Haochang

doi:10.1016/j.actaastro.2020.03.013

Cited by 13 publications

(3 citation statements)

References 20 publications

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“…Martin et al studied the dynamic and control of a deep-space tethered artificial gravity system [13]. Construction and stabilization of an artificial gravity environment with SEDTs in high eccentricity orbit were studied by Li et al [14] Payload transportation and debris removal with tethers were also studied by Li et al [15], Hoyt [16], and Huang et al [17]. Spinning deployment of tethered formations was studied by Zhang et al [18] A dynamic analysis and a ground experiment for a tethered spinning formation were proposed by Yu et al [19].…”

Section: Introductionmentioning

confidence: 99%

Nonlinear deformation and attitude control for spinning electrodynamic tether systems during spin-up stage

Hongshi,

Hang,

Changqing

et al. 2024

Nonlinear Dyn

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This paper studies the non-linear control of a spinning electrodynamic tether system during its spin-up process. The main problem of the spin-up process is that the tether shape may become irregular due to distributed electrodynamic force, which can lead to risks such as entanglement of the deformed tether with end bodies (base spacecraft and sub-satellite). To deal with this problem, a nonlinear control strategy is proposed in this paper for reducing tether deformation and for stabilizing attitude motions of end bodies. Firstly, the tether system is modeled based on the assumption of a flexible tether, and the minimum current for spin-up is given as the basis for open-loop program design. Secondly, considering the underactuation problem of the tether system, a sliding mode controller with an adaptive law is proposed to track spinning motion and stabilize tether deformation by adjusting only electrical current. Thirdly, considering the limit of attitude control moment, a high-gain saturated controller is proposed to stabilize the attitude motions of end bodies. In the end, numerical results validate that under the regulation of the proposed control strategy, tether deformation is reduced to an insignificant level, and attitude motions of end bodies are stabilized around designated orientations.

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Section: Introductionmentioning

confidence: 99%

Nonlinear deformation and attitude control for spinning electrodynamic tether systems during spin-up stage

Hongshi,

Hang,

Changqing

et al. 2024

Nonlinear Dyn

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“…1 Space-tethered system generally consists of a spacecraft, one or more multiple tether(s), and one or more satellites connected to each other by the tether(s). 2 With the help of the tether, the STS is applied widely in scientific tasks, such as the orbit transfer, 3 aerobraking maneuver, 4 active debris removal, 5 energy harvesting, 6 payload transportation, 7 artificial gravity, 8 satellite formation flights, 9 and so on.…”

Section: Introductionmentioning

confidence: 99%

Adaptive super-twisting control for deployment of space-tethered system with unknown boundary disturbances

Dong

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper proposes an adaptive super-twisting control (ASTC) for the deployment of space-tethered systems with the consideration of uncertainty of external and internal disturbances with unknown boundaries. The main advantage of the ASTC scheme is that it can deal with the unknown bounds of uncertainties and disturbances. The proposed control law consists of two adaptive control gains that ensure the establishment, in a finite time, of a real second-order sliding mode. This, in turn, guarantees a convergence to a small domain and without overestimating the control gains. The stability of the control law is demonstrated theoretically. Compared with the sliding mode control algorithm with power reaching law, the newly proposed adaptive super-twisting control method performs better in the settling time, the maximum in-plane angle, and angular velocity control and suppressing oscillations. Numerical simulations are presented to validate the effectiveness and robustness of the proposed ASTC scheme.

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“…Kasaeian et al [8] utilized a robust guidance algorithm based on sliding mode method for a chaser to rendezvous with a target in space. Meanwhile, the terminal sliding mode control method is applied to tracking control problem for autonomous underwater vehicles (AUVs) [9,10], and a fixed-time terminal sliding mode control strategy introduced to produce an artificial gravity environment by spinning tether system in high eccentricity transfer orbit [11]; an adaptive fuzzy sliding mode control is proposed to solve the problem of spacecraft attitude tracking for space debris removal [12]. A novel sliding mode control strategy is developed to avoid entering dangerous areas during the implementation of the rendezvous procedure [13], and new neural sliding mode guidance is studies for maneuvering target in [14].…”

Section: Introductionmentioning

confidence: 99%

Method for Collision Avoidance in Spacecraft Rendezvous Problems with Space Objects in a Phasing Orbit

Chen¹,

Баранов²,

Wang³

et al. 2021

Computer Modeling in Engineering &Amp; Sciences

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As the number of space objects (SO) increases, collision avoidance problem in the rendezvous tasks or reconstellation of satellites with SO has been paid more attention, and the dangerous area of a possible collision should be derived. In this paper, a maneuvering method is proposed for avoiding collision with a space debris object in the phasing orbit of the initial optimal solution. Accordingly, based on the plane of eccentricity vector components, relevant dangerous area which is bounded by two parallel lines is formulated. The axises of eccentricity vector system pass through the end of eccentricity vector of phasing orbit in the optimal solution, and orientation of axis depends on the latitude argument where a collision will occur. The dangerous area is represented especially with the graphical dialogue, and it allows to find a compromise between the SO avoiding and the fuel consumption reduction. The proposed method to solve the collision avoidance problem provides simplicity to calculate rendezvous maneuvers, and possibility to avoid collisions from several collisions or from "slow" collisions in a phasing orbit, when the protected spacecraft and the object fly dangerously close to each other for a long period.

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Fixed-time terminal sliding mode control of spinning tether system for artificial gravity environment in high eccentricity orbit

Cited by 13 publications

References 20 publications

Nonlinear deformation and attitude control for spinning electrodynamic tether systems during spin-up stage

Nonlinear deformation and attitude control for spinning electrodynamic tether systems during spin-up stage

Adaptive super-twisting control for deployment of space-tethered system with unknown boundary disturbances

Method for Collision Avoidance in Spacecraft Rendezvous Problems with Space Objects in a Phasing Orbit

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