Stability analysis and motion control of spinning electrodynamic tether system during transition into spin

Lu, Hongshi; Li, A.; Wang, C.; Zabolotnov, Yu. M.

doi:10.1016/j.actaastro.2019.11.032

Cited by 15 publications

(5 citation statements)

References 21 publications

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“…Current (15) indicates that this electrical current is influenced only by the mass distribution of the EDT, and is independent of orbital height or tether length. It has been shown in the works [11] that the actual critical electrical current is about 75% of the electrical current calculated in (15).…”

Section: Minimum Current For Spin-upmentioning

confidence: 95%

“…It has been proven that exists the smallest possible amplitude of current for spin-up is due to the interaction of gravitational force and the electrodynamic force. Lu et al proposed that the minimum current can be calculated as [11]…”

Section: Minimum Current For Spin-upmentioning

confidence: 99%

“…Wang et al further proposed that unstable tether motions and attitude motions of end bodies lead to risks such as the entanglement of end bodies with the tether [8]. To ensure a stable spin-up process of a SEDT, Luo et [11,12] and validated the feasibility of stabilizing tether deformations by adjusting electrical currents. However, the closed-loop optimal controller in his work was still proposed based on the assumption of an inflexible tether.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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: Minimum Current For Spin-upmentioning

confidence: 95%

Section: Minimum Current For Spin-upmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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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“…An air-bearing multi-dimensional microgravity simulator supports the simulated debris-spacecraft configuration system, and an electromagnetic coil generates the controllable magnetic moment of the spacecraft. Given the fixed turns N and area S of the coil, the strength of the magnetic moment is proportional to the input current I from Equation (20). So we obtain the different magnetic moments (torque) by inputting different constant direct currents to the coil with a fixed NS.…”

Section: Development Of Ground Experimental Systemmentioning

confidence: 99%

“…To improve the cost effectiveness of a removal mission, many propulsion approaches without the use of propulsive fuel are raised gradually based on the space environmental force (including electrodynamic tethers [17], solar sails [18] and drag sails [19]), and space momentum exchange (i.e., momentum exchange tethers [20]), etc. Nevertheless, after capturing, the on-orbit deployment of the tether with an enormous length of tens of kilometers and a sail with a massive area of over ten thousand square meters is still a technical challenge that is difficult to achieve with the latest technology, limiting their on-orbit implementation [21][22][23].…”

Section: Introductionmentioning

confidence: 99%

Theoretical and Experimental Investigation of Geomagnetic Energy Effect for LEO Debris Deorbiting

Feng

Zhang

et al. 2022

Aerospace

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Space debris is increasingly problematic and needs active removal, especially in low Earth orbits (LEO). Paying for the vast cost of the disposal of debris from the situation is still inevitable even though pivotal technical hurdles have been overcome with the growing maturity of capturing and deorbiting methods. To this end, a novel geomagnetic energy (GME) propellant approach is firstly proposed to propel a spinning tethered spacecraft for LEO debris deorbiting, without the use of expendable fuel and a large-length tether. In this method, the time-cumulative effect of the interacted torque of the spacecraft’s electromagnet and geomagnetic field is used to accelerate the rotating system for GME storage, and the space momentum exchange from the angular momentum of system to the linear momentum of debris is introduced to deorbit the debris for GME release. Next, an on-orbit directional GME storage mechanism is built, and the corresponding two optimal strategies are put forward. Both theoretical and simulation results demonstrate that GME can be stored in the expected direction on any inclined LEO below 1000 km. Deorbiting kg-level debris can be accomplished within several orbital periods with the existing magnetorquer technology. Finally, proof-of-principle experiments of the GME effect are performed and elementarily validate the LEO GME utilization in space.

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Collision-avoidance strategy for a spinning electrodynamic tether system

Li,

et al. 2024

Astrodyn

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Stability analysis and motion control of spinning electrodynamic tether system during transition into spin

Cited by 15 publications

References 21 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

Theoretical and Experimental Investigation of Geomagnetic Energy Effect for LEO Debris Deorbiting

Collision-avoidance strategy for a spinning electrodynamic tether system

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