A Research on Strategy of Plume Impingement De-Tumbling Technology

Liu, Yuqi; Pan, Yi; Li, Qiang

doi:10.1109/ccdc.2018.8407916

“…Recently, an optimal guidance law has been proposed in Ref. [24], in which the impact force direction is defined by tracking the desired value based on feedback control. This method does not optimize the motion of target spacecraft directly, and the proposed objective function has a poor theoretical basis.…”

Section: Introductionmentioning

confidence: 99%

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Zhao,

Dai

2024

Nonlinear Dyn

2

0

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Detumbling is a crucial first step for on-orbit service and space debris removal. Recently, plume has become an efficient medium for detumbling failed spacecraft, which can avoid direct contact to improve operation safety. However, the traditional molecular plume may lead to an unaffordable fuel consumption, so it is necessary to propose a novel strategy to solve this problem. The Hall effect thruster is a common high specific impulse engine, which can generate high-speed plasma plume for contactless detumbling. The traditional plume models present difficulties for practical implementation due to the contradiction between the requirement of real-time computation and the limited computing capability of the spaceborne computer. To address the challenge of calculating the impact force, a fully analytical plasma plume model is proposed to substantially enhance the computing efficiency without loss of accuracy. A guidance law for optimal detumbling is proposed to mitigate the spin angular velocity while stabilizing nutation under multiple complex constraints. To facilitate the development of the detumbling control, a terminal non-singular sliding mode controller based on the saturation function (TSM-sat) is proposed, which can converge in finite time and avoid the chattering phenomenon. The Numerical results indicate that the proposed plasma plume model can significantly improve the computing efficiency and the optimal guidance law can stabilize the target within a reasonable time.

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“…To overcome the difficulty of real-time calculation in traditional models, a fully analytical plasma plume model is established which can improve the autonomy of the chaser [1]. An optimal detumbling guidance law is proposed to mitigate the spin angular velocity while stabilizing the nutation by adjusting the direction of the plasma plume and the position of the chaser in real time [2]. In order to improve the control efficiency of the chaser, a prescribed performance framework is established and a terminal non-singular sliding mode controller (TSM) is designed in this framework [3].…”

Section: Introductionmentioning

confidence: 99%

Optimal Plasma Plume Detumbling and Prescribed Performance Control for Tumbling Spacecraft

Zhao,

Dai,

Yue

2023

International Conference on Computational &Amp; Experimental Engineering and Sciences

0

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Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Zhao

¹

,

Dai

²

2023

Preprint

0

View full text Add to dashboard Cite

Detumbling is a crucial first step for on-orbit service and space debris removal. Recently, plume has become an efficient medium for detumbling failed spacecraft, which can avoid direct contact to improve operation safety. However, the traditional molecular plume may lead to an unaffordable fuel consumption, so it is necessary to propose a novel strategy to solve this problem. The Hall effect thruster is a common high specific impulse engine, which can generate high-speed plasma plume for contactless detumbling. The traditional plume models present difficulties for practical implementation due to the contradiction between the requirement of real-time computation and the limited computing capability of the spaceborne computer. To address the challenge of calculating the impact force, a fully analytical plasma plume model is proposed to substantially enhance the computing efficiency without loss of accuracy. A guidance law for optimal detumbling is proposed to mitigate the spin angular velocity while stabilizing nutation under multiple complex constraints. To facilitate the development of the detumbling control, a terminal non-singular sliding mode controller based on the saturation function (TSM-sat) is proposed, which can converge in finite time and avoid the chattering phenomenon. The Numerical results indicate that the proposed plasma plume model can significantly improve the computing efficiency and the optimal guidance law can stabilize the target within a reasonable time.

show abstract

A Research on Strategy of Plume Impingement De-Tumbling Technology

Cited by 3 publications

References 4 publications

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

Optimal Plasma Plume Detumbling and Prescribed Performance Control for Tumbling Spacecraft

Optimal detumbling guidance and control of plasma plume for tumbling spacecraft

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