Evolution of space tethered system’s orbit during space debris towing taking into account the atmosphere influence

Ledkov, Alexander S.; Aslanov, Vladimir S.

doi:10.1007/s11071-019-04918-6

Cited by 21 publications

(2 citation statements)

References 22 publications

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“…Usually, it consists of the mother satellite of mass m 1 moving in an unperturbed Kepler circular orbit and the sub-satellite of mass m 2 attached to the mother satellite through an elastic massless tether of length l(t). Although active debris removal using a tethered tug-debris system is a relatively new topic, several books [88][89][90] and hundreds of scientific articles have been already published [90][91][92][93]. However, many aspects of this problem remain unexplored.…”

Section: Theorem 11 (Morales-ramis (1999)) If a Hamiltonian System Is...mentioning

confidence: 99%

Dynamics and non-integrability of the double spring pendulum

Szumiński,

Maciejewski

2024

Journal of Sound and Vibration

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Section: Theorem 11 (Morales-ramis (1999)) If a Hamiltonian System Is...mentioning

confidence: 99%

Dynamics and non-integrability of the double spring pendulum

Szumiński,

Maciejewski

2024

Journal of Sound and Vibration

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“…However, most malfunctioning and endof-life satellites are non-cooperative targets that cannot provide useful information actively [8,9]. Moreover, they are usually rotating, or tumbling, because of residual angular momentum, energy dissipation, and factors such as the gravity gradient and eddy-current damping [10][11][12]. All these factors make it difficult to capture such debris [6,13].…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of detumbling a rotating satellite using flexible deceleration rod

2022

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Malfunctioning satellites are generally non-cooperative tumbling objects. Due to their complex tumbling motion, it is essential to stabilize the target within an acceptable rotating range in the pre-capture phase. In contrast to contactless methods, contact methods based on flexible devices are efficient and can generate sufficient operating torque through flexible contact. However, accurate dynamic analysis of the operation is challenging because of two limitations. It is difficult to obtain a high-efficiency description of the large deformation arising from the operating process. Moreover, the contact between a flexible device and a tumbling object is hard to detect efficiently. This paper proposes a method for detumbling a free-floating rotating satellite; it uses a flexible rod to contact the solar array of the target. The absolute nodal coordinate formulation is first applied to a rod-contact detumbling model in simulation to describe the large deformation of the rod precisely with a low computational burden. Next, a two-step method to detect the contact is employed to pinpoint the contact point and speed up the simulation: coarse detection in the contactless phase and fine detection in the contact phase. Finally, the feasibility of the contact detumbling method is verified. In addition, through the further analysis of the contact process, some characteristics of this kind of strategy are studied for the first time.

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