Active debris removal: Recent progress and current trends

Bonnal, Christophe; Ruault, Jean-Marc; Desjean, Marie-Christine

doi:10.1016/j.actaastro.2012.11.009

Cited by 278 publications

(103 citation statements)

References 4 publications

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“…In addition, the right ascension of ascending node (RAAN) of the debris is spread in a region [0 [598 km 1012 km], respectively. The space debris are very close from each other in terms of inclination and altitude; the major problem associated with the multiple debris rendezvous in SSO is the dispersion in RAAN [10]. Hence, the difference in RAAN is the main factor taken into account for choosing the next visited space debris.…”

Section: Sun-synchronous Orbitmentioning

confidence: 99%

Target sequence optimization for multiple debris rendezvous using low thrust based on characteristics of SSO

et al. 2017

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A method is proposed to select the target sequence for a J2-perturbed multiple debris rendezvous mission aimed at removing dozens of debris from several thousand debris candidates running on sun-synchronous orbits (SSO). The solving methodology proceeds in two steps: Firstly, the variance of the right ascension of ascending node (RAAN) of the debris group is used for narrowing down the potential debris candidate; secondly, the debris of the candidate group that has closest RAAN to the current debris is chosen as the next debris. Research Article

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Section: Sun-synchronous Orbitmentioning

confidence: 99%

Target sequence optimization for multiple debris rendezvous using low thrust based on characteristics of SSO

et al. 2017

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“…A lot of space debris has been generated during the past 60 years of human space activities. Most of the space debris spreads within the Low Earth Orbit (LEO) region, resulting in the density of space debris on orbit is approaching the safety threshold [2,3]. It is well recognized that the existence of space debris seriously threatens the safety of human space activities and the orbiting spacecrafts, so it is essential for the whole world to remove the LEO space debris.…”

Section: Introductionmentioning

confidence: 99%

The Capturing of Space Debris with a Spaceborne Multi-fingered Gripper

Zhang

Zhan

2017

MATEC Web Conf.

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Abstract.With the massive launching of spacecraft, more and more space debris are making the low Earth orbit (LEO) much more crowded which seriously affects the normal flight of other spacecrafts. Space debris removal has become a very urgent issue concerned by numerous countries. In this paper, using SwissCube as a target, the capturing of space debris with a spaceborne four-fingered gripper was studied in order to obtain the key factors that affect the capturing effect. The contact state between the gripper fingers and SwissCube was described using a defined contact matrix. The law of momentum conservation was used to model the motion variations of the gripper and SwissCube before and after the capturing process. A zero-gravity simulation environment was built using ADAMS software. Two typical kinds of capturing processes were simulated considering different stiffness of fingers and different friction conditions between fingers and SwissCube. Comparisons between results obtained with the law of momentum conservation and those from ADAMS simulation show that the theoretical calculations and simulation results are consistent. In addition, through analyzing the capturing process, a valuable finding was obtained that the contact friction and finger flexibility are two very important factors that affect the capturing result.

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“…The geometric parameters of the cylinder, which was taken as an example in this paper, correspond to the Cosmos 3M rocket stage. Currently, about 300 such stages are in orbit in some of the most crowded orbital regions [14]. The removal of these objects from the orbits is of great importance for the space debris mitigation issue.…”

Section: Introductionmentioning

confidence: 99%

Attitude Motion of Cylindrical Space Debris during Its Removal by Ion Beam

Aslanov

Ledkov

2017

Mathematical Problems in Engineering

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The paper is devoted to the problem of space debris mitigation. Contactless method of the space debris deorbiting is considered. It is assumed that ion thrusters on the active spacecraft create the ion flow, which blows the debris and slows it down. The objectives of this work are the development of mathematical models and the research of space debris motion under the action of the ion flow. It is supposed that the space debris is a rigid body of a cylindrical shape. Calculation of ion beam force and torque was performed for a self-similar model of plasma plume expansion using the hypothesis of ion fully diffused reflection from a surface. A mathematical model describing plane motions of the cylindrical space debris under the influence of gravity gradient torque and the ion flux was constructed. It was shown that motion of the space debris around its center of mass has a significant effect on its removal time. Phase portraits, describing the motion of the space debris relative to its center of mass, were constructed. Comparison of the descent times in different motion modes was carried out. The results can be used to create new effective systems of large space debris removal.

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Active debris removal: Recent progress and current trends

Cited by 278 publications

References 4 publications

Target sequence optimization for multiple debris rendezvous using low thrust based on characteristics of SSO

Target sequence optimization for multiple debris rendezvous using low thrust based on characteristics of SSO

The Capturing of Space Debris with a Spaceborne Multi-fingered Gripper

Attitude Motion of Cylindrical Space Debris during Its Removal by Ion Beam

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