Space debris capture by a joint compliance controlled robot

Nishida, Shin-Ichiro; Yoshikawa, Tetsuro

doi:10.1109/aim.2003.1225145

Cited by 19 publications

(16 citation statements)

References 3 publications

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“…It is intended that medium-size debris, if not fully arrested by the membrane, will be sufficiently retarded by it and go through the structure without damaging it. The overall compliance of the device is also advantageous for absorbing part of the impact energy of the debris, as it has been demonstrated for a compliant space manipulator in debris capture (Nishida and Yoshikawa (2003)).…”

Section: Tessellated Cupola Unfoldingmentioning

confidence: 99%

A deployable mechanism concept for the collection of small-to-medium-size space debris

St-Onge

Sharf

Sagnières

et al. 2018

Advances in Space Research

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Current efforts in active debris removal strategies and mission planning focus on removing the largest, most massive debris. It can be argued, however, that small untrackable debris, specifically those smaller than 5 cm in size, also pose a serious threat. In this work, we propose and analyze a mission to sweep the most crowded Low Earth Orbit with a large cupola device to remove small-tomedium-size debris. The cupola consists of a deployable mechanism expanding more than 25 times its storage size to extend a membrane covering its surface. The membrane is sufficiently stiff to capture most small debris and to slow down the medium-size objects, thus accelerating their fall. An overview of the design of a belt-driven rigid-link mechanism proposed to support the collecting cupola surface is presented, based on our previous work. Because of its large size, the cupola will be subject to significant aerodynamic drag; thus, orbit maintenance analysis is carried out using the DTM-2013 atmospheric density model and it predicts feasible requirements. While in operation, the device will also be subject to numerous hyper-velocity impacts which may significantly perturb its orientation from the desired attitude for debris collection. Thus, another important feature of the proposed debris removal device is a distributed array of flywheels mounted on the cupola for reorienting and stabilizing its attitude during the mission. Analysis using a stochastic modeling framework for hyper-velocity impacts demonstrates that three-axes attitude stabilization is achievable with the flywheels array. MASTER-2009 software is employed to provide relevant data for all debris related estimates, including the debris fluxes for the baseline mission design and for assessment of its expected performance. Space debris removal is a high priority for ensuring sustainability of space and continual launch and operation of man-made space assets. This manuscript presents the first analysis of a small-to-medium size debris removal mission, albeit finding it to not be economically viable at the present time.

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Section: Tessellated Cupola Unfoldingmentioning

confidence: 99%

A deployable mechanism concept for the collection of small-to-medium-size space debris

St-Onge

Sharf

Sagnières

et al. 2018

Advances in Space Research

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show abstract

“…Hence, it is common to assume that the positioning of an outline is performed by the rendezvous control of the flight function of a satellite. Furthermore, 0.1 m or less is acceptable as the accuracy of the rendezvous control by using the stereo visual-measurement system [8,9]. Hence, the range of the attitude adjustment angle of the capture mechanism in which the position adjustment by robot arm operation is required is relatively small.…”

Section: Composition Of a Capture Robot Armmentioning

confidence: 99%

Lightweight Robot Arm for Capturing Large Space Debris

Nishida¹,

Uenaka²,

Matsumoto³

et al. 2018

JEE

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Effective measures to mitigate space debris are urgently required. Active removal of space debris presents the most effective measures. This study examines a micro robotic satellite with a simple robot arm for active space debris removal. In this study, the details of a proposed active space debris removal system with a robot arm are proposed. The robot arm has flexible joints and a control method to capture the target. The results of feasibility studies, the performance assumed at each step, the prototyping of the capturing robot arm with flexible joints and with a new end-effecter, and their experiment result are presented.

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“…There have been several incidents producing the high number of debris. Two of them have been especially severe: (i) A 2007 Chinese anti-satellite missile test producing more than 1200 catalogued pieces of debris and an estimated 35,000 pieces of a size of 1 cm and larger, resulting in the most severe orbital debris cloud in history (NPDPO, 2009) (ii) the collision of the Iridium-33 and Kosmos-2251 satellites in 2009, which was the first accidental hypervelocity collision of two intact spacecraft (Nishida and Yoshikawa, 2003). Fig.…”

Section: Recent Debris Incidentsmentioning

confidence: 99%

“…The timeline of the growth in the number of objects being tracked in orbit. Due to limited tracking capabilities (limited to larger than 10 cm), the actual number of objects in orbit is estimated to be 2 to 3 times the numbers in the figure (Nishida and Yoshikawa, 2003) Total objects Currently, collisions are the smallest contributor to fragments of debris. However, as the number of debris objects increases, collisions become more likely, thus creating yet more debris (COPUOS, 2007).…”

Section: Figmentioning

confidence: 99%

Space Debris Removal Mechanism Using CubeSat with Gun Shot Facilities

Bhattarai¹,

Shang²

2018

American Journal of Applied Sciences

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Space derbies is a very perilous problem and most of the proposed methods for space debris removal are not successfully serviceable for all sized space junk. Keeping in view the limitation of the existing methods of debris removal techniques an active approach is needed and in this regard required to be instigated purposefully. In more than half a century of space activities, by using above 4800 launches have placed around 6000 satellites into orbit, of which less than a thousand are still operating. In this research, a new concept to remove small space junks of Low Earth Orbit (LEO) is proposed which functions by using CubeSat with Gunshot equipment. The target of this concept is to confiscate the small-sized space junk of ranges 0.2 to 1 inches diameter and which will be identified by collaborating with FGAN radar. CubeSat is loaded five bullets of 0.1 kg with strong thruster gunshot technology and after the first shot, reaction force will help to change the orbit of the satellite to find out the second space debris. This research intended to comprehend and helps to get assess of small-sized space debris removal activity in terms of the simple business model.

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Space debris capture by a joint compliance controlled robot

Cited by 19 publications

References 3 publications

A deployable mechanism concept for the collection of small-to-medium-size space debris

A deployable mechanism concept for the collection of small-to-medium-size space debris

Lightweight Robot Arm for Capturing Large Space Debris

Space Debris Removal Mechanism Using CubeSat with Gun Shot Facilities

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