An active debris removal parametric study for LEO environment remediation

Liou, J.‐C.

doi:10.1016/j.asr.2011.02.003

Cited by 285 publications

(144 citation statements)

References 9 publications

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“…The study by Liou and Johnson [1] indicated that the LEO debris population has reached a point where the environment was unstable and random collision would force the LEO population to increase even without any future launches. Currently-adopted mitigation measures, such as limiting postmission orbital lifetime to less than 25 years, are insufficient to stabilize the future LEO debris environment [2,3]. In addition to mitigation measures, the active removal of non-operating spacecraft, as well as rocket bodies, will be mandatory avoiding proliferation of space debris [4].…”

Section: Introductionmentioning

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: Introductionmentioning

confidence: 99%

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

et al. 2017

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“…rocket bodies), or when the satellites themselves reach the end of their useful life [1], [3]. Such debris present an ever-increasing risk to satellites and other spacecraft, as highlighted in 2009 by the high-velocity collision between the then operational Iridium 33 and the inactive Kosmos 2251 satellites [3].…”

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confidence: 99%

Rollable Multisegment Dielectric Elastomer Minimum Energy Structures for a Deployable Microsatellite Gripper

Araromi

Gavrilovich

Shintake

et al. 2015

IEEE/ASME Trans. Mechatron.

232

152

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Abstract-Debris in space present an ever-increasing problem for spacecraft in Earth orbit. As a step in the mitigation of this issue, the CleanSpace One (CSO) microsatellite has been proposed. Its mission is to perform active debris removal of a decommissioned nanosatellite (the CubeSat SwissCube). An important aspect of this project is the development of the gripper system that will entrap the capture target. We present the development of roll-able dielectric elastomer minimum energy structures (DEMES) as the main component of CSO's deployable gripper. DEMES consist of a prestretched dielectric elastomer actuator membrane bonded to a flexible frame. The actuator finds equilibrium in bending when the prestretch is released and the bending angle can be changed by the application of a voltage bias. The inherent flexibility and lightweight nature of the DEMES enables the gripper to be stored in a rolled-up state prior to deployment. We fabricated proof of concept actuators of three different geometries using a robust and repeatable fabrication methodology. The resulting actuators were mechanically resilient to external deformation, and display conformability to objects of varying shapes and sizes. Actuator mass is less than 0.65 g and all the actuators presented survived the rolling-up and subsequent deployment process. Our devices demonstrate a maximum change of bending angle of more than 60 degrees and a maximum gripping (reaction) force of 2.2 mN for a single actuator.Index Terms-Active debris removal (ADR), artificial muscles, deployable mechanism, dielectric elastomer actuator (DEA), space debris.

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“…Recent computer modelling studies have suggested that the LEO debris population may be stabilised at current levels through the removal of five large, intact objects per year [14]. Whilst this approach can only be successful if the objects that are targeted would otherwise contribute to future collision activity, it does provide a more cost-effective approach to remediation than the removal, en masse, of all debris objects.…”

Section: A Cloud-based Architecture Solution To the Ssa Case Studymentioning

confidence: 99%

Clouds in Space: Scientific Computing using Windows Azure

Johnston

O'Brien

Lewis

et al. 2013

Journal of Cloud Computing: Advances, Systems and Applications

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In this paper we report upon the cloud-based solution that we designed and implemented for space situational awareness. We begin by introducing the background to the work and to the area of space situational awareness. This concerns tracking the hundreds of thousands of known objects in near-Earth orbits, and determining where it is necessary for satellite operators to conduct collision-avoidance manoeuvres to protect their satellites. We also discuss active debris removal, which would be necessary to stabilise the debris population at current levels. We examine the strengths that cloud-based solutions offer in general and how these specifically fit to the challenges of space situational awareness, before describing the architecture we designed for this problem. We demonstrate the feasibility of solving the space situational awareness problem with a cloud-based architecture and note that as time goes on and debris levels rise due to future collisions, the inherent scalability offered by a cloud-based solution will be invaluable.

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An active debris removal parametric study for LEO environment remediation

Cited by 285 publications

References 9 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

Rollable Multisegment Dielectric Elastomer Minimum Energy Structures for a Deployable Microsatellite Gripper

Clouds in Space: Scientific Computing using Windows Azure

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