Development of in-situ Space Debris Detector

Bauer, Waldemar; Romberg, Oliver; Wiedemann, Carsten; Drolshagen, G.; Vörsmann, Peter

doi:10.1016/j.asr.2014.07.035

Cited by 16 publications

(12 citation statements)

References 20 publications

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“…In Liou (2011a), the same author states that for most operational spacecraft, "any impact by debris between 5 mm and 1 cm is likely to cause mission-ending damage." This statement has since then been supported by other studies (Nakamura et al (2015); Bauer et al (2014)).…”

Section: Small-to-medium-sized Orbital Debrissupporting

confidence: 74%

“…This paper put forward one possible solution based on a novel deployable mechanism and actuation method for the removal of small-to-medium size debris. It is also worth noting and although not explored in this work, the proposed cupola concept could also be useful as small debris detection device, along the lines of dust detector concepts that have been proposed and used in space in the past Bauer et al (2014); Kobayashi et al (2011).…”

Section: Resultsmentioning

confidence: 99%

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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: Small-to-medium-sized Orbital Debrissupporting

confidence: 74%

Section: Resultsmentioning

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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“…Such instrumentation, albeit for now with much slower readout, is being developed at DLR for the study of space debris impacts on Earth-orbiting spacecraft. [53] The integration of such a practical deflection experiment with the ground-based planetary defence infrastructures and would certainly serve to develop and inform global and local decisionmaking processes [54] and promote the further refinement of related tools [55].…”

Section: Fast Fly-by Study Kinetic Impactor and A Brief But Completmentioning

confidence: 99%

Spacecraft for Hypervelocity Impact Research – An Overview of Capabilities, Constraints and the Challenges of Getting There

Grundmann

Dachwald

Grimm

et al. 2015

Procedia Engineering

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We present an introductory overview of the capabilities, constraints and challenges to be taken into account in the design of space missions for HVI research and application, focusing on related planetary defence applications, small spacecraft approaches, using our activities and projects as examples. Large lightweight deployable structure applications are discussed, for large-scale photovoltaic arrays in advanced solar-electric propulsion missions, and for solar sailing as a non-fuel-constrained method of achieving high-energy or retrograde orbit and multiple target missions. Small asteroid landers are discussed as vehicles for precursor exploration of impact target asteroids, precision target orbit determination, and for impact process monitoring that also can be deployed from sail-based missions.

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“…The Solar Genarator based Space Debris Impact-Detector (SOLID) [6,7] is a large area impact detector which can be flown in any orbit. The incident particle (see Figure 2) which hits the solar cell could lead to an anomaly in power supply.…”

Section: Functionalitymentioning

confidence: 99%

In orbit debris-detection based on solar panels

Bauer¹,

Romberg²,

Pissarskoi³

et al. 2013

CEAS Space J

Self Cite

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The Solar Genarator based Space Debris Impact-Detector (SOLID) currently under development at DLR, has a large impact area and offers high orbital flexibility. Once placed in orbit, it will collect Space Debris (SD) and Micro-Meteoroids (MM) impact data for software validation (e.g. MASTER or ORDEM). The verification of SOLID itself will be based on High-Velocity-Impact testing (HVI-testing) anticipated at the Fraunhofer EMI (Ernst-Mach-Institute for High-Speed Dynamics in Freiburg, Germany). This paper presents the current state of SOLID development. Furthermore the setup of the engineering model as well as corresponding assumptions made in terms of the manufacturing process are presented.

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Development of in-situ Space Debris Detector

Cited by 16 publications

References 20 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

Spacecraft for Hypervelocity Impact Research – An Overview of Capabilities, Constraints and the Challenges of Getting There

In orbit debris-detection based on solar panels

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