A study of the material density distribution of space debris

Opiela, J.

doi:10.1016/j.asr.2008.12.013

Cited by 33 publications

(14 citation statements)

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“…In turn, due to the lower ablation threshold which scales with ffiffi ffi τ p , less pulse energy is needed. Since aluminum appears to be a rather prevalent material in small-sized space debris, 30 it constitutes a good starting point for our considerations on laser-matter interaction. Following the proposals from the literature in Table 2, we performed a laser parameter study, using Polly-2T for laser-matter interaction with aluminum targets.…”

Section: Laser-matter Interaction Databasementioning

confidence: 99%

Momentum predictability and heat accumulation in laser-based space debris removal

et al. 2018

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Small space debris objects of even a few centimeters can cause severe damage to satellites. Powerful lasers are often proposed for pushing small debris by laser-ablative recoil toward an orbit where atmospheric burn-up yields their remediation. We analyze whether laser-ablative momentum generation is safe and reliable concerning predictability of momentum and accumulation of heat at the target. With hydrodynamic simulations on laser ablation of aluminum as the prevalent debris material, we study laser parameter dependencies of thermomechanical coupling. The results serve as configuration for raytracing-based Monte Carlo simulations on imparted momentum and heat of randomly shaped fragments within a Gaussian laser spot. Orbit modification and heating are analyzed exemplarily under repetitive laser irradiation. Short wavelengths are advantageous, yielding momentum coupling up to ∼40 mNs∕kJ, and thermal coupling can be minimized to 7% of the pulse energy using short-laser pulses. Random target orientation yields a momentum uncertainty of 86% and the thrust angle exhibits 40% scatter around 45 deg. Moreover, laser pointing errors at least redouble the uncertainty in momentum prediction. Due to heat accumulation of a few Kelvin per pulse, their number is restricted to allow for intermediate cooldown. Momentum scatter requires a sound collision analysis for conceivable trajectory modifications. © The Authors. Published by SPIE under a Creative Commons Attribution 3.0 Unported License. Distribution or reproduction of this work in whole or in part requires full attribution of the original publication, including its DOI.

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Section: Laser-matter Interaction Databasementioning

confidence: 99%

Momentum predictability and heat accumulation in laser-based space debris removal

et al. 2018

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“…At least 7,000 of them are large enough that they were not completely burnt up during reentry and eventually struck the Earth's surface. Study by Opiela (2009) concluded that 30% of payload debris consists of medium to high-density and 10% of rocket bodies are high-density with higher endurance to atmospheric ablation. Most of the survive debris will fall on the ocean such that the threat of space debris reentry is generally considered to be less risky.…”

Section: Abstrakmentioning

confidence: 99%

Basic Lifetime Model for Reentry Time Prediction of Artificial Space Objects

Rachman

Priyatikanto

2018

JSD

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The identification of space debris and the prediction of its orbital lifetime are two important things in the initial mitigation processes of threat from falling debris. As a part of the development of related decision support system, this study focuses on developing a basic lifetime model of artificial space object based on a well-known theory and prediction scheme in the field of satellite reentry research. Current implemented model has not accounted atmospheric oblateness or other correcting factors, but it has a reasonably good performance in predicting reentry time of several objects with various initial eccentricities. Among 30 predictions conducted to 10 objects that reentered the atmosphere from 1970 to 2012, there are 13 calculations that yield prediction time with accuracy of < 30% relative to the actual reentry time. In addition, 11 calculations yields prediction time which were more accurate compared to the outputs from SatEvo software that is currently used in the decision support system on the falling debris operated by Space Science Center LAPAN. These results were considered satisfying and can be developed further by adopting the updated atmospheric model and by calculating other relevant correcting factors.

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“…To that end ORDEM 3.0 organizes debris populations mainly by material density and associated type. This choice is encouraged by the in-situ STS (Shuttle Transportation System) database of radiator and window impacts, along with data of past ground impact tests [3][4][5][6][7]. These support a representation of on-orbit debris in terms of the material density categories -low density (1.4 g/cm 3 ), medium density (2.8 g/ cm 3 ), and high density (7.9 g/cm 3 ).…”

Section: Modeled Orbital Debris Populationsmentioning

confidence: 99%