Cleaning space debris with a space-based laser system

Shen, Shuangyan; Xing, Jun; Chang, Hao

doi:10.1016/j.cja.2014.05.002

Cited by 53 publications

(28 citation statements)

References 15 publications

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“…In this work two spherical shape space debris made of aluminum (2024) density (2.785 gm/cm 3 ), diameters (1, 10 cm) [12,13] were selected for investigation. The selection criteria depend on the abundance of this type of aluminum in most spacecraft structures.…”

Section: Resultsmentioning

confidence: 99%

Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1-10 cm) in LEO under Atmosphere Drag Effects

Al-Zaidi¹,

Al-Bermani²,

Taleb³

2020

JK-Physics

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This study attempts to address the lifetime and reentry of the space debris in low earth orbit LEO which extends from 200 to 1200 km. In this study a new Computer programs were designed to simulate the orbit dynamics of space debris lifetime and reentry under atmospheric drag force using Runge-Kutta Method to solve the differential equations of drag force. This model was adapted with the Drag Thermosphere Model (DTM78, 94), the Aluminum 2024 space debris in certain size (1&10 cm) were used in this study, which is frequently employed in the structure of spacecraft and aerospace designs. The selected atmospheric model for this investigation was the drag thermospheric models DTM78 and DTM94, because of this dependence on solar and geomagnetic activities. It was found that the lifetime of the space debris increases with increasing perigee altitudes. It was also found that the elliptical shape of the debris orbit would change gradually into a circular shape, then its kinetic energy would be transformed into heat and hence the debris might be destroyed in the dense atmosphere.

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Section: Resultsmentioning

confidence: 99%

Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1-10 cm) in LEO under Atmosphere Drag Effects

Al-Zaidi¹,

Al-Bermani²,

Taleb³

2020

JK-Physics

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“…Laser ablation: Shen et al [3], explores the optimal choice of laser transmission by taking into consideration four conditions that should be met: high average power and peak power, high pulse energy, high laser beam quality, and mature technology with simple maintenance [3]. The authors describe a reliable solid-state laser operating in a burst mode that does not have a mechanically driven component and no need to refuel the system [3]. They determine the optimal mirror diameter to be 2.44 m to obtain a 15 cm focal spot considering the difficulty of tracking and energy waste [3].…”

Section: Methodsmentioning

confidence: 99%

“…The authors describe a reliable solid-state laser operating in a burst mode that does not have a mechanically driven component and no need to refuel the system [3]. They determine the optimal mirror diameter to be 2.44 m to obtain a 15 cm focal spot considering the difficulty of tracking and energy waste [3]. They also demonstrate that the optimal laser repeat frequency to be 100 Hz assuming laser pulse energy is 1 kJ and considering effectiveness and cost [3].…”

Section: Methodsmentioning

confidence: 99%

Evaluating the Effectiveness and Efficiency of a Laser Guided and Electrodynamic Approach to Performing Space Debris Removal

2022

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Introduction: Space debris is an alarming problem that researchers around the globe have been working to solve. These space particles consist of meteorites that exist in space as well as fragmentation originating from satellites and spacecraft. The effect of these debris can be devastating upon collision with devices such as satellites, telecommunicators, etc. The National Aeronautics and Space Administration database reported that approximately 200 million objects were found orbiting close to the Earth. Currently, different techniques are under investigation to eliminate space debris. Methods: Space debris varies in size, thus can only be fully removed if the various sizes are accounted for. We propose a model where efficiency and effectiveness can be optimized towards certain sizes of space debris. The laser ablation process involves concentrating multiple laser pulses on space debris to create plasma plumes which eject from the cavity created in the material at a substantial velocity, acting against the material's original orbit and can be guided into Earth's atmosphere where it will disintegrate or fall into the ocean. An electrodynamic net will also be used to attract and capture space debris. Once taken a hold of, this debris will be transported by the satellite towards the Earth's atmosphere. Here both the satellite and the debris will be disintegrated. Results: To solve this problem, this study proposes a dual-debris model which combines a laser-guided and electrodynamic approach. The first process involves short-wavelength laser pulses that focus on debris greater than 10 cm in diameter, generating plasma plume ejections that decrease orbital velocity. The electrodynamic approach will attract and dispose materials less than 10 cm in diameter with an electrically charged net dispatched by a satellite, which is then guided towards the Earth. Discussion: Based on the results of the studies analyzed, laser ablation is an effective method of removing large space debris while the electrodynamic net serves as a cost-efficient method of eliminating small debris. Both methods allow targeted debris to approach and disintegrate in the Earth's atmosphere or fall into the ocean. Results from previous studies were largely based on simulations, and further testing should be done.

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“…Therefore, laser-based concepts of space debris removal have been formulated and investigated for both Earth-based as well as satellite-borne laser operations for several decades now. [6][7][8][9][10][11] In many of those studies, the specific target geometry has been neglected though it has a significant impact on the amount and direction of the laser-induced velocity increment. Therefore, we analyzed laser-induced momentum coupling on irregularly shaped targets in our previous paper.…”

Section: Laser-based Remediation Strategiesmentioning

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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Cleaning space debris with a space-based laser system

Cited by 53 publications

References 15 publications

Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1-10 cm) in LEO under Atmosphere Drag Effects

Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1-10 cm) in LEO under Atmosphere Drag Effects

Evaluating the Effectiveness and Efficiency of a Laser Guided and Electrodynamic Approach to Performing Space Debris Removal

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

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