Electromagnetic-launch-based method for cost-efficient space debris removal

AbstractThe increase in space debris orbiting Earth is a critical problem for future space missions. Space debris removal has thus become an area of interest, and significant research progress is being made in this field. However, the exorbitant cost of space debris removal missions is a major concern for commercial space companies. We therefore propose the debris removal using electromagnetic launcher (DREL) system, a ground-based electromagnetic launch system (railgun), for space debris removal missions. The DREL system has three components: a ground-based electromagnetic launcher (GEML), suborbital vehicle (SOV), and mass of micrometer-scale dust (MSD) particles. The average cost of removing a piece of low-earth orbit space debris using DREL was found to be approximately USD 160,000. The DREL method is thus shown to be economical; the total cost to remove more than 2,000 pieces of debris in a cluster was only approximately USD 400 million, compared to the millions of dollars required to remove just one or two pieces of debris using a conventional space debris removal mission. By using DREL, the cost of entering space is negligible, thereby enabling countries to remove their space debris in an affordable manner.

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On the Design of an Active Debris Removal Architecture for Low Earth Orbit Space Debris Remediation

AIAA SPACE 2011 Conference & Exposition ◽

10.2514/6.2011-7250 ◽

2011 ◽

Cited By ~ 2

Author(s):

Jesse Quinlan ◽

Christopher Jones ◽

Vivek Vittaldev ◽

Alan Wilhite

Keyword(s):

Space Debris ◽

Orbit Space ◽

Low Earth Orbit ◽

Earth Orbit ◽

Active Debris Removal ◽

Debris Removal

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Innovative observing strategy and orbit determination for Low Earth Orbit space debris

Planetary and Space Science ◽

10.1016/j.pss.2011.11.012 ◽

2012 ◽

Vol 62 (1) ◽

pp. 10-22 ◽

Cited By ~ 5

Author(s):

A. Milani ◽

D. Farnocchia ◽

L. Dimare ◽

A. Rossi ◽

F. Bernardi

Keyword(s):

Orbit Determination ◽

Space Debris ◽

Orbit Space ◽

Low Earth Orbit ◽

Earth Orbit

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A laser-optical system to re-enter or lower low Earth orbit space debris

Acta Astronautica ◽

10.1016/j.actaastro.2013.07.031 ◽

2014 ◽

Vol 93 ◽

pp. 418-429 ◽

Cited By ~ 28

Author(s):

Claude R. Phipps

Keyword(s):

Optical System ◽

Space Debris ◽

Orbit Space ◽

Low Earth Orbit ◽

Earth Orbit

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Space Debris Removal under Spatial Grasp Technology

Network and Communication Technologies ◽

10.5539/nct.v6n1p16 ◽

2021 ◽

Vol 6 (1) ◽

pp. 16

Author(s):

Peter Simon Sapaty

Keyword(s):

Space Debris ◽

Low Earth Orbit ◽

Space Environment ◽

Satellite Constellations ◽

Distributed Resources ◽

Debris Removal ◽

Combined Solution ◽

Directed Energy ◽

Minimum Interaction ◽

High Level

The threats of space debris are enormously high, which are increasing due to launch of multi-satellite constellations, especially in low-Earth orbit, with millions of pieces of junk there. Different passive and active debris removal methods are being developed like self-deorbiting of used satellites, drag sails, mechanical grasps, tethers and nets, also directed energy, lasers including. Space junk is the responsibility of the whole mankind, and the problem of managing space debris is both the international challenge and the opportunity to preserve the space environment for future space exploration missions. The paper shows how self-organized constellation networks of deorbiting satellites can organize multiple cleaning operations autonomously under the developed Spatial Grasp Technology (SGT), with cooperative involvement of the whole network and minimum interaction with costly ground antennas and stations. It also offers a unique solution where most dangerous junk items can themselves be treated as active virtual-physical items freely moving through terrestrial and celestial environments and ultimately finding, by their own initiative, the proper cleaning satellites. This can effectively organize the global junk management and removal problem, where the active junk items can keep initiative of self-removal for any time needed and using any distributed resources. A combined solution is also offered with initial global search for approximate satellite-debris matching, after which the junk is delegated its own initiative to find the absolute match by traveling around the globe as far and as long as required. The paper shows and explains different practical cleaning scenarios in the high-level Spatial Grasp Language (as key element of SGT) and possibilities of quick implementation of the approach.

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Human Survivability Issues in the Low Earth Orbit Space Debris Environment

Preservation of Near-Earth Space for Future Generations ◽

10.1017/cbo9780511564925.006 ◽

1994 ◽

pp. 56-70

Author(s):

Bernard Bloom

Keyword(s):

Space Debris ◽

Orbit Space ◽

Low Earth Orbit ◽

Earth Orbit

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The predicted growth of the low-Earth orbit space debris environment — an assessment of future risk for spacecraft

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/09544100jaero192 ◽

2007 ◽

Vol 221 (6) ◽

pp. 975-985 ◽

Cited By ~ 4

Author(s):

P H Krisko

Keyword(s):

Space Debris ◽

Orbit Space ◽

Low Earth Orbit ◽

Earth Orbit ◽

Future Risk

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Surface Modification of Space Exposed Materials Induced by Low Energetic Proton Irradiation

The Journal of the Astronautical Sciences ◽

10.1007/s40295-021-00277-w ◽

2021 ◽

Author(s):

Denise Keil ◽

Frederic Seiz ◽

Nils Bartels ◽

Wolfgang Riede ◽

Maciej Sznajder ◽

...

Keyword(s):

Space Debris ◽

Spectroscopic Analysis ◽

Proton Irradiation ◽

Low Earth Orbit ◽

Low Energy ◽

Optical Data ◽

Metallic Surfaces ◽

Fiber Reinforced Plastic ◽

Reinforced Plastic ◽

Debris Removal

AbstractThe aim of this paper is to verify if commonly occurring space debris materials change their reflectivity and morphology after being exposed to low energy protons. Therefore, a set of six different materials frequently used in spacecraft engineering was irradiated with low energy (100 keV) protons to simulate the aging of their surfaces due to space radiation in low Earth orbit (LEO). A microscopic and spectroscopic analysis of the irradiated samples reveals that the tested materials containing organic polymers (Polytetrafluoroethylene (PTFE) and carbon fiber reinforced plastic (CFRP)) show changes in surface morphology. Metallic surfaces did not show surface modifications but we found changes in the reflectivity of coated polyimide sheets, like used in Multi Layer Insulation blankets, during and after proton irradiation. Our results show that space materials exhibit significant changes after irradiation equivalent to the dose accumulated after 100 years in LEO. This knowledge is highly relevant for the interpretation of optical data related to the observation of space debris as well as to studies about laser-matter interaction for laser-based debris removal.

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Geomagnetic Energy Approach to Space Debris Deorbiting in a Low Earth Orbit

International Journal of Aerospace Engineering ◽

10.1155/2019/5876861 ◽

2019 ◽

Vol 2019 ◽

pp. 1-18 ◽

Cited By ~ 1

Author(s):

Guanhua Feng ◽

Wenhao Li ◽

Heng Zhang

Keyword(s):

Angular Momentum ◽

Geomagnetic Field ◽

Space Debris ◽

High Efficiency ◽

Low Earth Orbit ◽

Future Application ◽

Spin Angular Momentum ◽

Momentum Exchange ◽

Debris Removal ◽

Low Earth Orbits

The space debris removal problem needs to be solved urgently. Over 70% of debris is distributed between the 500 km and 1000 km low Earth orbits (LEO), and existing methods may be theoretically feasible but are not the high-efficiency and low-consumption methods for LEO debris removal. Based on the torque effect of a static magnet interacting with the geomagnetic field, a new spin angular momentum exchange (SAME) method by geomagnetic excitation (without working medium consumption) for LEO active debris deorbiting is proposed. The LEO delivery capability of this method is researched. Two kinds of spin angular momentum accumulation (SAMA) strategies are proposed. Then through numerical simulation under the dipole model and International Geomagnetic Reference Field (IGRF11) model, the results confirm the physical feasibility and basic performance of the proposed method. The method can be applied to the regions of the LEO below 1000 km with different altitudes/inclinations and eccentricities, and with existent magnetorquer technology, only several days of preparation is required for about 104 m·kg mechanism-scale-debris-mass deorbiting, which can be used for deorbiting missions in debris-intensive areas (altitude≤1000 km); without consideration of external effects on the geomagnetic field distribution, it has the same deorbiting capability with that of the LEO below 1000 km when the altitude is over 1000 km. Besides, the method is characterized by explicit mechanism, flexible control strategy and application, and low dependence on the scale. Finally, the key technology requirements and future application of LEO active debris removal and on-orbit delivery by using SAME are prospected.

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