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

2022 ◽  
Vol 6 (1) ◽  
pp. 1-7
Author(s):  
Manish Angrish ◽  
Matthew Badal-Badalian ◽  
Edward Shen
2020 ◽  
Vol 29 (1) ◽  
pp. 94-106
Author(s):  
Chongyuan Hou ◽  
Yuan Yang ◽  
Yikang Yang ◽  
Kaizhong Yang ◽  
Xiao Zhang ◽  
...  

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.


2021 ◽  
Author(s):  
Han Peixian ◽  
JunLi Guo ◽  
QIHONG BAO ◽  
Tao Qin ◽  
ren ge ◽  
...  

2021 ◽  
pp. 1-9
Author(s):  
Shinichi Kimura ◽  
Eijiro Atarashi ◽  
Taro Kashiwayanagi ◽  
Kohei Fujimoto ◽  
Ryan Proffitt

2020 ◽  
Vol 43 (7) ◽  
pp. 1259-1268
Author(s):  
Mirko Leomanni ◽  
Gianni Bianchini ◽  
Andrea Garulli ◽  
Antonio Giannitrapani ◽  
Renato Quartullo

2020 ◽  
Vol 2020 (4) ◽  
pp. 55-64
Author(s):  
A.A. Fokov ◽  
◽  
S.V. Khoroshylov ◽  
D.S. Svorobin ◽  
◽  
...  

A modified scheme of the known technology for contactless space debris removal, which is called Ion Beam Shepherd, is considered. This scheme uses an aerodynamic compensator in order to reduce the propellant consumption of the additional electrojet thruster of the shepherd spacecraft. The thruster serves to compensate the spacecraft motion caused by the action of the main electrojet thruster, whose ion plume “brakes” the space debris object. The aerodynamic compensator significantly increases the spacecraft cross-sectional area compared to the space debris object one. This fact, together with the aerodynamic perturbations acting in the direction perpendicular to the orbital plane, calls for estimating the propellant consumption of the control system thruster to maintain the required position of the spacecraft relative to the space debris object in that direction. The goal of this article is to identify the advantages of using the aerodynamic compensator in space debris removal from low Earth orbits using the Ion Beam Shepherd technology. The tasks of the study are to estimate the reduction in the cost of the momentum of the additional electrojet thruster during contactless space debris object de-orbiting due to the use of the aerodynamic compensator and the additional cost of the momentum of the thruster of the spacecraft – space debris object relative position control system to correct deviations perpendicular to the orbital plane. Using a number of simplifying assumptions, integral estimates of these costs are obtained. Using these cost estimates, it is shown that the use of an aerodynamic compensator is advantageous in terms of the cost of the saved electrojet thruster propellant (xenon) regardless of the type of the spacecraft control system thruster.


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