A Robotic Concept for the NASA Asteroid-capture Mission

2015 ◽  
Author(s):  
Angel Flores-Abad ◽  
Luis G. Crespo
Keyword(s):  
Asteroid Capture

scholarly journals Low-energy near Earth asteroid capture using Earth flybys and aerobraking

2018 ◽  
Vol 61 (8) ◽  
pp. 2099-2115 ◽  
Author(s):  
Minghu Tan ◽  
Colin McInnes ◽  
Matteo Ceriotti
Keyword(s):  
Low Energy ◽  
Earth Asteroid ◽  
Asteroid Capture

scholarly journals Low-Energy Near-Earth Asteroid Capture Using Momentum Exchange Strategies

2018 ◽  
Vol 41 (3) ◽  
pp. 632-643 ◽  
Author(s):  
Minghu Tan ◽  
Colin R. McInnes ◽  
Matteo Ceriotti
Keyword(s):  
Low Energy ◽  
Momentum Exchange ◽  
Earth Asteroid ◽  
Asteroid Capture

scholarly journals Near-Earth Asteroid Capture via Using Lunar Flyby plus Earth Aerobraking

Universe ◽  
2021 ◽  
Vol 7 (9) ◽  
pp. 316
Author(s):  
Yirui Wang ◽  
Mingtao Li
Keyword(s):  
Mass Loss ◽  
Fuel Consumption ◽  
Potential Method ◽  
Design Stage ◽  
Loss Ratio ◽  
The Earth ◽  
Effective Option ◽  
Transfer Orbit ◽  
Preliminary Design Stage ◽  
Asteroid Capture

Capturing Near-Earth Asteroids (NEAs) in the Earth-Moon system is a potential method of future space exploration and resource utilization. In order to make the captured NEA easily rendezvoused by spacecrafts, it is expected to capture the asteroid in a low-energy and low-inclination orbit. Lunar flyby and Earth aerobraking have been proved to be effective energy-saving methods in asteroid retrieval missions. Based on the Earth aerobraking capture strategy, if a lunar flyby process is performed before the asteroid enters the atmosphere, the thermal ablation of the asteroid in the atmosphere is expected to be alleviated. This paper proposes a lunar flyby plus Earth aerobraking method to capture an NEA. Using Geostationary Transfer Orbit (GTO) as the target orbit, the efficiency of three different capture strategies (direct capture strategy, Earth aerobraking capture strategy and lunar flyby plus Earth aerobraking capture strategy) are compared. Compared to the Earth aerobraking capture strategy, simulation results show that the main advantage of the lunar flyby plus Earth aerobraking capture strategy is that the mass loss ratio can be reduced (15 real asteroids are used as examples and mass loss ratio can be reduced by 0.98–3.39%). For example, for an asteroid with a diameter of 5 m, the mass is about 170.17 tons (with a density of 2.6g/cm3), reducing the mass loss ratio by 1% means that 1701.7 kg of the asteroid materials can be saved. Meanwhile, if the asteroid has a suitable phase for lunar flyby, while reducing the mass loss ratio, the fuel consumption can also be reduced. Furthermore, the conditions that do not require maneuvering between the lunar flyby and Earth aerobraking are preliminarily discussed. During the preliminary design stage of asteroid retrieval missions, compared with the Earth aerobraking capture strategy, lunar flyby plus Earth aerobraking capture strategy provides a potentially effective option for reducing the mass loss and the fuel consumption.

Asteroid Capture

Asteroids ◽  
2013 ◽  
pp. 459-468
Author(s):  
Didier Massonnet
Keyword(s):  
Asteroid Capture

Asteroid capture using lunar flyby

2015 ◽  
Vol 56 (5) ◽  
pp. 848-858 ◽  
Author(s):  
Shengping Gong ◽  
Junfeng Li
Keyword(s):  
Asteroid Capture
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