Asteroid capture using lunar flyby

This paper focuses on the approach which enables us to capture an asteroid using the lunar flyby. Assume that the asteroid is able to enter the Earth–Moon system. The orbits of the asteroid before and after lunar flybys are investigated for different Jacobi constants in the restricted three body problem. The capture will happen when the post-flyby Jacobi constant reaches certain value due to the flyby. The capture regions of different pre-flyby initial Jacobi constants are numerically explored in the diagram that is represented by two defined angles. To give an intuitive description of the capture region, it is represented by the orbital elements of the asteroid. Based on this capture region, the asteroids that can be captured through lunar flybys are chosen from the asteroid database. Finally, the capture processes of selected asteroids are validated through the ephemerides model.