Optimal trajectories are presented that intercept and rendezvous with Earth-crossing objects by using an advanced magnetoplasma spacecraft with variable low-thrust capability. A detailed optimization method is formulated to provide optimal trajectories for any threat scenarios caused by Earth-crossing asteroids/comets. The characteristics of the trajectories are analyzed to find insights into appropriate trajectories for a targeted celestial body. It is primarily illustrated that the optimal trajectories are significantly dependent on the orbital elements of the impacting object, as well as on the distance from the Earth to the target. The trajectories can be used as reference trajectories to formulate an overall concept for solving the deflection problem of the Earth-crossing objects.
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics