Collaborative Optimization of Evaluation Trajectory and Impact Deflection for Near Earth Asteroid

Abstract

Based on the problem of impacting and flying alongside a near-Earth asteroid with a single launch vehicle，a model for the coordinated optimization of the trajectories of two is proposed. The optimization objective is to minimize the weighted velocity increment of the two spacecraft. An optimization framework for the flight trajectories of the two spacecraft，which are by a single launch vehicle and fly alongside each other before impacting，is given. Constraints such as launch C₃，the impact relative velocity，and the impact sun angle are considered. The impact probe can use two transfer forms，one is direct transfer and the other is Earth flyby. This paper has optimized 15 candidate asteroids in the 2025 window and provided feasible engineering design solutions. The results can provide theoretical reference for China's asteroid defense mission.

Keywords

asteroid defense / kinetic energy impact / trajectory optimization / one rocket launching two probes