Parameter-space study of kinetic-impactor mission design

TL;DR

This study systematically analyzes kinetic-impactor asteroid deflection missions across the entire relevant orbital parameter space, identifying optimal strategies and potential challenges based on asteroid orbit characteristics.

Contribution

It reduces the complex parameter space to three key variables and explores optimal mitigation solutions considering practical constraints.

Findings

Different classes of optimal solutions linked to asteroid orbital properties

Identification of parameter space regions with potential difficulties

Preliminary mission design guidelines for asteroid deflection

Abstract

While almost all potentially hazardous asteroids (PHAs) with a size larger than one kilometre have been discovered, it is well-known that the vast majority of the smaller ones are in fact yet to be found. There is therefore an excellent motivation to consider at once all possible Earth-crossing orbits, and to undertake a systematic study of mitigation missions for the entire parameter space of orbital elements. It is shown that the whole parameter space can be reduced, without loss of generality, to only three relevant dimensionless parameters: the eccentricity and inclination of the asteroid orbit, and the asteroid true anomaly at impact. Ballistic kinetic-impactor mitigation missions are studied for the entire parameter space, considering critical feasibility constraints such as the launcher performance and the illumination conditions at deflection. Different classes of optimal solutions are found to exist and can be directly linked to asteroid orbital properties. The aim of this work is to help identify an appropriate response to the potential threat of a collision of a near-Earth object with our planet, to provide a preliminary mission design, and to determine in which parts of parameter space difficulties may arise. (abridged)