Small-body deflection techniques using spacecraft: techniques in simulating the fate of ejecta

TL;DR

This paper presents a numerical framework for simulating asteroid ejecta behavior post-impact, integrating N-Body, SPH, and impact scaling laws to inform asteroid deflection strategies.

Contribution

It develops a simplified, adaptable model for impact ejecta evolution, combining multiple simulation techniques to improve understanding of asteroid deflection outcomes.

Findings

High-speed ejecta escape at low angles

Slow ejecta lofting and potential re-impact observed

Model behaviors under investigation for realism

Abstract

We define a set of procedures to numerically study the fate of ejecta produced by the impact of an artificial projectile with the aim of deflecting an asteroid. Here we develop a simplified, idealized model of impact conditions that can be adapted to fit the details of specific deflection-test scenarios, such as what is being proposed for the AIDA project. Ongoing studies based upon the methodology described here can be used to inform observational strategies and safety conditions for an observing spacecraft. To account for ejecta evolution, the numerical strategies we are employing are varied and include a large N-Body component, a smoothed-particle hydrodynamics (SPH) component, and an application of impactor scaling laws. Simulations that use SPH-derived initial conditions show high-speed ejecta escaping at low angles of inclination, and very slowly moving ejecta lofting off the surface at higher inclination angles, some of which re-impacts the small-body surface. We are currently investigating the realism of this and other models' behaviors. Next steps will include the addition of solar perturbations to the model and applying the protocol developed here directly to specific potential mission concepts such as the proposed AIDA scenario.