Sun-Earth debris study, Part 2: Preliminary investigation of debris-induced spacecraft survivability risks near the Sun-Earth collinear Lagrange points

Authors

Nicholas S. Reid, Air Force Institute of Technology
Robert A. Bettinger, Air Force Institute of TechnologyFollow

Document Type

Article

Publication Date

12-13-2024

Abstract

Excerpt: In the past two years of 2023-2024, two space vehicles were inserted into orbits about Sun-Earth Lagrange points, joining eight other spacecraft about the L₁ and L₂ points. As interest in these points grows and become more populated, the chance for artificial space debris to inflict hazard on the region increases. The Circular Restricted Three-Body Problem (CR3BP) may be used to propagate the motion of debris in the region, and this paper investigates the risks associated with a catastrophic spacecraft breakup occurring in currently used or planned orbits about the Sun-Earth L₁ and L₂ points.

Comments

This article appears in Aerospace Science and Technology as cited, and is available to subscribers through the DOI link below.

DOI

10.1016/j.ast.2024.109865

Source Publication

Aerospace Science and Technology

Recommended Citation

Reid, N. S., & Bettinger, R. A. (2025). Sun-Earth debris study, Part 2: Preliminary investigation of debris-induced spacecraft survivability risks near the Sun-Earth collinear Lagrange points. Aerospace Science and Technology, 157, 109865. https://doi.org/10.1016/j.ast.2024.109865