The orbital evolution of a passive high-orbit fragment with large surface area

TL;DR

This paper analyzes the orbital evolution of a high-altitude, large surface area space debris, using long-term observational data and numerical modeling to propose a new de-orbiting method.

Contribution

It introduces a novel de-orbiting approach based on a detailed numerical model accounting for major perturbations affecting high-area-to-mass ratio objects.

Findings

Determined precise orbital elements of the space debris.

Developed a numerical model considering Earth's flattening, lunar, solar, and radiation effects.

Proposed a new de-orbiting method for high-altitude objects.

Abstract

The observation data for artificial celestial body 43096, which had been obtained during 2006-2012 within the framework of international project "The Scientific Network of Optical Instruments for Astrometric and Photometric Observations" - International Scientific Optical Network (ISON), were processed. The Keplerian elements and state vector as of 24 November 2006 01:55:50.76 UTC were determined. The numerical integration of the motion equations was performed accounting for the perturbations due to the polar flattening of the Earth, Moon and Sun, as well as the solar radiation pressure. Based on the numerical model of a motion in the near-Earth space that accounts for only the most powerful perturbations, a new method for de-orbiting artificial celestial bodies from high altitudes is suggested. For the first time such a considerable amount of data over long time intervals was gathered for the objects with high area-to-mass ratio that enabled to determine their specific characteristics.