Concept-of-Operations Disposal Analysis of Spacecraft by Gossamer Structure

TL;DR

This paper evaluates a gossamer structure for spacecraft end-of-life disposal, comparing it with other methods like solar sailing and propulsion, and finds atmospheric drag augmentation most effective for low to medium mass spacecraft.

Contribution

It introduces a concept-of-operations for gossamer structures and provides a parametric comparison with existing disposal techniques, highlighting its advantages and limitations.

Findings

Atmospheric drag augmentation is most beneficial for passive end-of-life disposal.

Gossamer structures are effective for low and medium mass spacecraft.

The maximum benefit occurs at 550-650 km altitude, independent of de-orbit time.

Abstract

A gossamer structure for end-of-life disposal of spacecraft to mitigate space debris is considered in comparison with other end-of-life disposal concepts to determine when it would be preferable. A needs analysis, potential use cases, and concept-of-operations are developed. A survey of disposal strategies is presented for comparison prior to a down-selection of viable competing techniques; solar sailing, high and low-thrust propulsion, and electrodynamic tethers. A parametric comparison of the down-selection competing techniques is presented. Exploiting solar radiation pressure on the structure is of limited value. Atmospheric drag augmentation was found to be of most benefit for end-of-life disposal when an entirely passive means is required, allowing the gossamer device to act as a fail-safe. This is applicable to only low and medium mass spacecraft, or spacecraft that are unlikely to survive atmospheric re-entry, hence minimizing risk to human life. It does not significantly alter the operating ceiling altitude but does the maximum allowable end-of-life mass. Peak mass benefit occurs in the altitude range 550 - 650 km and is largely independent of de-orbit time.