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A gossamer structure for end-of-life disposal of spacecraft to mitigate spacedebris is considered in comparison with other end-of-life disposal concepts todetermine when it would be preferable. A needs analysis, potential use cases,and concept-of-operations are developed. A survey of disposal strategies ispresented for comparison prior to a down-selection of viable competingtechniques; solar sailing, high and low-thrust propulsion, and electrodynamictethers. A parametric comparison of the down-selection competing techniques ispresented. Exploiting solar radiation pressure on the structure is of limitedvalue. Atmospheric drag augmentation was found to be of most benefit forend-of-life disposal when an entirely passive means is required, allowing thegossamer device to act as a fail-safe. This is applicable to only low andmedium mass spacecraft, or spacecraft that are unlikely to survive atmosphericre-entry, hence minimizing risk to human life. It does not significantly alterthe 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 largelyindependent of de-orbit time.

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