Solar-powered space flight

2. Structure of paper

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The structure of the paper is:

(a)    Sections 3 and 4 explore the theoretical power requirements of a hypothetical solar-powered vehicle for a series of increasingly sophisticated flight trajectory scenarios (Section 2 ignores atmospheric drag, Section 3 extends the analysis to include the impact of atmospheric drag).

(b)   Section 5 considers how large a proportion of total payload the solar power collector element of the vehicle might need to be to deliver the power requirements identified in sections 3 and 4, if we make the unrealistic assumption that all incident solar energy is converted with 100% efficiency into thrust. We introduce a two-mirror collector arrangement that appears to have close to optimal optical characteristics for this purpose.

(c)    Section 6 considers the propulsion approaches that are likely to be the most efficient when combined with the sorts of solar collectors proposed in section 5. At least in earlier trajectory phases, solar thermal propulsion seems likely to be the most attractive approach, although propellant-less solar sail propulsion methodologies may be favoured post orbital transfer.

(d)   Sections 7 and 8 consider some of the other practical challenges that such a vehicle would face. Section 6 considers in some detail the potential difficulties involved in keeping a large ultra-thin mirror sufficiently accurately positioned, whilst section 7 covers some of the other issues, including the need to ensure that the solar collector does not foul the engine exhaust plume of a solar thermal engine.

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