Initial Sizing and Reentry Trajectory Design Methodologies for Dual-Mode-Propulsion Reusable Aerospace Vehicles

*† An evaluation of the current state of the commercial space sector coupled with the everincreasing presence of micro- and mini-satellites in the telecommunication market stresses the requirement to find an economically feasible launch opportunity for relatively small satellites. The aim of this paper is to present a series of design methodologies which will enable the initial design of a dual-propulsion uninhabited aerospace vehicle with horizontal take-off and landing capability, which will fill this niche in the space launch sector. A concept-specific initial sizing methodology is presented together with a design tool that integrates aerodynamic heating, descent trajectory optimisation and thermal protection system sizing, which form part of the development of a complete design methodology embedded in a visually-interfaced software program.

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