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

摘要

An evaluation of the current state of the commercial space sector in conjunction with the ever-increasing presence of micro- and minisatellites in the telecommunication market stresses the requirement to establish an economically feasible launch capability for relatively small satellites. The aim of this paper is to present a series of design methodologies that will enable the initial design of dual-propulsion uninhabited aerospace vehicles with horizontal-takeoff-and-landing capabilities, which will fill this niche in the space launch sector. A concept-specific initial sizing methodology is presented with a trajectory design tool that integrates aerodynamic heating with descent trajectory optimization, which together form part of the development of a complete design methodology embedded in a visually interfaced software program.