R. Wuilbercq , J. Y. Andro , L. Serre , H. Taguchi , A. Tremolet
DoI Number XXX-YYY-ZZZ
Conference Number HiSST 2018_39801107
This work is part of a joint effort between the French Aerospace Lab (ONERA) and the Japan Aerospace Exploration Agency (JAXA) to demonstrate a number of key enabling technologies for future reusable space transportation systems. A pre-cooled turbojet engine is currently being investigated at the JAXA as a key technology that could enable the design of a sub-orbital space plane – i.e. the first stage of a two-stage-to-orbit space plane – and, potentially, that of a future hypersonic airliner. More particularly, the present study focuses on the planning and technical feasibility of a scaled-down, low-cost, and reusable hypersonic flight demonstrator, based on the precooled turbojet concept explored by the JAXA, using a Multi-disciplinary Design and Optimisation (MDO) environment. This paper thus describes the inception of a framework for the sizing of a potential flight testbed under a number of mission, operational and budget specifications that are representative of the full-scale vehicle. The sizing of the experiment is thus undertaken using a series of reduced-order models for the evaluation of the performance of a round mission from a given takeoff point. The mission of the experimental flight vehicle will indeed be to accelerate from a standstill up to a target Mach number before initiating a deceleration phase in order to return to its take-off point.