Preliminary analysis of the HEXAFLY-International Vehicle

Aerotecnica Missili & Spazio

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Title Preliminary analysis of the HEXAFLY-International Vehicle
Creator Favaloro, Nunzia
Di Donato, Maria Pia
Rispoli, Attilio
Pezzella, Giuseppe
Subject Space design- Aerodynamics- Flight Mechanics- Aircraft Systems

Description Achieving airbreathing hypersonic ight is an ongoing challenge with the potential to cut air travel time and provide cheaper access to space. Waveriders are potential candidates for achieving hypersonic cruise or acceleration ight within the atmosphere. Current research tends to focus on key issues like ight mechanics, thermal loading, aero-elasticity, aerodynamic and aerothermodynamics at hypersonic speeds. Design problems in each of these areas must be solved if the design of a hypersonic waverider-like vehicle is to be viable. In this framework, the HEXAFLY-INT project aims at the test in free- ight conditions of an innovative gliding vehicle with several breakthrough technologies on-board to be launched along a suborbital trajectory. Its preliminary conceptual design has been carried out by means of a numberof numerical tools suitable to design vehicles ying in hypersonic conditions Starting from high-level requirements, preliminary aerodynamic and trajectories analyses have been carried out to assess also mission capability. Once theaeroshape and the reference mission have been identied, system and sub-system analysis have been performed to close the system loop. The main results of the design analysis carried out during the preliminary phase of the study, such as vehicle aerodynamics and aerothermodynamics, re-entry trajectories, structures and mechanisms, and on the overall system, as well, are presented in this work.
Publisher Associazione Italiana di Aeronautica e Astronautica (AIDAA)
Contributor ESA- DLR- ONERA -
Date 2018-10-22
Type info:eu-repo/semantics/article
Peer-reviewed Article
Experimental - Numerical--; Simulation;
Format application/pdf
Source Aerotecnica Missili & Spazio; Vol 97, No 3 (2018); 113-128
Language eng
Rights Copyright (c) 2018 Aerotecnica Missili & Spazio

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