Concurrent Engineering Approach for the Preliminary Study of Hypersonic Morphing for a Cabin Escape System

Paper number

IAC-14,D1,3,10,x23996

Author

Mr. Tobias Schwanekamp, German Aerospace Center (DLR), Bremen, Germany, Germany

Coauthor

Ms. Emmanuelle David, German Aerospace Center (DLR), Germany

Coauthor

Ms. Carola Bauer, Germany

Coauthor

Dr. Martin Sippel, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Alexander Kopp, Germany

Coauthor

Mr. Magni Johannsson, DLR (German Aerospace Center), Germany

Coauthor

Mr. Rodrigo Haya-Ramos, Spain

Coauthor

Mr. Davide Bonetti, Deimos Space S.L., Spain

Coauthor

Mr. Hugo André Costa, Spain

Coauthor

Mr. Frederic Sourgen, ONERA, France

Coauthor

Mr. Emmanuel Laroche, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France

Coauthor

Mr. Franco Fossati, Italy

Coauthor

Dr. Francesco Nisticò, Aviospace, Italy

Coauthor

Mr. Giovanni Gambacciani, Aviospace, Italy

Year

2014

Abstract

HYPMOCES is a EU FP7 funded project which aims to investigate and develop the technologies in the area of control, structures, aerothermodynamics, mission and system required to enable the use of morphing in escape systems for hypersonic transport aircrafts.
To investigate, define and evaluate the reference concepts of HYPMOCES, a Concurrent Engineering (CE) Approach at DLR Bremen has been conducted.
The applied CE process is based on the optimization of the conventional established design process characterized by centralized and sequential engineering. Simultaneous presence of all relevant discipline specialists within one location and the utilization of a common data handling tool enable efficient communication among the set of integrated subsystems. The study comprised the multidisciplinary analysis and the development of all relevant subsystems for the space mission and system, e.g. with respect to system engineering, configuration, geometry, aero-/thermodynamics, trajectory and mission analysis, structure, thermal protection system and actuators. Candidate morphing schemes are proposed at the beginning of the CE study and traded-off to identify one reference candidate architecture and one backup concept that is compatible with the constraints imposed by the integration within the reference mother aircraft, not only in terms of the direct impact in mass, volume, power and complexity but also considering the overall operation of the cabin escape system and the mother aircraft. System requirements for morphing schemes and operational aspects are formulated and evaluated during the CE study. As far as possible the capsule shall be an integral part of the orbiter structure. This imposes the necessity to find the best compromise between the requirements of the capsule and the orbiter. Candidate architectures include the use of folding of wings, sliding surfaces, telescopic wings, deformable shape and tilting wings.
During the CE study the architecture approaches are investigated on a preliminary but multidisciplinary level. The proposed paper focuses on the general attributes of the CE approach as well as the initial input data for HYPMOCES, the multidisciplinary CE study process itself, the results and the lessons learned for the next steps of the project.

Abstract document

IAC-14,D1,3,10,x23996.brief.pdf

Manuscript document

IAC-14,D1,3,10,x23996.pdf (🔒 authorized access only).

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