Upcoming DLR Reusability Flight Experiment

Paper number

IAC-17,D2,6,1,x39677

Author

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

Coauthor

Dr. Peter Rickmers, Deutsches Zentrum für Luft- und Raumfahrt, Germany

Coauthor

Mr. Alexander Kallenbach, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Sven Stappert, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Janis Häseker, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Renè Schwarz, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

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

Coauthor

Mr. Andreas Flock, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Thomas Thiele, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Andreas Bierig, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Jens Windelberg, Deutsches Zentrum für Luft- und Raumfahrt, Germany

Coauthor

Mr. Eugen Ksenik, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany

Year

2017

Abstract

After the successful hypersonic flight experiments SHEFEX I and II, the German Aerospace Center (DLR) is now investigating the realization of the Reusability Flight Experiment (ReFEx). This successor mission shall be launched on a sounding rocket VSB-30 in the time frame of 2020/2021 and shall achieve a reentry velocity of more than Mach 5. The main goal is the demonstration of a controlled autonomous re-entry flight from hypersonic velocity down to subsonic range and to test key technologies required for future reusable booster system. So far, two Concurrent Engineering (CE) studies were conducted to investigate the feasibility of this sophisticated project. The required subsystems, including sensors and actuators as well as their interfaces have been defined and different options were assessed regarding matters like the scientific output, complexity, risk, and cost. The current configuration of ReFEx has a re-entry mass of about 450 kg and a length of 2.7 m and a wingspan of 1.1 m. This paper provides a system overview, addresses systems engineering aspects and main challenges regarding the mission realization. For example, to meet the VSB-30 launcher requirement, the wings of the ReFEx experiment were designed foldable. Therefore, special attention was paid to a passive and reliable lock mechanism for the wings.

Abstract document

IAC-17,D2,6,1,x39677.brief.pdf

Manuscript document

IAC-17,D2,6,1,x39677.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.