PHOEBUS: A High Lift-over-Drag Vehicle for Earth Re-entry

Paper number

IAC-09.D2.4.10

Author

Mr. Matthias Tausche, OHB-System AG, Germany

Coauthor

Dr. Rolf Janovsky, OHB-System AG, Germany

Coauthor

Mr. Jeffrey Apeldoorn, OHB-System AG, Germany

Coauthor

Mr. Marc Scheper, OHB-System AG, Germany

Coauthor

Prof. Rodolfo Monti, University of Naples "Federico II", Italy

Coauthor

Prof. Raffaele Savino, University of Naples "Federico II", Italy

Coauthor

Mr. Rafael Molina, European Space Agency (ESA), The Netherlands

Coauthor

Mr. Emanuele Di Sotto, Portugal

Coauthor

Dr. D. Paterna, University of Naples "Federico II", Italy

Coauthor

Dr. Mario De Stefano Fumo, University of Naples "Federico II", Italy

Year

2009

Abstract

The current European and international interest in human exploration missions leads to particular focus on the return to Earth with superorbital re-entry speeds. Currently used re-entry vehicles, like capsules and the Space Shuttle, reduce their initial kinetic and potential energy during atmospheric re-entry by exploiting mainly the drag forces. Advanced re-entry vehicles with a high lift-over-drag ratio are able to perform long duration re-entry trajectories with large downrange and crossrange with good manoeuvrability by a proper utilization of lift forces. A long-duration re-entry of that type reduces drastically the g-loads to typically approximately 1 to 2 g, compared to $>$ 8 g for ballistic capsule-type re-entry (LEO). This is especially an advantage for an ill or de-conditioned crew. These requirements lead to a winged vehicle with a low wing loading and a high aerodynamic efficiency.

The PHOEBUS concept shows a re-entry vehicle which achieves all requirements for a high lift flight. Contrary to the conventional vehicles with a maximum hypersonic lift-over-drag ratio in the range of 0.3 (capsule) to 1.2 (Space Shuttle), the PHOEBUS has a maximum hypersonic L/D of about 3. It is designed to carry a crew of three astronauts and is attached to a modular resource module, which can be adapted to different mission scenarios. The structure is designed as a hot structure concept with sharp leading edges at the fuselage and the wings and is made of state-of-the-art materials. An insulated compartment is foreseen for the crew, payload and avionics.

The outstanding flight quality of a high lift-over-drag re-entry vehicle compared to a conservative vehicle admits to fly a low-risk and smooth atmospheric trajectory with a large variety of substantial changes of inclination and expands number of possible re-entry windows and landing sites.

The paper will show an overview of the study results for the spacecraft design, the analysis of the flight mechanics, the aero- and aerothermodynamics as well as the guidance and control techniques performed in the PHOEBUS study to show the feasibility of such a re-entry vehicle. Furthermore, the requirements for the launch and landing sites and their scenarios will be described.

As an outcome it can be summarized, that the characteristics of the PHOEBUS open up a wide range of operational flexibility concerning the re-entry windows and landing sites for exploration missions to meet their requirements including abort cases and/or medical return.

Abstract document

IAC-09.D2.4.10.pdf

Manuscript document

IAC-09.D2.4.10.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.