The Pre-X atmospheric re-entry experimental lifting body: program status and system synthesis

Paper number

IAC-06-D2.P.2.02

Author

Mr. Paolo Baiocco, Centre National d'Etudes Spatiales (CNES), France

Year

2006

Abstract

Atmospheric glided re-entry is one of the main key technologies for future space vehicle applications. In this frame Pre-X is the CNES proposal to perform in-flight experimentation mainly on reusable thermal protections, aero-thermo-dynamics and guidance to secure the second generation of re-entry X vehicles.
This paper describes the programme status and the synthesis of the system activities performed up to now together with the main technical issues. A preliminary in-flight experimentation and measurement plan has been assessed defining the main objectives in terms of 1. Testing of Reusable Thermal Protection System (TPS) subassemblies, being potential candidates for future vehicles in actual flight conditions; 2. Getting Aero Thermo Dynamics (ATD) data on the most critical phenomena concerning the design and sizing of a re-entry vehicle; 3. Improving the flight measurement system in consistency with pre-flight and post flight analysis to take the opportunity to fly innovative measurement.
The current Pre-X procurement specification states that the vehicle recovery without damage of the TPS is mandatory for the mission success. The functional and experimental measurements are transmitted from the vehicle to ground during flight, except for some innovative measurement. The vehicle is recovered in the Pacific Ocean assuring sufficient duration of buoyancy. Flight is foreseen for year 2010. During year 2005 the phase A of the Pre-X program has been achieved with the main objective to verify the compliance of the proposed vehicle solution with the procurement specification. The VEGA and DNEPR launch vehicles have been assumed as main candidates for launching Pre-X.
A complete system loop has been performed including the operations, ground system assessment, and visibility analysis. The vehicle re-entry point is at 120 km and the mission objectives are fulfilled between Mach 25 and 5. Then the vehicle has to pass to subsonic speeds, the parachute opens and it is finally recovered in the sea.
The main results of the system activities are shown in this paper. In particular, the aero dynamic aero thermal data bases obtained by means of computer codes and wind tunnel tests, the re-entry trajectory parameters, the Guidance Navigation and Control characteristics, the flight qualities, the thermo-mechanical architecture, the ground segment and operations definitions.
The results of Pre-X phase A activity will provide an input for the phase B of the European re-entry demonstrator IXV.

Abstract document

IAC-06-D2.P.2.02.pdf

Manuscript document

IAC-06-D2.P.2.02.pdf (🔒 authorized access only).

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