The Phase B Status and Synthesis of the Pre-X Experimental re-Entry Lifting Body
- Paper number
IAC-07-D2.6.07
- Author
Mr. Patrice Plotard, EADS Astrium, France
- Coauthor
Mr. Jacques Moulin, Science Applications International Corporation (SAIC), France
- Coauthor
Mr. Sylvain Guedron, Centre National d'Etudes Spatiales (CNES), France
- Coauthor
Mr. Paolo Baicco, Centre National d'Etudes Spatiales (CNES), France
- Year
2007
- Abstract
Atmospheric glided re-entry is one of the main key technologies for future space vehicle applications, such as reusable launchers, ISS servicing and exploration as well. In this frame Pre-X project, proposed by CNES and leaded by ASTRIUM ST as Prime Contractor, is part of the first generation of experimental vehicles:
- To improve knowledge and skills in aero-thermo-dynamics phenomena and guidance schemes using several control means such as RCS, flaps and movable masses
- To demonstrate in flight reusable TPS ability
- to secure the second generation of re-entry X vehicles by demonstrating European engineering ability to perform an end to end re-entry project The CNES Pre-X procurement specification states that:
- The vehicle has to be launched by the European Vega launcher. Flight is foressen for year 2010
- Recovery in Pacific Ocean 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.
This paper describes the programme status at System PDR level that has just been hold.and the synthesis of the system activities performed up to now together with the main technical issues. Therefore, the main results of the system activities are shown in this paper.In particular, it is described:
- the aero dynamic/aero thermal data bases obtained by means of computer codes and a complete set of wind tunnel tests,
- the flight qualities, the re-entry trajectories based on monte carlo calculations, the Guidance Navigation and Control characteristics and performances,
- the thermo-mechanical architecture base on the preliminary design and justification of the overall sub-system (structure, TPS pattern, DRS, RCS, FpCS,avionics..),
- the ground segment and operations definitions. In addition,a preliminary in-flight experimentation and measurement plan has been assessed defining the main objectives in terms of testing of Reusable TPS subassemblies, of getting Aero Thermo Dynamics (ATD) data on the most critical phenomena concerning the design and sizing of a re-entry vehicle; of improving the flight measurement system in consistency with pre-flight and post flight analysis to take the opportunity to fly innovative measurement.
A complete system loop has been performed including the operations, ground system assessment, and visibility analysis demonstrating that the mission objectives are fulfilled: the vehicle re-entry point is at 120 km; the ATD phenomena are catched between Mach 25 and 2, the parchutes system opens in supersonic regime at Mach 1.4 and the vehicule.is finally recovered in the sea.
Authors: Patrice Plotard, Astrium, Saint Médard en Jalles, France, patrice.plotard@space.eads.net
Jacques Moulin, Astrium, Saint Médard en Jalles, France, jacques.moulin@space.eads.net
Sylvain Guedron, CNES, Evry, sylvain.guedron@cnes.fr
Paolo Baiocco, CNES, Evry, paolo.baiocco@cnes.fr
- Abstract document
- Manuscript document
IAC-07-D2.6.07.pdf (🔒 authorized access only).
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