Thermal Protection Systems Technologies For Re-Entry Vehicles

Abstract

Experimental re-entry demonstrators are currently being developed in Europe, with the objective of increasing the Technology Readiness Level (TRL) of technologies applicable to future reusable launch vehicles. Among these are the Pre-X programme, currently funded by CNES, the French Space Agency, and which is about to enter into development phase B, and the IXV, within the FLPP (Future Launcher Preparatory Programme) funded by ESA. One of the major technologies necessary for such vehicles is the Thermal Protection System (TPS), and in particular the Ceramic Matric Composite (CMC) based windward TPS. In support of this goal, technology maturation named Shingle activities were initiated beginning of 2003 by SPS, under a CNES contract, with the objective of performing a test campaign of a complete shingle of generic design, in preparation of the development of a re-entry experimental vehicle decided in Europe. Pre-development at TPS level have also been performed in preparation of the Pre-X hypersonic reentry demonstrator, and the development phase B is currently ongoing. The main tasks in this programme, based on the work performed in parallel of the Generic Shingle program, is to provide system level support, in order to determine the best suited CMC TPS configuration covering the windward and leading edge areas of the vehicle. This has been done by examining several layouts in ter ms of thickness, shingle size, and patterns. In addition, technological demonstrator have been initiated in the frame of Period 1 of the FLPP Materials and Structures Technological Demonstration Programme. The paper will present a status of these activities, in particular those concerning the design and testing of components of the thermal protection system. Testing includes mechanical, modal characterization, dynamic, acoustic, thermal and thermo-mechanical evaluations. Preparation of planned plasma tests in relevant re-entry environment will also be addressed.