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Abstract: In the framework of the preparation of the next generation of launchers to be developed in Europe, the European Space Agency (ESA) has contracted NGL Prime and its industrial team to conduct a first slice of launch system and stage design activities and programmatic analyses for two types of launchers: [•] A new expendable mid-term launch system relying on elements or “Building Blocks” from Ariane and Vega to be operational by 2015. [•] A new long-term launch system called the Next Generation Launcher (NGL) to be operational by 2020–2025. The design reference missions include a 5 metric tons performance requirement into a Geostationary Transfer Orbit (GTO), to meet the European institutional need, with the increased capability to 8 metric tons into GTO by the addition of solid boosters, to meet the commercial market needs. In a first step, a series of trade-offs were conducted to select the concepts that best fit the requirements of the NGL and “Building Block” launcher options, in terms of propulsion (thrust level, engine characteristics), propellant choice (hydrogen, methane or solid propellants), launcher architecture (with or without strap-on boosters, bi or three stages architecture). In a second step, more detailed analyses were carried out in term of thermo-mechanical design, functional architecture, as well as in term of versatility capacity, i.e. the capability of the launcher to perform different missions than the reference ones. Consistently with this technical activity, a programmatic evaluation was consolidated by the industrial team. This paper details the outcomes of the activity carried out during this second step targeting at selecting one or two concepts. The paper will also give an overview and first results of the follow-on contract in which selected NGL concepts are being further investigated, in the prospect of creating a new European launcher family encompassing versions dedicated to the institutional needs and the commercial market (reference missions), as well as some versions dedicated to more demanding institutional missions (heavy low orbit payload insertions or escape missions) based on a Common Core Booster approach. [Copyright &y& Elsevier]

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 future launcher preparatory programme (FLPP) funded by ESA. One of the major technologies necessary for such vehicles is the thermal protection system (TPS), and in particular the ceramic matrix composites (CMC) based windward TPS. In support of this goal, technology maturation activities named “generic shingle” 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. The activities performed to date include: the design, manufacturing of two C/SiC panels, finite element model (FEM) calculation of the design, testing of technological samples extracted from a dedicated panel, mechanical pressure testing of a panel, and a complete study of the attachment system. Additional testing is currently under preparation on the panel equipped with its insulation, seal, attachment device, and representative portion of cold structure, to further assess its behaviour in environments relevant to its application The paper will present the activities that will have been performed in 2006 on the prediction and preparation of these modal characterization, dynamic, acoustic as well as thermal and thermo-mechanical tests. Results of these tests will be presented and the lessons learned will be discussed. [Copyright &y& Elsevier]

The Hopper, a concept for a reusable launch system was developed and found attractive in the frame of FESTIP, ESA''s Furure European Space Transportation Initiation Programme Later, in the national German ASTRA programme this concept was adapted to newly emerged requirement and subjected to a detailed design loop. Taking off horizontally and staging at high sub-orbital velocity, the Hopper needs a rail-guided launch sled, downrange landing, re-transportation back to the launch site, and one, but only one upper stage. Horizontal take-off is used to improve safety and to reduce thrust requirement, and number, mass, and cost of main engines, and also problems with vehicle centering. Transportang of the cargo (e.g.) payload and expendable upper stage) in the RLV results in only one aerodynamically affected flight configuration. Staging at high sub-orbital velocity above the sensible atmosphere enables the use of only one standardised upper stage for all missions. Using a cryogenic upper stage the Hopper system is nearly optimally staged for the dimensioning GTO mission. The paper describes the consolidated unmaanned RLV concept and highlights areas of special interest, evolution potential, and further steps. [Copyright &y& Elsevier]