Space Launch System

Résumé

Le Space Launch System ( « système de lancement spatial »), abrégé SLS, est un lanceur spatial super-lourd américain développé par la NASA depuis 2011 et dont le premier vol a lieu le . Le SLS joue un rôle central dans le programme Artemis dont l'objectif est, après le programme Apollo, d'envoyer de nouveau des équipages à la surface de la Lune, puis de préparer les futures missions habitées vers Mars. Cette fusée sera chargée de placer le vaisseau Orion transportant l'équipage sur une trajectoire à destination de la Lune. Pour placer en orbite lunaire un vaisseau avec équipage d'une masse de près de , il faut disposer d'un lanceur beaucoup plus puissant que ceux actuellement disponibles. Le lanceur Saturn V du programme Apollo, d'une capacité de en orbite lunaire, n'est plus produit depuis la fin de ce programme au début des années 1970. L'architecture du lanceur SLS, similaire à celle de l'Ares V abandonné après l'arrêt du programme Constellation en 2010, reprend en les adaptant

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https://fr.wikipedia.org/wiki/Space_Launch_System

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This work is dedicated to research on the Selective Laser Sintering (SLS) process. The problem has been intensively investigated by many research groups. A number of physical phenomena observed in SLS are studied. There is, however, no comprehensive understanding of the true process nature and no solid theory of the SLS process has been established up to date. In this thesis, a theoretical model of the process has been developed. This model considers the laser-matter interaction, the non-linear heat diffusion and the phase transformations. The evolution of the material properties due to the sintering phenomena is analyzed by a microscopic sub-model. For solving the governing equations a numerical method based on finite element analysis has been proposed. A combination of non-conformal adaptive mesh for space discretization with a Chernoff's scheme for time discretization has been used. The results of the numerical simulations have been compared to the experimental results. The temperature field evolution predicted by the model is validated by experimental measurements performed with an infra-red camera.

EPFL2005

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Enhanced operation of the Eu Ec test facility

Stefano Alberti, Jérémie Dubray, Damien Fasel, Timothy Goodman, Jean-Philippe Hogge, Albert Perez, Ugo Siravo

A Test Facility (TF) has been designed and installed at SPC to allow for the commissioning of the EU gyrotrons developed in view of their integration to the ITER EC system. The first phase of operation of this TF was dedicated to the development of the EU 2 MW coaxial cavity gyrotron [1,2]. The EU gyrotron development for ITER has been reoriented since then and is presently advancing a 170 GHz/1MW/CW gyrotron developed within the EGYC consortium and manufactured by THALES. At the same time, the TF has been enhanced to host the FALCON project [3], consisting in the integration of a second 170 GHz/1MW/CW gyrotron delivered by GYCOM. This new experiment is aiming to test the main RF components of the EC Transmission Line (TL) and of the Upper Launcher system to be installed on ITER. This paper describes the technical modifications brought to the existing TF to comply with the requirements of both 1 MW gyrotrons operation. Effort has been put in switching of the auxiliaries from one tower to the other within a short time ( < 1 week) while maintaining operator safety and equipment protection. A detailed description of the additional implementation and of the strategy followed to share the main auxiliaries (like the HVPS, the cooling system, the control system, etc.) will be presented. Moreover, most of the new equipment, such as the control hardware, have been designed to fulfil ITER site standards. Finally, the preliminary operation results with this reconfigured TF will be presented.

ELSEVIER SCIENCE SA2019

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Four EC H&CD (Electron Cyclotron Heating and Current Drive) launchers will be installed into the upper ports #12, #13, #15 and #16 in ITER. Beside plasma heating their main purpose is to counteract plasma instabilities by injecting up to 20 MW of microwave power at a frequency of 170 GHz at dedicated positions into the plasma. The microwave power is generated in 24 Gyrotrons outside the Tokamak and transmitted into the dedicated ports by 8 waveguide lines per launcher. After passing a CVD (Chemical Vapor Deposition) diamond window and another section of circular waveguides, the microwaves are quasi-optically guided into the plasma by an adjusted set of mirrors. These mirrors and also the foremost segments of the waveguides are mounted into the Upper Port Plug, which is a massive steel structure capable to dissipate up to 800 kW heat and to withstand heavy mechanical loads induced mainly from plasma disruptions. This paper presents the most recent status of the design of the EC H&CD Upper Port Plug (UPP), featuring the construction of the supporting structure and the BSM (Blanket Shield Module) with its plasma facing First Wall, the PHTS (Primary Heat Transfer System) water cooling layout, the shielding components engineering, the microwave system integration and comprehensive manufacturing strategies. Also correlated computational analyses to prove the final design of the launchers structural system are given.

ELSEVIER SCIENCE SA2018

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