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101	Compact air separation system for space launcher / Compact air separation system demonstrator for space launchers using in-fight oxygen collection Bizzarri, Didier 01 September 2008 (has links) A compact air separator demonstrator based on centrifugally enhanced distillation has been studied. The full size device is meant to be used on board of a Two Stage To Orbit vehicle launcher. The air separation system must be able to extract oxygen in highly concentrated liquid form (LEA, Liquid Enriched Air) from atmospheric air. The LEA is stored before being used in a subsequent rocket propulsion phase by the second stage of the launcher. Two reference vehicles are defined, one with a subsonic first stage and one with a supersonic first stage. In both cases, oxygen collection is performed during a cruise phase (M 0.7 and M 2.5 respectively). The aim of the project is to demonstrate the feasibility of the air separation system, investigate the separation cycle design, and assess that the separator design selected is suitable for the reference vehicles.<p><p>The project is described from original base ideas to design, construction, extended testing and analysis of experimental results. Preliminary computations for a realistic layout have been performed and the motivations for the choices made during the process are explained. Test rig design, separator design and technical discussion are provided for a subscale pilot unit. Mass transport parameters and flooding limits have been estimated and experimentally measured. Performance has been assessed and shown to be sufficient for the reference Two Stage To Orbit vehicles. The technology developed is found suitable without further optimization, although some volume and mass reduction would be desirable for the supersonic first stage concept. There are many ways of optimisation that can be further investigated. The aim of this program, however, is not to fully optimize the device, but to demonstrate that a device based on a simple, robust, low-risk design is already suitable for the launch vehicles. On top of that analysis, directions for improvements are suggested and their potentials estimated. A complete assessment of those improvements requires further maturation of the technological concept through further testing and practical implementations.<p><p>Directions for future work, general conclusions and a vehicle development roadmap have also been provided.<p> / Doctorat en Sciences de l'ingénieur / info:eu-repo/semantics/nonPublished Sciences de l'ingénieur Mécanique Launch vehicles (Astronautics) Mass transfer Two-phase flow Oxygen -- Separation Lanceurs (Astronautique) Transfert de masse Ecoulement diphasique Oxygène -- Séparation mass transfer/tranfert de matière demonstrator/démonstrateur heat transfer/transfert de chaleur prototype two phase flow/écoulement biphasique HTU HETP pressure drop/pertes de charge flooding/noyage centrifugal/centrifuge RDS two stage to orbit/lanceur biétage TSTO air launch/lanceur aéroporté porous material/matériaux poreux distillation experimental study/étude expérimentale system study/étude système liquid air/air liquide liquid oxygen/oxygène liquide

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Compact air separation system for space launcher / Compact air separation system demonstrator for space launchers using in-fight oxygen collection