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| Reference : Integration of vehicle, propulsion system and separation unit designs for a launcher usi... |
| Scientific congresses and symposiums : Paper published in a book | |||
| Engineering, computing & technology : Aerospace & aeronautics engineering | |||
| http://hdl.handle.net/2268/36743 | |||
| Integration of vehicle, propulsion system and separation unit designs for a launcher using in-flight oxygen collection | |
| English | |
| Bizzarri, Didier [ > > ] | |
| Hendrick, Patrick [ > > ] | |
Heyen, Georges  [Université de Liège - ULg > Département de chimie appliquée > LASSC (Labo d'analyse et synthèse des systèmes chimiques) >] | |
| Ngendakumana, Philippe [Université de Liège - ULg > Département d'aérospatiale et mécanique > Thermotechnique >] | |
| May-2005 | |
| AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference | |
| International | |
| AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference | |
| du 16 mai 2005 au 20 mai 2005 | |
| Capua | |
| Italy | |
| [en] Two-Stage-To-Orbit ; LOX collection ; ACES ; centrifugal distillation ; mass transfer ; liquid-gas contactor ; liquid hydrogen ; space launcher | |
| [en] The use of in-flight Oxygen Collection has shown to significantly improve space launcher performance. The conceptual approach followed by the Royal Military Academy of Brussels (RMA) has tried to widen the available design margins in order to reduce the required technological leap and limit the economical risk associated with such a development.
The aim of the ESA-funded theoretical and experimental study on an air separation device is to demonstrate the possibility of performing efficient air distillation in a compact rotating column. An integration of the vehicle, propulsion system and separation unit designs is presented aiming to optimise the overall vehicle performance while keeping technological difficulty and system complexity at a reasonable level. Reference vehicles are presented in their specific mission profiles with an emphasis on TSTO’s. Different layouts of the internal energy and mass flowsheets are compared, in order to make best use of the refrigeration capacity of the hydrogen fuel running though the propulsion system during the first phase of the flight considering the separator as a classical distillation column. This analysis provides the requirements in terms of heat exchange capacity, compression ratios and number of so-called transfer units needed in the separator. Here, the system is intentionally kept simple, to limit complexity, but the analysis is thorough and accurate, including, for example, the effect of the presence of argon. An analysis of the separation unit to reach those requirements is proposed. That includes internals, practical building with estimates of pressure drop, separation performance and flow limitation. Analysis of size reduction of the distillation unit from usual 1-g column to the high-g unit is provided as well as the scale up methodology of laboratory results. First experimental results obtained with our centrifugally enhanced distillation separation system are presented and perspectives for a larger on-board operational unit proposed. | |
| European Space Agency (ESA) | |
| Researchers ; Professionals | |
| http://hdl.handle.net/2268/36743 |
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