Numerical simulation of a green monopropellant for spacecraft application
| Autor: | Levard, Quentin, Louis, Neven, Pelletier, N., Le, Duc Minh, Rouzaud, Olivier, Lempereur, Christine, Hijlkema, Jouke, Lestrade, Jean-Yves, Anthoine, Jerôme |
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| Přispěvatelé: | ONERA / DMPE, Université de Toulouse [Toulouse], ONERA-PRES Université de Toulouse, Centre National d'Études Spatiales [Toulouse] (CNES), André, Cécile |
| Jazyk: | angličtina |
| Rok vydání: | 2018 |
| Předmět: |
SHADOW IMAGING
REGRESSION DE GOUTTE [SPI.FLUID]Engineering Sciences [physics]/Reactive fluid environment MONERGOL VERT LIQUIDE IONIQUE ENERGETIQUE [SPI.FLUID] Engineering Sciences [physics]/Reactive fluid environment GREEN MONOPROPELLANT DROPLET REGRESSION RETROECLAIRAGE [PHYS.PHYS.PHYS-SPACE-PH] Physics [physics]/Physics [physics]/Space Physics [physics.space-ph] ENERGETIC IONIC LIQUID [PHYS.PHYS.PHYS-SPACE-PH]Physics [physics]/Physics [physics]/Space Physics [physics.space-ph] |
| Zdroj: | Space Propulsion 2018 Space Propulsion 2018, May 2018, SEVILLE, Spain |
| Popis: | International audience; Satellite attitude and orbit control manoeuvers are mostly realized by chemical thrusters, using catalytic decomposition of hydrazine. However, hydrazine is known for its carcinogenic and toxic effects and its use is thus threatened by the European chemical regulation REACh. A new monopropellant is therefore under development by CNES (the French Space Agency), and 3 prototypes are still in competition. The final choice of the best formulation will be based on real thruster tests. These new propellants are based on energetic ionic liquids, and the expected flame temperature is about 3000 K. To develop an optimized thruster demonstrator, numerical simulations, combining heat transfer and radiation in complex materials and diphasic behavior are necessary. Energetic ionic liquids have a very complex way of decomposing which explains why it is impossible to use current phase change models implemented in ONERA’s multiphysics code CEDRE. A new macroscopic combustion model is being developed and implemented in CEDRE following the phenomenology of solid homogeneous propellants. Simultaneously an experiment is prepared to observe the combustion of an isolated droplet, in order to measure its regression. This experiment is a proof of concept for the final experimental CNES’s setup GIMLI. This experiment will be validated on ethanol combustion and tested with the new family of green monopropellant. |
| Databáze: | OpenAIRE |
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