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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN Imprimer: 2150-766X
ISSN En ligne: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.130
pages 90-100

HYBRID PROPULSION FOR SMALL SATELLITES DESIGN LOGIC AND TESTS

V. Maisonneuve
Office National d'Etudes et de Recherches Aérospatiales (ONERA), Centre du Fauga-Mauzac 31410 Mauzac, France
J. C. Godon
Office National d'Etudes et de Recherches Aérospatiales (ONERA), Centre du Fauga-Mauzac 31410 Mauzac, France
Renaud Lecourt
Office National d'Etudes et de Recherches Aérospatiales (ONERA), Centre du Fauga-Mauzac 31410 Mauzac, France
G. Lengelle
Energetics Department, ONERA National Laboratory for Aerospace Research and Development of France
N. Pillet
Centre National d'Etudes Spatiales, Centre de Toulouse (CNES), F - 31401 Toulouse Cedex 4, France

RÉSUMÉ

The objective of the study is to offer an alternative to the propulsion by hydrazine for the positioning and control of micro-satellites or small interplanetary probes, which require high velocity impulse. This paper presents the study of a design and an operation code for polyethylene/H2O2 (87%) hybrid rocket motors. The assumptions used at the moment do not allow for a perfect optimization. The developments which will follow will keep the same logic but with less restrictive hypotheses and more realistic calculations. At the same time, an experimental study has been started with the aim of better understanding the operating range of hybrid rocket motors and the influence of the polyethylene pyrolysis rate in the design. Hybrid rocket motor design and operation have been computed according to the available volume on a micro-satellite.


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