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Most interplanetary probes use MMH / NTO or hydrazine. Small / medium launcher upper stages like FREGAT and AVUM (VEGA) use also UDMH / NTO combinations. It is proposed to study their replacement by green propellants either storable (nitrous oxide / hydrocarbons) or semi cryogenic (LOX / hydrocarbons). The storable solutions are interesting for V < 2 000 m/s while semi cryogenic or cryogenic solutions are more attractive for higher V. Mission's examples toward Moon, Mars and Jupiter are proposed as well as a small upper stage for a micro satellite launcher. Some very simple ground demonstrators are proposed to validate the selected combinations.