FIELD: jet propulsion systems.
SUBSTANCE: invention relates to pressurising propellant reservoirs of a rocket engine. Device comprises primary heater (58) able to heat the propellant coming from reservoir (16) before its reintroduction into that reservoir. Primary heater (58) uses the combustion heat of the engine and the device additionally comprises secondary heater (66) of which the heat source is independent of the operation of the engine, the secondary heater being arranged downstream of primary heater (58) to heat the propellant between its exit from the primary heater and its reintroduction into the reservoir. Device also comprises means (62) for pressurising the propellant between the supply of primary heater (58) and the return of the propellant to the reservoir.
EFFECT: invention provides an increase in the propellant pressure both at the jet thrust generation stage and the ballistic movement stage.
7 cl, 1 dwg
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