Arianegroup Sas

Airbus Safran Launchers Sas

Gérard Roz

Didier Vuillamy

Alain Pyre

Emmanuel Edeline

David Hayoun

Nicolas Ravier

François Lassoudiere

Jean-Luc Barthoulot

Lauren Nguyen Duc

Stéphanie Dreyer

Antoine Caratge

Cryogenic propellant tank () for a spacecraft engine, comprising an external enclosure () defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V) and a secondary volume (V) connected to the primary volume (V) via a valve () configured to selectively allow a passage of fluid from the primary volume (V) to the secondary volume (V), or to isolate the secondary volume (V) from the primary volume (V), the primary volume (V) having a primary orifice () adapted to be connected to a first pressurization source (), the secondary volume (V) having a supply orifice () adapted to be connected to a supply line of a spacecraft engine (), and a secondary orifice () adapted to be connected to a second pressurization source ().

Tank for a spacecraft engine

A rocket engine benefiting from better behavior during its starting stage, the rocket engine () including a diverging section () and a lashing system () configured to hold the diverging section () while starting the rocket engine (), the lashing system () comprising: a plurality of radial cables () connected at respective first ends to a plurality of points of the diverging section (), and a peripheral cable () connected to the second ends of the radial cables () and configured to co-operate with attachment points () of a launch platform ().

Rocket engine including a lashing device

The device comprises two heat exchangers () suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (). The heat exchangers co-operate respectively with first and second gas generators () suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator () being suitable for being fed at least in part by the exhaust from the first gas generator ().

Device for pressurizing propellant tanks of a rocket engine

The device comprises a primary heater () suitable for heating the propellant coming from the tank () prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine () and the device further comprises a secondary heater () having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater () in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means () between the feed to the primary heater () and the return of the propellant to the tank for putting the propellant under pressure.

Device for pressurizing a propellant tank of a rocket engine

The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit () for feeding a rocket engine () at least with a first liquid propellant, the feed circuit including at least one first heat exchanger () suitable for being connected to a cooling circuit () for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.

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Pressagny l'Orgueilleux, France

Gérard Roz