Encyclopedia Astronautica
Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

Vulcain
SEP, Ottobrunn LOx/LH2 rocket engine. In production. Powered the cryogenic core stage of Ariane 5. First flight 1996. Upgraded versions developed and proposed for later Ariane 5 versions.

Status: In production. Number: 22 . Thrust: 1,075.00 kN (241,669 lbf). Unfuelled mass: 1,300 kg (2,800 lb). Specific impulse: 431 s. Specific impulse sea level: 326 s. Burn time: 605 s. Height: 3.00 m (9.80 ft). Diameter: 2.00 m (6.50 ft).

The Vulcain rocket engine powered the cryogenic core stage of Ariane 5. The Ottobrunn facility was responsible for the development and manufacture of the Vulcain thrust chamber comprising the regeneratively cooled combustion chamber, coaxial propellant mixing injectors, dump cooled nozzle extension, and gimbal joint. The LOX and LH2 propellant valves were also manufactured and produced at the Ottobrunn Production Centre.

The thrust chamber design was based on the regenerative cooling concept that was developed at Ottobrunn, since continually refined. Before combustion, LH2 was pumped into a distribution manifold and then flowed through closely arranged small tubular cooling channels within the combustion chamber wall. The LH2 then entered an injector head where it was uniformly distributed to 516 coaxial injector elements.

The coaxial injector elements caused the LOX and LH2 propellants to be mixed together. LOX was injected at the center of the injector, around which the LH2 was injected. These propellants were mainly atomized and mixed by shear forces generated by the velocity differences between LOX and LH2. Although the injector design was complex, it assured consistent and reliable combustion efficiencies greater than 99 %, which were reached in the remaining process in the combustion chamber.

At the combustion chamber, the mixed propellants were burned and accelerated up to sonic conditions. The combustion temperatures in the chamber almost reached 3250 degrees Celsius at pressures greater than 100 bar.

Combustion temperature control was achieved by the flow of LH2 in the cooling channels within the combustion chamber wall. This thin copper alloy wall, just 1.5 mm thick separated the combustion temperatures from the - 239 to - 120 degree Celsius LH2 cooling flow.

The final acceleration of hot gases, up to supersonic velocities, was achieved by gas expansion in the nozzle extension, thereby increasing the thrust.

Thrust (sl): 773.200 kN (173,822 lbf). Thrust (sl): 78,844 kgf. Engine: 625 kg (1,377 lb). Chamber Pressure: 102.00 bar. Area Ratio: 45. Thrust to Weight Ratio: 84.318. Oxidizer to Fuel Ratio: 6.2. Coefficient of Thrust vacuum: 1.86973284462013. Coefficient of Thrust sea level: 1.4411614160487.

Subtopics

Vulcain 2 SEP, Ottobrunn LOx/LH2 rocket engine. In development. New generator cycle rocket engine for an Ariane 5 core stage upgrade. Thrust increased more than 30% from Vulcain 1. First flight 2002.

Country: France. Launch Vehicles: Ariane 5. Propellants: Lox/LH2. Stages: Ariane 5-1 H155. Agency: Ottobrunn. More at: 7573. Bibliography: 225.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2016 Mark Wade - Contact
© / Conditions for Use