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The original Ariane — Ariane 5G — used the EPS (Étage à Propergols Stockables — Storable Propellant Stage), which was fueled by monomethylhydrazine (MMH) and nitrogen tetroxide, containing 10,000 kg (22,000 lb) of storable propellant. The EPS was subsequently improved for use on the Ariane 5G+, GS, and ES.
Aestus is a hypergolic liquid rocket engine used on an upper stage of Ariane 5 family rockets for the orbital insertion. It features unique design of 132 coaxial injection elements causing swirl mixing of the MMH propellants with nitrogen tetroxide oxidizer. The pressure-fed engine allows for multiple re-ignitions.
Ariane is a series of European civilian expendable launch vehicles for space launch use. The name comes from the French spelling of the mythological character Ariadne . France first proposed the Ariane project and it was officially agreed upon at the end of 1973 after discussions between France, Germany and the UK.
In 2022, development began on the P120C+ variant, which evolved into the P160C. This extended version adds 1 metre (3 ft 3 in) to the motor's length and an additional 14,000 kilograms (31,000 lb) of propellant. [2] This upgrade translates to a roughly 2,000-kilogram (4,400 lb) improvement in lift performance on the Ariane 64 with four boosters. [3]
Vulcain is a family of European first stage rocket engines for Ariane 5 and Ariane 6. Its development began in 1988 and the first flight was completed in 1996. The updated version of the engine, Vulcain 2, was first successfully flown in 2005. Both members of the family use liquid oxygen/liquid hydrogen cryogenic fuel.
Ariane flight VA256 was an Ariane 5 rocket flight that launched the James Webb Space Telescope (JWST) into space on 25 December 2021. [3] It was 2021's final Ariane flight, its most valuable payload to date, and the 256th Ariane mission. The launch was described by NASA as "flawless" and "perfect". [4]
These cryogenic temperatures vary depending on the propellant, with liquid oxygen existing below −183 °C (−297.4 °F; 90.1 K) and liquid hydrogen below −253 °C (−423.4 °F; 20.1 K). Since one or more of the propellants is in the liquid phase, all cryogenic rocket engines are by definition liquid-propellant rocket engines. [2]
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio