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Ariane 5's cryogenic H173 main stage (H158 for Ariane 5G, G+, and GS) was called the EPC (Étage Principal Cryotechnique — Cryotechnic Main Stage). It consisted of a 5.4 m (18 ft) diameter by 30.5 m (100 ft) high tank with two compartments, one for liquid oxygen and one for liquid hydrogen , and a Vulcain 2 engine at the base with a vacuum ...
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]
Aestus was developed by the Ottobrunn Space Propulsion Centre between 1988 and 1995 with first flight as an upper stage of Ariane 5 G flight 502 and performed as designed. [ 1 ] [ 4 ] The first improvements were developed between 1999 and 2002 improving the frame performance and adjusting propellant mixture ratio from 2.05 to 1.90 with a first ...
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.
The ATV propellant used for re-boost (monomethylhydrazine fuel and N 2 O 4 oxidizer) is of a different type from the payload refueling propellant (UDMH fuel and N 2 O 4 oxidizer). The system bus section of the ATV had solar panels (3,800 W), 40 Ah of batteries, propellant tanks, four R-4D (490 N) thrusters, and 28 attitude control and braking ...
Vinci is a restartable, cryogenic, liquid-propellant rocket engine that powers the upper stage of Ariane 6.While development began in 1998 for the planned Ariane 5ME upgrade, funding for that programme shifted in 2014 to prioritize the development of Ariane 6, making Vinci the engine for the new launcher.
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]
Hybrid-propellant rockets use a combination of solid and liquid propellant, typically involving a liquid oxidizer being pumped through a hollow cylinder of solid fuel. All current spacecraft use conventional chemical rockets (solid-fuel or liquid bipropellant) for launch, though some [note 3] have used air-breathing engines on their first stage ...