SEP N2O4/UDMH rocket engine. 720 kN. Isp=278s. Used on Ariane 2/3. First flight 1984.
Thrust (sl): 642.300 kN (144,395 lbf). Thrust (sl): 65,496 kgf. Engine: 776 kg (1,710 lb). Chamber Pressure: 59.00 bar. Area Ratio: 11. Thrust to Weight Ratio: 86.3758823529412.
Unfuelled mass: 776 kg (1,710 lb).
More... - Chronology...
Height: 2.87 m (9.41 ft).
Diameter: 0.95 m (3.11 ft).
Thrust: 720.00 kN (161,860 lbf).
Specific impulse: 278 s.
Specific impulse sea level: 248 s.
Burn time: 205 s.
Number: 532 .
Associated Launch Vehicles
Ariane 2/3 French orbital launch vehicle. Improved version of the Ariane 1. It featured increased thrust first and second stage engines, a 25% stretched third stage, 4 seconds specific impulse improvement in the third stage, a larger internal payload fairing volume, and introduced the Sylda payload carrier for dual payloads. The Ariane 3 version added two solid rocket motor strap-ons. Development was authorised in July 1980 and had a total cost of 144 million 1986 Euros. More...
Ariane 4 French orbital launch vehicle. The ultimate Ariane development. Compared with the Ariane 2/3, the Ariane 4 featured stretched first (61%) and third stages, a strengthened structure, new propulsion bay layouts, new avionics, and the Spelda dual-payload carrier. The basic 40 version used no strap-on motors, while the Ariane 42L, 44L, 42P, 44P, and 44LP versions used varous combinations of solid and liquid propellant strap-on motors). Development was authorised in January 1982, with the objective of increasing payload by 90%. Total development cost 476 million 1986 ECU's. More...
Ariane 44LP French orbital launch vehicle. Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons. More...
Ariane 44L French orbital launch vehicle. Ariane 4 with 4 liquid rocket strap-ons. More...
Ariane 42P French orbital launch vehicle. Ariane 4 with 2 solid rocket strap-ons. More...
Ariane 44P French orbital launch vehicle. Ariane 4 with 4 solid rocket strap-ons. More...
Ariane 42L French orbital launch vehicle. Ariane 4 with 2 liquid rocket strap-ons. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Ariane 4-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 245,900/17,900 kg. Thrust 3,034.10 kN. Vacuum specific impulse 278 seconds. More...
Ariane 2-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 160,030/13,750 kg. Thrust 2,880.00 kN. Vacuum specific impulse 281 seconds. More...
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