SEP N2O4/UDMH rocket engine. 805 kN. Isp=296s. Used on Ariane 4. First flight 1984.
Thrust (sl): 571.100 kN (128,388 lbf). Thrust (sl): 58,237 kgf. Engine: 850 kg (1,870 lb). Chamber Pressure: 58.50 bar. Area Ratio: 30.8. Thrust to Weight Ratio: 99.3791224512388. Oxidizer to Fuel Ratio: 1.7. Coefficient of Thrust vacuum: 1.84359746305747. Coefficient of Thrust sea level: 1.31710173656174.
Unfuelled mass: 850 kg (1,870 lb).
More... - Chronology...
Height: 3.51 m (11.51 ft).
Diameter: 2.60 m (8.50 ft).
Thrust: 805.00 kN (180,971 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 210 s.
Burn time: 125 s.
Number: 133 .
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...
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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 2-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 37,130/3,625 kg. Thrust 805.00 kN. Vacuum specific impulse 296 seconds. More...
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