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Atlas A stage
LOx/Kerosene propellant rocket stage. .

AKA: Atlas A. Status: Out of production. Thrust: 1,517.41 kN (341,128 lbf). Gross mass: 81,647 kg (180,000 lb). Unfuelled mass: 7,230 kg (15,930 lb). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 133 s. Height: 23.17 m (76.01 ft). Diameter: 3.05 m (10.00 ft). Span: 4.90 m (16.00 ft).

Cost $ : 11.000 million. No Engines: 2.



Subtopics

Atlas Able stage LOx/Kerosene propellant rocket stage. .

Atlas Centaur LV-3C stage LOx/Kerosene propellant rocket stage.

Atlas E/F LOx/Kerosene propellant rocket stage. .

Atlas IIIA LOx/Kerosene propellant rocket stage. The American Atlas booster and sustainer engine arrangement was replaced by derivatives of Glushko engines developed for the Ukrainian Zenit launch vehicle. Not capable of single stage to single stage to orbit capability (an Internet spaceflight urban myth).

Atlas Agena SLV-3 LOx/Kerosene propellant rocket stage. .

Atlas Agena LV-3A LOx/Kerosene propellant rocket stage. .

Atlas Agena SLV-3A LOx/Kerosene propellant rocket stage. .

Atlas IIA stage LOx/Kerosene propellant rocket stage. .

Atlas B stage LOx/Kerosene propellant rocket stage. .

Atlas Centaur SLV-3C/D LOx/Kerosene propellant rocket stage.

Atlas D stage LOx/Kerosene propellant rocket stage. .

Atlas G/H/I LOx/Kerosene propellant rocket stage. .

Atlas II stage LOx/Kerosene propellant rocket stage. .

Atlas IIAS stage LOx/Kerosene propellant rocket stage. .

Country: USA. Engines: XLR89-1. Launch Vehicles: Atlas A. Propellants: Lox/Kerosene.

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