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How did the Atlas II rocket work?
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Atlas IIIA. Atlas V. Atlas is a family of US missiles and space launch vehicles that originated with the SM-65 Atlas. The Atlas intercontinental ballistic missile (ICBM) program was initiated in the late 1950s under the Convair Division of General Dynamics. [2] Atlas was a liquid propellant rocket burning RP-1 kerosene fuel with liquid oxygen ...
- December 17, 1957; 65 years ago
- 1957–2010s (decade)
Apr 6, 2020 · Used in: Space Shuttle booster stages. Liquid Propellants: These are the most commonly used propellants today. The common subtypes are: – a. Liquid oxygen (LOX) and highly refined kerosene (RP-1). Used for the first stages of the Saturn V, Atlas V, and Falcon 9. The equation for the corresponding chemical reaction will be as follows –
Jan 1, 2021 · The two booster engines shared a turbopump and gas generator. The verniers received propellants from the sustainer. This configuration was used on Atlas B and C test missiles. MA-2, produced from 1958 through 1962, consisted of two XLR89-5 booster engines, an LR105-5 sustainer, and two LR101 vernier engines. The two booster engines each had its ...
Atlas II provided higher performance than the earlier Atlas I by using engines with greater thrust and longer propellant tanks for both stages. The increased thrust, engine efficiency, and propellant capacity enabled the vehicle to lift payloads of 6,100 pounds (2,767 kg) into geostationary transfer orbit (GTO), or more on later Atlas II variants.
- II: December 7, 1991, IIA: June 10, 1992, IIAS: December 16, 1993
- 63, (II: 10, IIA: 23, IIAS: 30)
- 3.5
May 25, 2020 · Convair engineers developed a “balloon” which was its fuel tank, always kept under pressure with either propellant or nitrogen gas to provide the needed rigidity. At launch three engines would fire using RP-1 and LOX as fuel.
The vernier engines, a trademark of Atlas vehicles, were designed to control the roll of the missile and trim its final flight velocity. The booster and vernier engines were all fed by liquid oxygen/RP-1 (kerosene) liquid propellant, and all engines were ignited at liftoff.
May 7, 2024 · The Thor missile force was withdrawn in 1963. Propelled by liquid oxygen and kerosene, the basic rocket was 65 feet (19.8 m) in length, with a body diameter of 8 feet (2.4 m), weight at firing of 110,000 pounds (49,900 kg), and speed at burnout of 7,670 to 11,505 miles (12,300 to 18,500 km) per hour.
