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RP-1 kerosene fuel
- Atlas was a liquid propellant rocket burning RP-1 kerosene fuel with liquid oxygen in three engines configured in an unusual "stage-and-a-half" or "parallel staging" design: two outboard booster engines were jettisoned along with supporting structures during ascent, while the center sustainer engine, propellant tanks and other structural elements remained connected through propellant depletion and engine shutdown.
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Atlas was a liquid propellant rocket burning RP-1 kerosene fuel with liquid oxygen in three engines configured in an unusual "stage-and-a-half" or "parallel staging" design: two outboard booster engines were jettisoned along with supporting structures during ascent, while the center sustainer engine, propellant tanks and other structural ...
- December 17, 1957; 65 years ago
- 1957–2010s (decade)
The SM-65D Atlas, or Atlas D, was the first operational version of the Atlas missile and the basis for all Atlas space launchers, debuting in 1959. Atlas D weighed 255,950 lb (116,100 kg) (without payload) and had an empty weight of only 11,894 lb (5,395 kg); the other 95.35% was propellant.
- 6 June 1957
- 24
- 1½
- Intercontinental Ballistic Missile (ICBM)
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 ...
Finally, a highly-refined version of JP-4 known as RP-1 (Rocket Propellant 1) was developed. LOX was retained as the oxidizer. This combination became the basis for a number of rocket engines. Gas Generators - Steam-driven turbopumps, which had been used on the V-2 and Redstone, in addition to having power limitations, were heavy and ...
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.
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 –
5 days ago · 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.
