SM-65D Atlas
First operational version of the U.S. Atlas missile / From Wikipedia, the free encyclopedia
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The SM-65D Atlas, or Atlas D, was the first operational version of the U.S. Atlas missile. Atlas D was first used as an intercontinental ballistic missile (ICBM) to deliver a nuclear weapon payload on a suborbital trajectory. It was later developed as a launch vehicle to carry a payload to low Earth orbit on its own, and later to geosynchronous orbit, to the Moon, Venus, or Mars with the Agena or Centaur upper stage.
This rocket article contains payload capacity, but does not include orbital altitude or inclination, which greatly affects the capacity. |
Function | ICBM Expendable launch system |
---|---|
Manufacturer | Convair |
Country of origin | United States |
Size | |
Height | 25.15 metres (82.51 ft) |
Diameter | 3.0 metres (10.0 ft) |
Mass | 119,000 kilograms (262,000 lb) |
Stages | 1½ |
Capacity | |
Payload to LEO | |
Mass | 1,400 kg (3,100 lb)[1] |
Launch history | |
Status | Retired |
Launch sites | LC-11, 12, 13 & 14, CCAFS LC-576, VAFB |
Total launches | 135 |
Success(es) | 103 |
Failure(s) | 32 |
First flight | 14 April 1959 |
Last flight | 7 November 1967 |
Boosters | |
No. boosters | 1 |
Powered by | 2 Rocketdyne XLR-89-5 |
Maximum thrust | 1,517.4 kilonewtons (341,130 lbf) |
Burn time | 135 seconds |
Propellant | RP-1/LOX |
First stage | |
Diameter | 3.0 metres (10.0 ft) |
Powered by | 1 Rocketdyne XLR-105-5 |
Maximum thrust | 363.22 kilonewtons (81,655 lbf) |
Burn time | 5 minutes |
Propellant | RP-1/LOX |
Atlas D was launched from Cape Canaveral Air Force Station, at Launch Complexes 11, 12, 13 and 14, and Vandenberg Air Force Base at Launch Complex 576.
The fully operational D-series Atlas was similar to the R&D model Atlas B and C, but incorporated a number of design changes implemented as a result of lessons learned during test flights. In addition, the D-series had the full-up Rocketdyne MA-2 propulsion system with 360,000 pounds-force (1,600 kN) of thrust versus the 250,000 pounds-force (1,100 kN) of thrust in the Atlas B/C's engines. Operational Atlas D missiles retained radio ground guidance aside from a few R&D launches which tested the inertial guidance system designed for the Atlas E/F, and the Atlas D would be the basis for most space launcher variants of Atlas.