SM-65D Atlas

This rocket article contains payload capacity, but does not include orbital altitude or inclination, which greatly affects the capacity. Please help improve this article by adding the orbital altitude and inclination for the given payload. (Learn how and when to remove this message)

Atlas D (SM-65D)

564th Strategic Missile Squadron Convair SM-65D Atlas missile 58-220, pad 564-A2, Warren I site, F. E. Warren AFB, Wyoming
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
Engines	2 Rocketdyne XLR-89-5
Thrust	1,517.4 kilonewtons (341,130 lbf)
Burn time	135 seconds
Propellant	RP-1/LOX
First stage
Engines	1 Rocketdyne XLR-105-5
Thrust	363.22 kilonewtons (81,655 lbf)
Burn time	5 minutes
Propellant	RP-1/LOX
[edit on Wikidata]

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.

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.