Atlas C Credit - US Air Force

Last development version of Atlas. Never deployed operationally or used for space launches.

Historical Essay © Andreas Parsch

The XSM-65C Atlas C, flown between December 1958 and August 1959, tested the thin-skinned fuel tanks and the radio-command guidance in production configuration.

Manufacturer: Convair. Launches: 6. Failures: 3. Success Rate: 50.00%. First Launch Date: 1958-12-24. Last Launch Date: 1959-08-24. Launch data is: complete. LEO Payload: 70 kg (154 lb). to: 185 km Orbit. at: 32.00 degrees. Apogee: 900 km (550 mi). Liftoff Thrust: 1,587.200 kN (356,817 lbf). Total Mass: 110,740 kg (244,130 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 25.15 m (82.51 ft). Span: 4.88 m (16.01 ft). Maximum range: 8,000 km (4,900 mi). Number Standard Warheads: 1. Standard RV: Mk. 2/3. Standard warhead: W49. Standard warhead yield: 1,440 KT. Standard warhead CEP: 3.23 km (2.00 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Development Cost $: 2,230.000 million. in: 1965 average dollars. Recurring Price $: 8.309 million. Total Number Built: 381. Total Development Built: 18. Total Production Built: 343. Flyaway Unit Cost $: 1.800 million. in: 1965 unit dollars. Cost comments: Development cost and flyaway cost total for Atlas A through F (ICBM's).

• Stage Number: 0. 1 x Stage: Atlas MA-2. Gross Mass: 3,050 kg (6,720 lb). Empty Mass: 3,050 kg (6,720 lb). Thrust (vac): 1,517.422 kN (341,130 lbf). Isp: 282 sec. Burn time: 135 sec. Isp(sl): 248 sec. Diameter: 4.90 m (16.00 ft). Span: 4.90 m (16.00 ft). Length: 0.00 m ( ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: XLR-89-5.

• Stage Number: 1. 1 x Stage: Atlas B. Gross Mass: 107,610 kg (237,230 lb). Empty Mass: 3,980 kg (8,770 lb). Thrust (vac): 363.218 kN (81,655 lbf). Isp: 309 sec. Burn time: 240 sec. Isp(sl): 215 sec. Diameter: 3.05 m (10.00 ft). Span: 4.90 m (16.00 ft). Length: 21.90 m (71.80 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: XLR-105-5. Status: Out of production.

1958 January - Launch Vehicle: Atlas C.

• Scheduled design complete (95%) for Atlas C-series missiles Nation: USA. References: 4460.

• Research and development launch Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). First Atlas C flight (3C), successful. References: 1811.

• Mod II re-entry vehicle research and development mission Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). References: 1811.

• Research and development launch Nation: USA. Agency: USAF. Apogee: 100 km (60 mi). References: 1811.

• Atlas 6C blows up. Nation: USA. Missile 6C blows up, destroying ERB Stand 1-A. References: 4460.

• RVX-2 re-entry vehicle research and development mission Nation: USA. Agency: USAF. Apogee: 200 km (120 mi). References: 1811.

• Research and development launch Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). A full-scale USAF Atlas ICBM nose cone recovered for the first time after flight down the AMR. References: 17, 278, 1811.

• Research and development launch Nation: USA. Agency: USAF. Apogee: 900 km (550 mi). Last successful Atlas C flight (11C); 9C exploded one month later during the Able static firing. References: 1737.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961. The only such comprehensive handbook ever produced, and at the dawn of the space age.

• Parsch, Andreas, DesignationSystems.Net, . Outstanding, unique reference for aircraft, missiles, propulsion, and avionics systems. Accessed at: http://www.designation-systems.net/.