Atlas 2 Media Gallery

The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. The original Atlas II model was developed to support the United States Air Force Medium Launch Vehicle II program. Its Centaur used RL10A-3-3A engines operating at an increased mixture ratio. The first Atlas II flew on 7 December 1991, successfully delivering AC-102/Eutelsat II F3 to orbit.

Manufacturer: Convair. Launches: 10. Success Rate: 100.00%. First Launch Date: 1991-12-07. Last Launch Date: 1998-03-16. Launch data is: complete. LEO Payload: 6,580 kg (14,500 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 2,810 kg (6,190 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: DSCS III, HS 601, Spacebus 100. Liftoff Thrust: 2,110.600 kN (474,482 lbf). Total Mass: 187,600 kg (413,500 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 47.50 m (155.80 ft). Launch Price $: 85.000 million. in: 1994 price dollars.

• Stage Number: 0. 1 x Stage: Atlas MA-5A. Gross Mass: 4,187 kg (9,230 lb). Empty Mass: 4,187 kg (9,230 lb). Thrust (vac): 2,093.700 kN (470,682 lbf). Isp: 299 sec. Burn time: 172 sec. Isp(sl): 263 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: RS-56-OBA. Status: Out of production.

• Stage Number: 1. 1 x Stage: Atlas II. Gross Mass: 161,995 kg (357,137 lb). Empty Mass: 6,095 kg (13,437 lb). Thrust (vac): 386.300 kN (86,844 lbf). Isp: 316 sec. Burn time: 283 sec. Isp(sl): 220 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 24.90 m (81.60 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-56-OSA. Status: Out of production.

• Stage Number: 2. 1 x Stage: Centaur II. Gross Mass: 18,833 kg (41,519 lb). Empty Mass: 2,053 kg (4,526 lb). Thrust (vac): 146.800 kN (33,002 lbf). Isp: 444 sec. Burn time: 488 sec. Isp(sl): 0 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 10.10 m (33.10 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3A. Status: Out of production.

• Stage Number: 3. 1 x Stage: IABS. Gross Mass: 1,578 kg (3,478 lb). Empty Mass: 275 kg (606 lb). Thrust (vac): 980 N (220 lbf). Isp: 312 sec. Burn time: 60 sec. Isp(sl): 0 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 0.68 m (2.23 ft). Propellants: N2O4/MMH. No Engines: 2. Engine: R-4D. Other designations: Integrated Apogee Boost Subsystem. Status: Out of production.

1991 December 7 - 22:47 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36. Launch Pad: LC36B. Launch Vehicle: Atlas II. Model: Atlas II. LV Configuration: Atlas II AC-102 / Centaur II 8102.

• Eutelsat II F3 Nation: Europe. Program: Eutelsat. Mass: 1,874 kg (4,131 lb). Class: Communications. Spacecraft: Spacebus 100. Agency: Eutelsat. Perigee: 35,769 km (22,225 mi). Apogee: 35,802 km (22,246 mi). Inclination: 2.00 deg. Period: 1,436.10 min. COSPAR: 1991-083A. USAF Sat Cat: 21803. Stationed at 16 deg E. Telecommunications satellite. French registration 1991-8. Transfer orbit was 663 min, 200 x 36000 km x 7.0 deg. Registered by France in ST/SG/SER.E/249 until EUTELSAT can register the satellite. EUTELSAT is the European Telecommunications Satellite Organi zation. Launch vehicle put payload into supersynchronous earth orbit with IFR trajectory option. Positioned in geosynchronous orbit at 16 deg E in 1992-1998; 36 deg E in 1999. As of 1 September 2001 located at 21.51 deg E drifting at 0.017 deg E per day. As of 2007 Mar 11 located at 74.40E drifting at 3.531W degrees per day.References: 1, 2, 5, 6, 278.

• USA 78 Nation: USA. Program: DSCS. Payload: DSCS III B-14. Class: Communications. Type: Military. Spacecraft: DSCS III. Agency: USAF. Perigee: 30,675 km (19,060 mi). Apogee: 35,503 km (22,060 mi). Inclination: 0.90 deg. Period: 1,300.50 min. COSPAR: 1992-006A. USAF Sat Cat: 21873. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit; at 135 deg W in 1995. References: 1, 2, 5, 6, 278.

• USA 82 Nation: USA. Program: DSCS. Payload: DSCS III B-12. Class: Communications. Type: Military. Spacecraft: DSCS III. Agency: USAF. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.20 deg. Period: 1,436.20 min. COSPAR: 1992-037A. USAF Sat Cat: 22009. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 12 deg W in 1995-1996. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).References: 1, 2, 5, 6, 278.

• USA 93 Nation: USA. Program: DSCS. Payload: DSCS III B-9. Mass: 2,615 kg (5,765 lb). Class: Communications. Type: Military. Spacecraft: DSCS III. Agency: USAF. Perigee: 183 km (113 mi). Apogee: 35,764 km (22,222 mi). Inclination: 26.10 deg. Period: 625.80 min. COSPAR: 1993-046A. USAF Sat Cat: 22719. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 175 deg E in 1995-1997.References: 1, 2, 5, 6, 278.

• USA 97 Nation: USA. Program: DSCS. Payload: DSCS III B-10. Mass: 2,615 kg (5,765 lb). Class: Communications. Type: Military. Spacecraft: DSCS III. Agency: USAF. Perigee: 195 km (121 mi). Apogee: 35,501 km (22,059 mi). Inclination: 26.40 deg. Period: 625.40 min. COSPAR: 1993-074A. USAF Sat Cat: 22915. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 52 deg W in 1995; 60 deg E in 1997. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).References: 1, 2, 5, 6, 278.

• USA 108 Nation: USA. Program: UHF. Payload: UHF F/O F4. Mass: 3,023 kg (6,664 lb). Class: Communications. Spacecraft: HS 601. Agency: HCI. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 2.20 deg. Period: 1,436.10 min. COSPAR: 1995-003A. USAF Sat Cat: 23467. UHF Follow-On #4; US Navy communications . Stationed at 177.0 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 177 deg W in 1995-1999. References: 2, 5, 6, 278.

• USA 111 Nation: USA. Program: UHF. Payload: UHF F/O F5-EHF. Mass: 3,015 kg (6,646 lb). Class: Communications. Spacecraft: HS 601. Agency: USN. Perigee: 35,774 km (22,228 mi). Apogee: 35,796 km (22,242 mi). Inclination: 4.80 deg. Period: 1,436.10 min. COSPAR: 1995-027A. USAF Sat Cat: 23589. UHF Follow-On #5; US Navy communications . Stationed at 72.3 deg E. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1995-1999. References: 2, 5, 6, 278.

• General Dynamics Space Division bought by Martin Nation: USA. References: 4460.

• Lockheed Aircraft Corporation merged with Martin to form Lockheed Martin Nation: USA. Atlas assembly line moved from Kearney Mesa, California, to Littleton, Colorado References: 4460.

• Final Atlas produced in California. Nation: USA. Ceremony commemorating final Atlas (AC-126) produced at Kearny Mesa plant References: 4460.

• USA 114 Nation: USA. Program: UHF. Payload: UHF F/O F6-EHF. Mass: 3,015 kg (6,646 lb). Class: Communications. Spacecraft: HS 601. Agency: USN. Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 5.00 deg. Period: 1,436.10 min. COSPAR: 1995-057A. USAF Sat Cat: 23696. UHF Follow-On #6; US Navy communications. Stationed at 105.3 deg W. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1995-1999. References: 2, 5, 6, 278.

• USA 127 Nation: USA. Program: UHF. Payload: UHF F/O F7-EHF. Mass: 3,015 kg (6,646 lb). Class: Communications. Spacecraft: HS 601. Agency: HCI. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 4.90 deg. Period: 1,436.20 min. COSPAR: 1996-042A. USAF Sat Cat: 23967. Positioned in geosynchronous orbit at 170 deg W in 1996; 23 deg W in 1996-1999; 100 deg W in 1999. As of 29 July 1999) 99.21 deg W drifting at 0.011 deg W per day. As of 2007 Feb 22 located at 21.85W drifting at 0.014W degrees per day. References: 4, 6, 278.

• USA 138 Nation: USA. Program: UHF. Payload: UHF F/O F8-EHF. Class: Communications. Spacecraft: HS 601. Agency: USN. Manufacturer: Hughes Space and Communications, El Segundo. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 3.30 deg. Period: 1,436.10 min. COSPAR: 1998-016A. USAF Sat Cat: 25258. UHF Follow-On F8 was the first Block III UHF Follow-On satellite, replacing the old FLTSATCOM satellites. It carried UHF, EHF and Ka-band transponders, including a video broadcast payload. This was the last Atlas II launch; future Atlas launches would use the Atlas IIA, IIAS and III models. Positioned in geosynchronous orbit at 172 deg E in 1998-1999.References: , 278.

• 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.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al. ISBN: 0710618107. The most comprehensive source of information for current space projects. Too expensive for human beings and most libraries. More at amazon.com...

• Lockheed Martin Coporation, Atlas Family Fact Sheets, September 1998.. Accessed at: http://www.lmco.com/ILS/txtmain/ils_lsysinfo.htm.

• Walker, Chuck, with Powell, Joel, Atlas - The Ultimate Weapon, Apogee Books, Canada, 2005. ISBN: 1894959183. Another excellent Apogee Book, the only in-depth account of the design, development, and production of the rocket that was America's first ICBM, pioneered US spaceflight, and continued to take payloads into orbit into the next millenium. More at amazon.com...