Atlas Centaur 69 Credit - Lockheed Martin Media Gallery

The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus. The first flight of an Atlas I was on July 25, 1990. Originally, 18 Atlas I vehicles were planned for manufacture. With the award by the USAF to General Dynamics of the MLV-II vehicle development contract for the Atlas II launch vehicle, the Atlas program rescoped Atlas I production commitments to 11 vehicles and converted the remaining commitments to the Atlas II/IIA/IIAS production effort.

Manufacturer: Convair. Launches: 11. Failures: 3. Success Rate: 72.73%. First Launch Date: 1990-07-25. Last Launch Date: 1997-04-25. Launch data is: complete. LEO Payload: 3,630 kg (8,000 lb). to: 185 km Orbit. Payload: 2,255 kg (4,971 lb). to a: Geosynchronous transfer trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: AS 3000, CRRES, GOES-Next, HS 376, HS 601, SAX. Liftoff Thrust: 1,939.300 kN (435,972 lbf). Total Mass: 164,300 kg (362,200 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 43.90 m (144.00 ft). Development Cost $: 400.000 million. in: 1987 average dollars. Launch Price $: 75.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 70.300 million. in: 1985 unit dollars. Cost comments: 1989, 61 sets of motors cost $ 650 mn.

• Stage Number: 0. 1 x Stage: Atlas MA-5. Gross Mass: 3,646 kg (8,038 lb). Empty Mass: 3,646 kg (8,038 lb). Thrust (vac): 1,896.010 kN (426,240 lbf). Isp: 294 sec. Burn time: 174 sec. Isp(sl): 259 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: LR-89-7. Status: Out of production.

• Stage Number: 1. 1 x Stage: Atlas G/H/I. Gross Mass: 142,536 kg (314,238 lb). Empty Mass: 4,236 kg (9,338 lb). Thrust (vac): 386.300 kN (86,844 lbf). Isp: 316 sec. Burn time: 266 sec. Isp(sl): 220 sec. Diameter: 3.05 m (10.00 ft). Span: 4.90 m (16.00 ft). Length: 22.20 m (72.80 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: LR-105-7. Status: Out of production.

• Stage Number: 2. 1 x Stage: Centaur I. Gross Mass: 15,600 kg (34,300 lb). Empty Mass: 1,700 kg (3,700 lb). Thrust (vac): 146.800 kN (33,002 lbf). Isp: 444 sec. Burn time: 402 sec. Isp(sl): 0 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.15 m (30.01 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3A. Status: Out of production.

1990 July 25 - 19:21 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36. Launch Pad: LC36B. Launch Vehicle: Atlas I. Model: Atlas I. LV Configuration: Atlas I AC-69 / Centaur I 5049.

• CRRES Nation: USA. Payload: CRRES (P 86-1). Mass: 1,629 kg (3,591 lb). Class: Earth. Type: Magnetosphere. Spacecraft: CRRES. Agency: USAF/NAS. Perigee: 335 km (208 mi). Apogee: 34,739 km (21,585 mi). Inclination: 18.00 deg. Period: 613.40 min. COSPAR: 1990-065A. USAF Sat Cat: 20712. Combined Release and Radiation Effects Satellite. First launch of commercial Atlas-Centaur. Spacecraft engaged in research and exploration of the upper atmosphere or outer space. Elliptical orbit; MRS trajectory. References: 1, 2, 5, 6, 278.

• Yuri 3H Nation: Japan. Program: BS. Payload: BS-3H. Mass: 600 kg (1,320 lb). Class: Communications. Spacecraft: AS 3000. Agency: TSCJ. Manufacturer: Lockheed Martin. Apogee: 175 km (108 mi). COSPAR: F910418A. Decay Date: 1991-04-18. References: 5, 278.

• Galaxy 5 Nation: USA. Program: Galaxy. Mass: 1,412 kg (3,112 lb). Class: Communications. Spacecraft: HS 376. Agency: HCI. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1992-013A. USAF Sat Cat: 21906. Geostationary at 125 deg W. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 125 deg W in 1992-2001. As of 2007 Mar 8 located at 7.46E drifting at 3.538W degrees per day. References: 1, 2, 5, 6, 278.

• Galaxy 1R Nation: USA. Program: Galaxy. Payload: Galaxy 1R. Class: Communications. Spacecraft: HS 376. Agency: Hughes Communications Inc. COSPAR: F920822A. Decay Date: 1992-08-22. References: 5, 278.

• UHF F1 Nation: USA. Program: UHF. Payload: UHF F/O F1. Mass: 2,866 kg (6,318 lb). Class: Communications. Spacecraft: HS 601. Agency: HCI. Perigee: 36,053 km (22,402 mi). Apogee: 36,098 km (22,430 mi). Inclination: 21.10 deg. Period: 1,450.90 min. COSPAR: 1993-015A. USAF Sat Cat: 22563. Completed Operations Date: 1993-07-01. US Navy communications; Ultra High Frequency Follow On; unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into subsynchronous earth orbit with MRS trajectory option. As of 28 August 2001 located at 45.55 deg W drifting at 3.676 deg W per day. As of 2007 Mar 10 located at 95.89E drifting at 3.687W degrees per day.References: 1, 2, 5, 6, 278.

• USA 95 Nation: USA. Program: UHF. Payload: UHF F/O F2. Mass: 2,844 kg (6,269 lb). Class: Communications. Spacecraft: HS 601. Agency: HCI. Perigee: 35,767 km (22,224 mi). Apogee: 35,805 km (22,248 mi). Inclination: 5.00 deg. Period: 1,436.10 min. COSPAR: 1993-056A. USAF Sat Cat: 22787. US Navy communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 72 deg E in 1993-1999.References: 1, 2, 5, 6, 278.

• GOES 8 Nation: USA. Payload: GOES I. Mass: 2,105 kg (4,640 lb). Class: Earth. Type: Weather. Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,770 km (22,220 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.10 deg. Period: 1,436.20 min. COSPAR: 1994-022A. USAF Sat Cat: 23051. Geostationary Environmental Satellite. Stationed at 75 deg W. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1994-1995; 75 deg W in 1995-1999 As of 5 September 2001 located at 74.78 deg W drifting at 0.019 deg E per day. NASA announced that GOES-8 was "de-orbited" (presumably moved to a sub-synchronous orbit) on May 5, 2004 after 10 years of service. As of 2007 Mar 11 located at 87.46E drifting at 4.935W degrees per day.References: 1, 2, 5, 6, 278.

• USA 104 Nation: USA. Program: UHF. Payload: UHF F/O F3. Mass: 2,847 kg (6,276 lb). Class: Communications. Spacecraft: HS 601. Agency: HCI. Perigee: 35,776 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 4.81 deg. Period: 1,436.05 min. COSPAR: 1994-035A. USAF Sat Cat: 23132. US Navy communications . Stationed at 14.38 deg W 1995-1999. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. References: 2, 5, 6, 278.

• GOES 9 Nation: USA. Payload: GOES J. Mass: 2,105 kg (4,640 lb). Class: Earth. Type: Weather. Spacecraft: GOES-Next. Agency: NOAA. Perigee: 35,809 km (22,250 mi). Apogee: 35,911 km (22,314 mi). Inclination: 0.20 deg. Period: 1,435.90 min. COSPAR: 1995-025A. USAF Sat Cat: 23581. Stationed at 135 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 90 deg W in 1995; 135 deg W in 1996-1998; 98-105 deg W in 1998-1999 As of 5 September 2001 located at 103.62 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 159.81E drifting at 0.002W degrees per day.References: 2, 5, 6, 278.

• Beppo SAX Nation: Italy. Payload: BeppoSAX. Class: Astronomy. Spacecraft: SAX. Agency: ASI. Perigee: 584 km (362 mi). Apogee: 601 km (373 mi). Inclination: 4.00 deg. Period: 96.50 min. COSPAR: 1996-027A. USAF Sat Cat: 23857. Decay Date: 2003-04-29. LEO. Satellite per Astronomia a raggi X; X-ray celestial observatory Launch vehicle put payload into low earth orbit with IFR trajectory option. 100th Atlas-Centaur flight. References: 4, 6, 278.

• GOES 10 Nation: USA. Payload: GOES K. Class: Earth. Type: Weather. Spacecraft: GOES-Next. Agency: NOAA. Manufacturer: Space Systems/Loral, Palo Alto. Perigee: 35,780 km (22,230 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.40 deg. Period: 1,436.30 min. COSPAR: 1997-019A. USAF Sat Cat: 24786. Geosynchronous. Stationed over 105.7W Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 105 deg W in 1997-1998; 135 deg W in 1998-1999 As of 6 September 2001 located at 135.09 deg W drifting at 0.037 deg W per day. As of 2007 Mar 11 located at 59.64W drifting at 0.009W degrees per day.References: 4, 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...