Atlas II Credit - © Mark Wade Media Gallery

The Atlas IIIA was a development of the Atlas using Russian engines in place of the Rocketdyne MA-5 booster/sustainer group used on all previous models. It was the centerpiece of Lockheed Martin's strategy to remain a leader in the commercial launch services industry. However customers never materialized, and it was used for only two launches in 2002-2004 before being replaced by the Atlas V.

The first stage coupled the unique Atlas balloon tanks and high performance Glushko engines. In a typical Atlas IIIA launch, the vehicle's two RD-180 thrust chambers were ignited shortly before liftoff. Pre-programmed engine thrust settings were used during booster ascent to minimize vehicle loads by throttling back during peak transonic loads in the high dynamic pressure region while otherwise maximizing vehicle performance. Just over two minutes into flight, as the vehicle reached an axial acceleration of 4 g's, the engines began to throttle back, eventually initiating a constant throttle rate to sustain acceleration at 5.5 g's. Booster engine cutoff occurred approximately three minutes into flight and was followed by separation of Centaur from Atlas.

The first Centaur burn lasted about nine minutes after which the Centaur and its payload coasted in a parking orbit. During the first burn, approximately ten seconds after ignition, the payload fairing was jettisoned. The second Centaur ignition occurred about 23 minutes into the flight, continued for about three minutes, and was followed several minutes later by the separation of the spacecraft from Centaur. Major suppliers included: NPO Energomash / Pratt & Whitney - Atlas RD-180 engines; Pratt & Whitney - Centaur engines; Honeywell - Inertial Navigation Unit; BF Goodrich - Digital acquisition system; SAAB - Payload Separation Systems.

Manufacturer: Convair. Launches: 2. Success Rate: 100.00%. First Launch Date: 2000-05-24. Last Launch Date: 2004-03-13. Launch data is: continuing. LEO Payload: 8,640 kg (19,040 lb). Payload: 4,055 kg (8,939 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: FS-1300, Spacebus 3000. Liftoff Thrust: 2,600.000 kN (584,500 lbf). Total Mass: 214,338 kg (472,534 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 52.80 m (173.20 ft). Development Cost $: 300.000 million. in: 1995 average dollars. Launch Price $: 105.000 million. in: 1999 price dollars.

• Stage Number: 1. 1 x Stage: Atlas IIIA. Gross Mass: 195,628 kg (431,285 lb). Empty Mass: 13,725 kg (30,258 lb). Thrust (vac): 4,148.722 kN (932,670 lbf). Isp: 337 sec. Burn time: 132 sec. Isp(sl): 311 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 29.00 m (95.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-180. Status: Out of production. Atlas booster and sustainer engine arrangement replaced by Glushko engines developed for Zenit. Not capable of single stage to single stage to orbit capability (an Internet spaceflight urban myth). The single-stage Atlas IIIA booster uses a high-performance RD-180 propulsion system produced by a U.S./Russian joint venture (RD AMROSS) comprised of Pratt & Whitney (U.S.) and NPO Energomash (Russia). The RD-180 burns liquid oxygen and RP-1 propellant and develops a lift-off (sea-level) thrust of 2.6 MN. The RD-180 throttles to various levels during atmospheric ascent to effectively manage the air-loads experienced by the vehicle enabling minimum Atlas vehicle and launch site infrastructure changes. Additionally, throttling results in satellite experienced flight environments that are nearly identical to Atlas IIAS.

• Stage Number: 2. 1 x Stage: Centaur IIIA. Gross Mass: 18,710 kg (41,240 lb). Empty Mass: 1,905 kg (4,199 lb). Thrust (vac): 99.155 kN (22,291 lbf). Isp: 451 sec. Burn time: 738 sec. Isp(sl): 0 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 10.00 m (32.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RL-10A-4-1. Status: Out of production. Single-engine Centaur for Atlas IIIA. The Lockheed Martin manufactured Centaur IIIA upper stage is powered by one Pratt & Whitney RL10A-4-1 turbopump-fed engine burning liquid oxygen and liquid hydrogen. Using the proven flight design of the Centaur IIAS stage, the only changes to Centaur for IIIA are in the aft region of the stage. For Centaur IIIA, one of Centaur IIAS's two RL10 engines is removed. The remaining engine is re-positioned to a center-mount, and electro-mechanical thrust vector control actuators replace the hydraulically actuated system previously in use. Guidance, tank pressurization, and propellant usage controls for both Atlas and Centaur phases are provided by the inertial navigation unit (INU) located on the forward equipment module. The first Centaur burn lasts about nine minutes after which the Centaur and its payload coast in a parking orbit. During the first burn, approximately ten seconds after ignition, the payload fairing is jettisoned. The second Centaur ignition occurs about 23 minutes into the flight, continues for about three minutes, and is followed several minutes later by the separation of the spacecraft from Centaur.

2000 May 24 - 23:10 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36. Launch Pad: SLC36B. Launch Vehicle: Atlas IIIA. Model: Atlas 3A. LV Configuration: Atlas 3A AC-201.

• Eutelsat W4 Nation: Europe. Program: Eutelsat. Mass: 3,190 kg (7,030 lb). Class: Communications. Spacecraft: Spacebus 3000. Agency: Eutelsat. Manufacturer: Alcatel, Cannes. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. COSPAR: 2000-028A. USAF Sat Cat: 26369. Communications satellite. Maiden flight of Atlas IIIA with Russian RD-180 main engine; scrubbed four times. European Telecommunications Satellite Organization (Eutelsat) satellite equipped with 32 Ku-band transponders, and antennae covering Russia and Africa. It will be stationed at 36 deg E. This was the third of the high power Eutelsat W series to be launched (W1 was destroyed in a ground accident). Stationed at 36 deg E. Positioned in geosynchronous orbit at 32 deg E in 2000. As of 4 September 2001 located at 35.98 deg E drifting at 0.003 deg E per day. As of 2007 Mar 9 located at 36.08E drifting at 0.005E degrees per day.References: 4, 552, 554.

• MBSAT Nation: Japan. Mass: 4,143 kg (9,133 lb). Class: Communications. Spacecraft: FS-1300. Agency: Mobile Broadcasting Corp. Manufacturer: Space Systems/Loral. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2004-007A. USAF Sat Cat: 28184. Mobile S-band digital broadcasting services for home and automobile users in Japan. As of 2007 Mar 9 located at 144.03E drifting at 0.009W degrees per day. References: 552, 554.

• 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.