| Atlas V |
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The Atlas V launch vehicle system was a completely new design that succeeded the earlier Atlas series. Atlas V vehicles were based on the 3.8-m (12.5-ft) diameter Common Core Booster (CCB) powered by a single Russian RD-180 engine. These could be clustered together, and complemented by a Centaur upper stage, and up to five solid rocket boosters, to achieve a wide range of performance. When combined with a standard Atlas payload fairing, the configuration was designated as the Atlas V 400 series. The Atlas V 500 series combined the CCB with a larger 5 m diameter payload fairing derived from that used on the Ariane 5 vehicle The Atlas V 500 series could also tailor performance by incorporating from zero to five solid rocket boosters (SRB). Both Atlas V 400 and 500 configurations incorporated a stretched version of the Centaur upper stage (CIII), which could be configured as a single-engine Centaur (SEC) or a dual engine Centaur (DEC). The Atlas V family of launch vehicles could be launched from either Cape Canaveral Air Station Launch Complex 41 or Vandenberg Air Force Base Space Launch Complex 3W. A three-digit naming convention was developed for the Atlas V launch vehicle system to identify it’s multiple configuration possibilities, as follows: the first digit identified the diameter class (in meters) of the payload fairing (4 or 5 m); the second digit indicated the number of solid rocket motors used (zero for Atlas V 400 and zero to five for Atlas V 500); the third digit represented the number of Centaur engines (one or two). Payload performance of the possible variants were as follows (payloads over 9,050 kg would require structural modification to the basic vehicle):
Manufacturer: Lockheed Martin. Launches: 18. Success Rate: 100.00%. First Launch Date: 2000-05-24. Last Launch Date: 2007-12-10. Launch data is: continuing. LEO Payload: 12,500 kg (27,500 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 5,000 kg (11,000 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: AS 2100, Eurostar 2000, Spacebus 3000. Liftoff Thrust: 8,590.000 kN (1,931,100 lbf). Total Mass: 546,700 kg (1,205,200 lb). Core Diameter: 3.81 m (12.49 ft). Total Length: 58.30 m (191.20 ft). Span: 5.40 m (17.70 ft). Launch Price $: 138.000 million. in: 2004 price dollars. The originally estimated launch price in 1998 for the Atlas V 401 model was $77 million, the 500 series $ 110 million, and the HLV model $ 170 million. Due to the collapse of the commercial launch market, this was revised by the USAF in November 2004 to $ 138, $192, and $ 254 million respectively.
Version: Atlas IIIA.
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. Launches: 2. First Launch Date: 2000-05-24. Last Launch Date: 2004-03-13. 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.
Atlas IIIB. Status: Out of production. Alternate Designation: Atlas IIRC; Atlas IIARC. This was the first version of the Atlas to fly using Russian RD-180 engines; and the last version to fly using the original balloon-tank concept for the first stage. It differed from the Atlas IIIA in use of a stretched, two-engine upper stage, and had a brief three-year operational career in 2002-2005 before being superseded by the Atlas V. The single-stage Atlas IIIB booster was the same as that used for the Atlas IIIA. The Lockheed-Martin manufactured Centaur upper stage was powered by two Pratt & Whitney RL10A-4-2 turbopump-fed engines burning liquid oxygen and liquid hydrogen. The changes to Centaur for the Atlas IIIB included a stretched tank (1.68 m) and the addition of the second engine. Guidance, tank pressurization, and propellant usage controls for both Atlas and Centaur phases were provided by the inertial navigation unit (INU) located on the forward equipment module. In a typical Atlas IIIB 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 five minutes, after which the Centaur and its payload coasted in a parking orbit. During the first burn, approximately eight seconds after ignition, the payload fairing was jettisoned. The second Centaur ignition occurred 27 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. LEO Payload: 10,718 kg (23,629 lb). Payload: 4,500 kg (9,900 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: HS 601, LM 700. Liftoff Thrust: 2,600.000 kN (584,500 lbf). Total Mass: 218,588 kg (481,904 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 52.80 m (173.20 ft). Launch Price $: 105.000 million. in: 2000 price dollars.
Atlas 3B SEC. Status: Retired 2005.
Launches: 3. First Launch Date: 2003-04-12. Last Launch Date: 2005-02-03.
Atlas 3B DEC. Status: Retired 2002.
Launches: 1. First Launch Date: 2002-02-21. Last Launch Date: 2002-02-21.
Atlas V 401.
Launches: 6. First Launch Date: 2002-08-21. Last Launch Date: 2007-12-10. LEO Payload: 4,950 kg (10,910 lb). Total Mass: 334,500 kg (737,400 lb). Core Diameter: 3.80 m (12.40 ft). Total Length: 58.30 m (191.20 ft).
Atlas V 411. Status: Active.
Launches: 1. First Launch Date: 2006-04-20. Last Launch Date: 2006-04-20. LEO Payload: 4,950 kg (10,910 lb). Total Mass: 334,500 kg (737,400 lb). Core Diameter: 3.80 m (12.40 ft). Total Length: 58.30 m (191.20 ft).
Atlas V 421. Status: Active.
Launches: 1. First Launch Date: 2007-10-11. Last Launch Date: 2007-10-11.
Version: Atlas V 431.
Launches: 1. First Launch Date: 2005-03-11. Last Launch Date: 2005-03-11. Total Mass: 334,500 kg (737,400 lb). Core Diameter: 3.80 m (12.40 ft). Total Length: 59.10 m (193.80 ft).
Atlas V 521. Status: Active.
Launches: 2. First Launch Date: 2003-07-17. Last Launch Date: 2004-12-17. LEO Payload: 6,000 kg (13,200 lb). Liftoff Thrust: 14,000.000 kN (3,147,000 lbf). Total Mass: 433,000 kg (954,000 lb). Core Diameter: 3.80 m (12.40 ft). Total Length: 59.70 m (195.80 ft).
Atlas V 551. Status: Active.
Launches: 1. First Launch Date: 2006-01-19. Last Launch Date: 2006-01-19.
Version: Atlas V Heavy.
Heavy-lift version of the Atlas V launch vehicle system with three parallel 3.8-m-diameter Common Core Boosters (CCB), and a stretched version of the Centaur upper stage (CIII), which could be configured as a single-engine Centaur (SEC) or a dual engine Centaur (DEC), and a 5 m diameter payload fairing. As of 2004 no work had been authorised to build Atlas V Heavy facilities at either Cape Canaveral or Vandenberg AFB.
Payload: 8,600 kg (18,900 lb). to a: earth escape trajectory. Liftoff Thrust: 11,470.000 kN (2,578,550 lbf). Total Mass: 945,000 kg (2,083,000 lb). Core Diameter: 3.81 m (12.49 ft). Total Length: 60.00 m (196.00 ft). Span: 11.50 m (37.70 ft).
Version: Atlas V Growth Phase 1. Status: Design 2003. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 3.8-m-diameter Common Core Boosters (CCB), a 5-m-diameter wide body version of the Centaur upper stage with a single-engine, and a 5 m diameter payload fairing. Another variant would use a stretched wide body version of the Centaur upper stage with 2 or 4 motors, allowing payloads of up to 13,500 kg to be lofted to earth escape velocity.
Payload: 12,000 kg (26,000 lb). to a: earth escape trajectory. Liftoff Thrust: 11,470.000 kN (2,578,550 lbf). Total Mass: 960,000 kg (2,110,000 lb). Core Diameter: 3.81 m (12.49 ft). Total Length: 60.00 m (196.00 ft). Span: 11.50 m (37.70 ft).
Version: Atlas V Growth Phase 2. Status: Design 2003. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 5-m-diameter new Lox/LH2 stage with 2 or 4 engines with a total thrust of 180,000 kgf; and a 5 m diameter payload fairing.
Payload: 29,000 kg (63,000 lb). to a: earth escape trajectory. Liftoff Thrust: 22,940.000 kN (5,157,110 lbf). Total Mass: 1,800,000 kg (3,900,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 63.00 m (206.00 ft). Span: 15.00 m (49.00 ft).
Version: Atlas V Growth Phase 3. Status: Design 2003. Proposed Saturn-V class variant of the heavy-lift version of the Atlas V launch vehicle with five parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 7-m-diameter new Lox/LH2 stage; and a 7 m diameter payload fairing.
Payload: 44,000 kg (97,000 lb). to a: earth escape trajectory. Liftoff Thrust: 35,300.000 kN (7,935,700 lbf). Total Mass: 2,900,000 kg (6,300,000 lb). Core Diameter: 5.00 m (16.40 ft). Total Length: 63.00 m (206.00 ft). Span: 15.00 m (49.00 ft).
Version: Andrews ETOS.
Proposed Earth-to-Orbit Segment booster for Andrews CEV architecture. Consisted of an Atlas V core, two Zenit-2 booster strap-ons, and a new-development Lox/LH2 upper stage. The new expendable Lox/LH2 upper stage would require development of a new RL-X engine. The stage would be 6.5 m in diameter and 17.6 m long, with a gross mass of 283,793 kg and a dry mass of 14,402 kg. All stages would be only partially fuelled for delivery of a low-earth orbit payload of 40 tonnes, with a gross lift-off mass of 865,950 kg in that configuration. Manufacturer: Andrews. LEO Payload: 40,000 kg (88,000 lb). to: 300 km Orbit. at: 28.00 degrees. Payload: 22,000 kg (48,000 lb). to a: trans-lunar injection trajectory. Other Associated Spacecraft: Andrews CEV. Total Mass: 1,213,618 kg (2,675,569 lb). Core Diameter: 5.40 m (17.70 ft). Total Length: 84.70 m (277.80 ft). Span: 17.00 m (55.00 ft). Launch Price $: 240.000 million. in: 2005 price dollars. Atlas V Chronology 2000 May 24 - 23:10 GMT - Cape Canaveral LC36B. LV Model: Atlas IIIA . Atlas 3A AC-201 Eutelsat W4 Mass: 3,190 kg (7,030 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. 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. 2002 February 21 - 12:43 GMT - Cape Canaveral LC36B. LV Model: Atlas 3B DEC . Atlas 3B-DEC AC-204 Echostar 7 Mass: 690 kg (1,520 lb). Spacecraft: LM 700. Agency: Echostar. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Direct Broasdcasting satellite. The first launch of the Atlas 3B, with the Common Centaur stretched two-engine upper stage. Launch delayed from December 19, 2001 and January 22. The Echostar 7 communications satellite was placed into geostationary transfer orbit. The first burn of the Centaur put the stack into a 185 x 193 km x 28.1 deg parking orbit. At 1305 UTC the Centaur burned again to achieve the final 245 x 57060 km x 22.6 deg transfer orbit and separated from Echostar. As of 2007 Mar 11 located at 118.92W drifting at 0.006W degrees per day. 2002 August 21 - 22:05 GMT - Cape Canaveral LC41. Atlas V 401 AV-001 Hot Bird 6 Mass: 3,905 kg (8,609 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,757 km (22,218 mi). Apogee: 35,814 km (22,253 mi). Inclination: 0.00 deg. Period: 1,436.10 min. This was the maiden flight of the Atlas 5 EELV. Launch delayed from May 9, July 8 and 29, August 6 and 12 due to both payload and booster delays. Hot Bird 6 was a European (EUTELSAT) geostationary communications spacecraft. The 4.9-ton Hot Bird 6 (a Spacebus 3000B3) was to provide digital radio and television coverage to Europe, North Africa, and the Middle East through its 28 Ku-band and four Ka-band transponders after being parked over 13° E longitude. As of 2007 Mar 4 located at 12.95E drifting at 0.012E degrees per day. 2002 December 13 - USAF to subsidise EELV's The US Air Force asked the Congress to provide $1 billion of subsidies in 2004-2009 for the Atlas V and Delta 4 EELV launch vehicles. The collapse of the commercial satellite market invalidated the cost model on which the manufacturers invested their own funds in development. Lack of adequate sales could have meant the closure of the production line of one or both of the launch vehicles on which the US government would rely for future space missions. The US Air Force asked for a $200-million first tranche n FY2004. 2003 April 12 - 00:47 GMT - Cape Canaveral LC36B. LV Model: Atlas 3B SEC . Atlas 3B-SEC AC-205 AsiaSat 4 Mass: 4,042 kg (8,911 lb). Spacecraft: HS 601. Agency: AsiaSat. Perigee: 35,772 km (22,227 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Delayed from May 28, 2002, and January 13, February 5, and April 11, 2003. AsiaSat 4 was designed to provide broadcast, telecommunications and broadband multimedia services to the Asia Pacific region, and direct-to-home broadcast servic-es to Hong Kong, from its orbital position of 122 deg É East longitude.The satellite generated up to 9,600 watts using two sun-tracking four-panel solar wings covered with triple-junction gallium arsenide solar cells. AsiaSat 4 was to operate in C-band and Ku-band. The satellite carried 28 active transponders with six spares in C-band, powered by 55-watt traveling-wave tube amplifiers (TWTAs), and 20 active transponders with four spares in Ku-band, powered by 140-watt TWTAs. The C-band payload was designed to offer pan-Asian coverage, similar to AsiaSat 3S, also a 601HP model. The Ku-band payload provided high power, and spot beams for selected areas in either the Fixed Satellite Service frequency band or in the Broadcast Satellite Service frequency band. As of 2007 Mar 10 located at 122.23E drifting at 0.011W degrees per day. 2003 May 13 - Cape Canaveral LC41. Atlas V 401 AV-002 Hellas Sat 2 Mass: 3,440 kg (7,580 lb). Spacecraft: Eurostar 2000. Agency: Hellas Sat Consortium. Perigee: 35,775 km (22,229 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Launch delayed from January 30, March 11 and 14, May 10 and 12, 2003. Spacecraft former Intelsat KTV, NSS-KTV, NSS-6, Intelsat APR-3. As of 2007 Mar 8 located at 38.95E drifting at 0.006E degrees per day. 2003 July 17 - 23:45 GMT - Cape Canaveral LC41. Atlas V 521 AV-003 Rainbow 1 (Cablevision 1) Mass: 4,328 kg (9,541 lb). Spacecraft: AS 2100. Agency: Cablevision. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Delayed from May 8 As of 2007 Mar 10 located at 61.68W drifting at 0.011W degrees per day. 2003 December 18 - 02:30 GMT - Cape Canaveral LC36B. LV Model: Atlas 3B SEC . Atlas 3B-SEC AC-203 USA 174 Spacecraft: HS 601. Agency: USN. Perigee: 35,781 km (22,233 mi). Apogee: 35,798 km (22,243 mi). Inclination: 4.20 deg. Period: 1,436.20 min. The last UHF Follow-On communications satellite for the US Navy. The satellite provided fleet communications from geostationary orbit. 2004 March 13 - 05:40 GMT - Cape Canaveral LC36B. LV Model: Atlas IIIA . Atlas 3A AC-202 MBSAT Mass: 4,143 kg (9,133 lb). Spacecraft: FS-1300. Agency: Mobile Broadcasting Corp. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. 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. 2004 December 17 - 12:07 GMT - Cape Canaveral LC41. Atlas V 521 AV-005 AMC-16 (GE-16) Mass: 4,200 kg (9,200 lb). Spacecraft: AS 2100. Agency: SES Americom. Perigee: 35,781 km (22,233 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,436.10 min. AMC-16, like AMC-15, was a hybrid Ku/Ka-band satellite built by Lockheed Martin and based on the A2100 spacecraft platform. The spacecraft was to become operational in early 2005 from 85º West with a 15 year design life. The satellite carried 24 x 36 MHz/140 W Ku-band transponders and 12 x 125MHz/75 W spot beams. Coverage included the continental United States, Alaska, and Hawaii. Launch was delayed from December 6 and 16. As of 2007 Mar 9 located at 118.75W drifting at 0.002W degrees per day. 2005 February 3 - 07:41 GMT - Cape Canaveral LC36B. LV Model: Atlas 3B SEC . Atlas 3B-SEC AC-206 USA 181 Spacecraft: NOSS-3. Perigee: 1,011 km (628 mi). Apogee: 1,209 km (751 mi). Inclination: 63.40 deg. Last launch of an Atlas model using the original, innovative, balloon propellant tanks conceived in 1947. Third launch of new generation paired satellites used for tracking, characterisation, and intelligence on naval vessels and civilian shipping worldwide. 2005 March 11 - 21:42 GMT - Cape Canaveral LC41. Atlas V 431 AV-004 Inmarsat 4-F1 Mass: 5,959 kg (13,137 lb). Spacecraft: Eurostar 3000. Agency: Inmarsat. Perigee: 35,562 km (22,097 mi). Apogee: 36,011 km (22,376 mi). Inclination: 3.00 deg. Period: 1,436.10 min. Heaviest single payload to geosynchronous transfer orbit to that date. Delayed from October 2004, February 27, March 10, 2005. The satellite was to provide L-band mobile communications and wideband data transmission for Inmarsat's global network. As of 2007 Mar 11 located at 63.82E drifting at 0.000E degrees per day. 2005 August 12 - 11:43 GMT - Cape Canaveral LC41. Atlas V 401 AV-007 Mars Reconnaissance Orbiter Mass: 2,180 kg (4,800 lb). Spacecraft: Mars Reconnaissance Orbiter. Agency: NASA/JPL. Transferred from Atlas 3B. Delayed from August 10 and 11, 2005. 2006 January 19 - 19:00 GMT - Cape Canaveral LC41. Atlas V 551 AV-010 / Star-48 New Horizons Mass: 478 kg (1,053 lb). Spacecraft: New Horizons. Agency: NASA/JPL. Last robotic mission to an unexplored planet in our solar system. New Horizons was due to receive a gravity boost from Jupiter in February 2007, then fly by Pluto in 2015. During launch toward Jupiter it reached a higher velocity than any manmade object, and was the first to be boosted directly to solar escape velocity. The trajectory had a perihelion of 0.98 AU, an inclination of 0.87 deg and an eccentricity of 1.03. After the Jupiter encounter it was to have a perihelion of 2.2 AU, an inclination of 2.3 deg and an eccentricity of 1.40. At encounter with Pluto on July 14, 2015, the spacecraft would be 1.1 AU above the ecliptic plane and 32.9 AU from the Sun, leaving the solar system toward the star Xi Sgr. 2006 April 20 - 20:27 GMT - Cape Canaveral LC41. Atlas V 411 AV-008 Astra 1KR Mass: 4,332 kg (9,550 lb). Spacecraft: AS 2100. Agency: SES Astra. Perigee: 35,631 km (22,140 mi). Apogee: 35,696 km (22,180 mi). Inclination: 0.10 deg. Period: 1,429.80 min. The first Centaur upper stage burn placed the stack into a 167 km x 22442 km x 24.8 deg transfer orbit. After a second burn the Centaur released the satellite into a 6470 km x 36240 km x 23.8 deg orbit, from which it would use its own engine to achieve final geosynchronous orbit. As of 2007 Mar 10 located at 19.18E drifting at 0.022W degrees per day. 2007 March 9 - 03:10 GMT - Cape Canaveral LC41. Atlas V 401 AV-013 STPSat-1 Mass: 170 kg (370 lb). Agency: USAFRL. Perigee: 558 km (346 mi). Apogee: 560 km (340 mi). Inclination: 35.40 deg. Period: 95.80 min. STPSat carried experiments to study the Earth's atmosphere, ionosphere and radiation environment. It also released the two MEPSI picosatellites. 2007 June 15 - 15:11 GMT - Cape Canaveral LC41. Atlas V 401 AV-009 USA 194 Spacecraft: NOSS-3. Agency: NRO. Perigee: 776 km (482 mi). Apogee: 1,246 km (774 mi). Inclination: 63.00 deg. Classified National Reconnaissance Office mission. There appeared to be problem in the second burn of the Centaur upper stage. Amateur observors believed that two satellites were to be have been deployed in 1150 km altitude, 63 deg inclination, but that only a 776 km x 1246 km was achieved. However it was believed that the payloads could reach the final intended orbits using on-board propulsion 2007 October 11 - 00:22 GMT - Cape Canaveral LC41. Atlas V 421 AV-011 USA 195 Spacecraft: HS 702. Perigee: 32,586 km (20,247 mi). Apogee: 39,016 km (24,243 mi). Inclination: 0.20 deg. Period: 1,436.80 min. First USAF Wideband Global Satcom satellite, designed to replace the DSCS series, was placed by the Atlas booster in an initial 477 km x 66,847 km x 20.1 deg geosynchronous transfer orbit. The satellite carried X-band and Ka-band communications payloads. 2007 December 10 - 22:05 GMT - Cape Canaveral LC41. Atlas V 401 AV-015 USA 198 Spacecraft: SDS-3. Perigee: 515 km (320 mi). Apogee: 39,705 km (24,671 mi). Inclination: 62.60 deg. Classified National Reconnaisance Office payload; probable primary payload data relay communications. May also have carried SBIRS HEO-2 infrared missile warning sensor and a TWINS-B magnetospheric research experiment. Initial orbit 261 x 16776 km x 60.0 deg. 2008 March 13 - 10:02 GMT - Vandenberg . Atlas V 411 AV-006 USA 200 Spacecraft: Jumpseat-2. Perigee: 1,112 km (690 mi). Apogee: 35,780 km (22,230 mi). Inclination: 63.60 deg. Classified National Reconnaisance Office satellite placed in a Molniya orbit; orbital parameters are estimated. Believed to be the second in a new series carrying combined signals intelligence and early warning payloads. Probable sensors included the SBIRS HEO-2 infrared missile early warning package and the NASA/Los Alamos TWINS-B magnetospheric research payload. 2008 April 14 - 20:12 GMT - Cape Canaveral . Atlas V 421 AV-014 ICO G1 Mass: 6,600 kg (14,500 lb). Spacecraft: FS-1300. Perigee: 35,774 km (22,228 mi). Apogee: 35,800 km (22,200 mi). Inclination: 6.00 deg. Period: 1,436.10 min. The satellite was to provide mobile communications services for ICO Global Communications, a successor company to Teledesic. Bibliography:
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