AKA: Lockheed Martin;Lockheed Martin Astronautics;Lockheed Martin Missiles & Space;Lockheed Missiles and Space Company (now LMMS). Location: Sunnyvale, CA.
Country: USA. Engines: SR13, SR75. Spacecraft: Lockheed Project 7969, KH-1, NF-104, TIROS, KH-2, KH-5, Early Spring, KH-3, KH-4, EMPIRE Lockheed, KH-6, KH-7, KH-4A, Astrocommuter, Lockheed 1963 Space Tug, Lockheed Space Taxi, Lockheed 1963 Space Station, Lockheed RTTOCV, Apollo Experiments Pallet, KH-8, Lockheed EEOED, KH-4B, KH-9, KH-11, Seasat, HST, Improved Crystal, Milstar, Polar, Athena Mars Flyby, LM 700, Lunar Prospector, TRACE, Ikonos, LMI, IMAGE, Gravity Probe-B, CEV Lockheed, Orion. Launch Vehicles: X-17 QTV, X-17 HTV, X-17, X-17 HTV 1, Argo, Polaris A1, Polaris, Polaris TV, Polaris AX, Polaris A2, Polaris A3, Polaris A3 A3T, Recoverable Booster Systems for Orbital Logistics, Reusable Orbital Carrier, Polaris A2E, Terrier Hydac, Starclipper, AACB Class 3, Starclipper Light, Poseidon C3, Shuttle LS A, D-21, Shuttle LS200, Trident, Trident C-4, HOE, Polaris A3 A3TK, ERIS, Senior Prom, Trident D-5, ALS, SSX, THAAD, Athena-1, Minuteman 2 PLV, Athena-2, Athena-3, X-33, HYSR, GMD/BV-Plus, Venturestar, STARS. Projects: Americom, Anik, Astra, Chinastar, Discovery series, Intelsat, Iridium, Navstar, Palapa, Sirius. Stages: TX-33, A1P-1, A1P-2, X-250, A2P-1, HYSR-1, A3P-1, C3-1, C3-2, C4-1, D-5-1, D-5-2, X-260. Agency: Echostar. 1975 December 13 - . 01:56 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1976-1983; over the Americas at 119 deg W in 1983-1984; over the Pacific Ocean 139 deg W in 1984 As of 5 September 2001 located at 38.03 deg E drifting at 2.422 deg W per day. As of 2007 Mar 9 located at 137.85W drifting at 2.426W degrees per day.
Positioned in geosynchronous orbit over the Americas at 119 deg W in 1976-1984 over the Pacific Ocean 139 deg W in 1984-1985 As of 5 September 2001 located at 72.03 deg W drifting at 5.939 deg W per day. As of 2007 Mar 9 located at 127.82W drifting at 5.942W degrees per day.
TV. BS-2a (Yuri-2a). Domestic satellite broadcasting; development of broadcasting satellite technology. Launch 0758 GMT. N launch vehicle flight no 12. Launching organization NASDA. Positioned in geosynchronous orbit at 110 deg E in 1984-1985; 108 deg E in 1985-1987; 110 deg E in 1987-1988 As of 28 August 2001 located at 69.57 deg E drifting at 4.403 deg W per day. As of 2007 Mar 10 located at 153.52W drifting at 4.395W degrees per day.
Stationed at 120 deg W. C, Ku band communications satellite. Positioned in geosynchronous orbit at 120 deg W in 1984-1993; 115 deg E in 1993-on. As of 2 September 2001 located at 165.12 deg E drifting at 0.985 deg W per day. As of 2007 Mar 10 located at 109.23W drifting at 1.077W degrees per day.
Stationed at 68 deg W. C, Ku band communications satellite. Positioned in geosynchronous orbit at 69 deg W in 1984-1997; 115 deg E in 1997-1998 As of 5 September 2001 located at 65.20 deg E drifting at 1.887 deg W per day. As of 2007 Mar 9 located at 64.76W drifting at 1.866W degrees per day.
Stationed at 103 deg W. Ku band communications satellite. Positioned in geosynchronous orbit at 103 deg W in 1985-1996; 105 deg W in 1997-1999 As of 5 September 2001 located at 105.33 deg W drifting at 0.011 deg W per day. As of 2007 Mar 9 located at 105.07W drifting at 0.006W degrees per day.
Released by STS 61B 11/28/85; 81 deg W. Positioned in geosynchronous orbit at 81 deg W in 1985-1996; 85 deg W in 1996-1997; 81 deg W in 1997-1999 As of 6 September 2001 located at 80.95 deg W drifting at 0.009 deg W per day. As of 2007 Mar 9 located at 157.11W drifting at 2.398W degrees per day.
Stationed at 117 deg E. BS-2b (Yuri-2b). Domestic satellite broadcasting; development of broadcasting satellite technology. Launching organization NASDA. N launch vehicle flight no 14. Launch time 0755 GMT. Positioned in geosynchronous orbit at 110 deg E in 1986-1991 As of 5 September 2001 located at 13.60 deg W drifting at 3.524 deg W per day. As of 2007 Mar 11 located at 77.04E drifting at 3.551W degrees per day.
Ku band communications satellite. Stationed at 70 degrees W. Positioned in geosynchronous orbit at 105 deg W in 1986-1992; 125 deg W in 1992-1997 As of 5 September 2001 located at 148.11 deg W drifting at 1.728 deg W per day. As of 2007 Mar 10 located at 2.39W drifting at 1.699W degrees per day.
US domestic communications; 87 deg W. C, Ku band communications satellite. Positioned in geosynchronous orbit at 87 deg W in 1988-1997; 83 deg W in 1997-1999 As of 2 September 2001 located at 107.85 deg W drifting at 2.220 deg W per day. As of 2007 Mar 9 located at 153.60E drifting at 2.179W degrees per day.
AKM malfunctioned, but orbit achieved using on-board propulsion system. Ku band communications satellite. Positioned in geosynchronous orbit at 93 deg W in 1989-1996; 105 deg W in 1996-1999 As of 5 September 2001 located at 105.39 deg W drifting at 0.005 deg W per day. As of 2007 Mar 9 located at 105.31W drifting at 0.004W degrees per day.
European TV broadcast; 19.2 deg W. Astra 1A provides TV coverage to Western Europe. The satellite is owned and operated by Société Europíenne des Satellites (SES), a private company formed in 1985. Astra 1A is based in the GE 4000 series platform, and was the first in a network of four satellites. Spacecraft: GE 4000 platform.3-axis stabilisation with momentum wheels, magnetic torquers, Earth sensors and 16 blowdown monopropellant hydrazine thrusters. Solar arrays provide 2800 W BOL, 3 50 Ahr NiH batteries. GEO insertion by Star 37XFP solid rocket motor. Payload: 16 Ku-band transponders (with six spares) . Positioned in geosynchronous orbit at 19 deg E in 1989-1999 As of 5 September 2001 located at 19.38 deg E drifting at 0.002 deg W per day. As of 2007 Mar 10 located at 13.01E drifting at 6.968W degrees per day.
Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.
Stationed at 137 deg W. Positioned in geosynchronous orbit at 137 deg W in 1990-1991; 139 deg W in 1991; 137 deg W in 1991-1999 As of 5 September 2001 located at 78.98 deg W drifting at 0.013 deg W per day. As of 2007 Mar 9 located at 151.83E drifting at 3.912W degrees per day.
Stationed at 125 deg W. Ku band communications satellite. Positioned in geosynchronous orbit at 125 deg W in 1990-1992; 105 deg W in 1992-1999 As of 6 September 2001 located at 104.95 deg W drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 74.47W drifting at 4.077W degrees per day.
Stationed at 19.2 deg E; European coverage. Astra 1B provides TV coverage to Western Europe. The satellite is owned and operated by Société Europíenne des Satellites (SES), a private company formed in 1985. Astra 1B is the second in a network of four satellites. SES acquired Astra 1B from DBS Crimson Satellite Associates while still under construction by GE Astro Space (as Satcom K3). Astra 1B is colocated with Astra 1A, and doubled the number of channels provided by the Astra network. Spacecraft: GE 5000 platform.3-axis stabilisation with momentum wheels, magnetic torquers, Earth sensors and 20 blowdown monopropellant hydrazine thrusters. Solar arrays provide 4850 W BOL, 4 50 Ahr NiH batteries. GEO insertion provided by 2 500N bipropellant motors. Payload: 16 Ku-band transponders (with six spares) Positioned in geosynchronous orbit at 19 deg E in 1991-1999 As of 5 September 2001 located at 19.20 deg E drifting at 0.002 deg W per day. As of 2007 Mar 10 located at 92.40W drifting at 6.354W degrees per day.
Stationed at 139 deg W. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit at 139 deg W in 1991-1999 As of 30 August 2001 located at 148.31 deg E drifting at 4.531 deg W per day. As of 2007 Mar 9 located at 2.15E drifting at 4.534W degrees per day.
Stationed at 21.5 deg W. Intelsat K is a single spacecraft purchased to meet critical requirements for Ku-band capacity over the Atlantic region, driven primarily by international broadcasters. The satellite was purchased from GE Americom while under construction (as Satcom K4) and required extensive payload modifications. Spacecraft: Based on GE 5000 series bus.3-axis stabilised using magnetotorquers. Hydrazine propulsion system. Two large solar panels with 1-axis articulation provide 4800 W BOL.4 50 Ahr NiH batteries. Payload: 16 Ku-band transponders which can be configured into 32 high quality television channels. Permits access from ground antennas 1.2 meters dia. and smaller. Launch vehicle put payload into geosynchronous transfer orbit with GCS trajectory option. Positioned in geosynchronous orbit at 21 deg W in 1992-1999 As of 6 September 2001 located at 21.54 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 160.51W drifting at 11.137W degrees per day.
Stationed at 97 deg W. 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 IFR trajectory option. Positioned in geosynchronous orbit at 97 deg W in 1994-1997 As of 5 September 2001 located at 100.42 deg W drifting at 0.039 deg E per day. As of 2007 Mar 10 located at 97.36W drifting at 0.024W degrees per day.
15 Ku-band transponders; boosted into geosynch orbit by satellite thrusters following Delta failure that left satellite in LEO; unplanned use of satellite propellant cut usable satellite lifetime by approx. 50 percent. Stationed at 116.0 deg E. Stage 1 SRM failure Positioned in geosynchronous orbit at 116 deg E in 1995-1999 As of 5 September 2001 located at 47.22 deg E drifting at 0.022 deg E per day. As of 2007 Mar 9 located at 152.88E drifting at 2.155W degrees per day.
Direct TV for continental US. Stationed at 89.0 deg W. Positioned in geosynchronous orbit at 89 deg W in 1995-1999 As of 5 September 2001 located at 88.96 deg W drifting at 0.003 deg W per day. The Telstar 4 (former Telstar 402R) satellite suffered a power failure on September 19 2003 and was a total loss. It was part of AT&T's satellite fleet, later sold to Loral Skynet by 2003 in the process of being sold to Intelsat. As of 2007 Mar 10 located at 116.15W drifting at 0.086W degrees per day.
TV; 24 C-band and 9 Ku-band transponders. Stationed at 100.5 deg E. Positioned in geosynchronous orbit at 100 deg E in 1995-1999 As of 5 September 2001 located at 100.49 deg E drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 100.49E drifting at 0.011W degrees per day.
16 Ku-band transponders. Stationed at 119 deg W. Positioned in geosynchronous orbit at 119 deg W in 1996-1999 As of 5 September 2001 located at 147.96 deg W drifting at 0.007 deg E per day. As of 2007 Mar 9 located at 148.10W drifting at 0.008W degrees per day.
Geostationary at 64.1E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 64 deg E in 1996-1999 As of 5 September 2001 located at 63.98 deg E drifting at 0.003 deg E per day. As of 2007 Mar 10 located at 64.52E drifting at 0.006W degrees per day.
Geostationary at 103.0W. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 103 deg W in 1996-1999 As of 4 September 2001 located at 103.06 deg W drifting at 0.009 deg W per day. As of 2007 Mar 11 located at 103.03W drifting at 0.006W degrees per day.
Geostationary at 157.6E. Launch vehicle put payload into geosynchronous transfer orbit with RAAN Cntl trajectory option. Positioned in geosynchronous orbit at 178 deg E in 1997-1999 As of 5 September 2001 located at 178.02 deg E drifting at 0.006 deg W per day. As of 2007 Mar 10 located at 178.19E drifting at 0.002E degrees per day.
Geosynchronous. Stationed over 64.2E. The Intelsat 8 and 8A vehicles are the latest in the Intelsat satellite series. Spacecraft: 3-axis stabilised. Two large solar panels with 1-axis articulation. Payload: 38 C-Band and 6 Ku-Band transponders.22,000 telephone calls and 3 colour TV broadcasts simultaneously. Or up to 112,500 telephone circuits using digital circuit multiplication equipment (DCME). Two independently steerable Ku-band spot beams. Interconnected operation between C- and Ku-bands.
Financial/Operational:
Lockheed/General Electric contract October 16 1992 $ 165 million for 2 units- potential 5 units. Positioned in geosynchronous orbit at 47 deg E in 1997; 62 deg E in 1997; 64 deg E in 1997-1998; 31 deg W in 1998-1999 As of 5 September 2001 located at 31.47 deg W drifting at 0.013 deg W per day. As of 2007 Mar 5 located at 31.46W drifting at 0.006W degrees per day.
Geosynchronous. Stationed over 174.1E Positioned in geosynchronous orbit at 174 deg E in 1997-2000; 177 deg E in 2000. As of 1 September 2001 located at 174.00 deg E drifting at 0.001 deg E per day. As of 2007 Mar 11 located at 32.91E drifting at 0.000W degrees per day.
Geosynchronous, 52 C-band and 12 Ku-band transponders. Stationed over 21 deg W in 1997-2001. Later assigned to Intelsat subsidiary New Skies, redesignated NSS 5, and moved to 183 deg E to connect North America with all major destinations in the Pacific Rim. As of 2007 Mar 7 located at 177.05W drifting at 0.001E degrees per day.
Geosynchronous. Stationed over 61.4W Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 61 deg W in 1997-1999 As of 5 September 2001 located at 61.53 deg W drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 61.50W drifting at 0.007W degrees per day.
The Lunar Prospector was designed for a low polar orbit investigation of the Moon, including mapping of surface composition and possible polar ice deposits, measurements of magnetic and gravity fields, and study of lunar outgassing events. Data from the 1 to 3 year mission will allow construction of a detailed map of the surface composition of the Moon, and will improve understanding of the origin, evolution, current state, and resources of the Moon. After launch, the Lunar Prospector had a 105 hour cruise to the Moon, followed by insertion into a near-circular 100 km altitude lunar polar orbit with a period of 118 minutes. The nominal mission duration was one year.
The Proton launch vehicle placed the Iridium cluster and the Block DM2 stage into low parking orbit. The DM2 fired twice to enter the deployment orbit and dispensed the seven satellites, which used their own propulsion units to reach operational altitude. The DM2 stage then fired again to deorbit itself, to avoid creating space debris. SV068 placed in Plane 1. Ascending node 167.8 degrees.
Geostationary at 148.0 degrees W. Positioned in geosynchronous orbit at 128 deg W in 1998; 148 deg W in 1998-1999; 110 deg W in 1999; 119 deg W in 2000. As of 5 September 2001 located at 118.91 deg W drifting at 0.001 deg W per day. As of 2007 Mar 10 located at 77.02W drifting at 0.001W degrees per day.
Also known as Chinastar 1; comsat to serve China, India, Korea and Southeast Asia with 18 C-band and 20 Ku-band transponders. Operated by the China Orient Telecommunications Satellite Company, part of the Chinese telecommunications ministry. Zhongwei 1 and the CZ-3B's final liquid hydrogen upper stage were placed in an initial supersynchronous 216 x 85,035 km x 24.4 deg transfer orbit. Geostationary at 87.6 degrees E. Positioned in geosynchronous orbit at 87 deg E in 1998-1999 As of 6 September 2001 located at 87.49 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 87.64E drifting at 0.010W degrees per day.
The Titan core vehicle operated correctly, but a software error in the Centaur stage resulted in all three planned burns being made at the wrong times, during the first orbit instead of over a six hour period. The three burns planned to place Milstar successively in a 170 x 190 km parking orbit, a geostationary transfer orbit, and finally geosynchronous orbit. Instead, at 19:00 GMT, several hours before the scheduled third burn, Milstar separated into a useless 740 km x 5000 km orbit. Milstar-2 F1 was the first upgraded Milstar with an extra Medium Data Rate payload with a higher throughput. The payload included EHF (44 GHz), SHF (20 GHz) and UHF communications transponders and satellite-to-satellite crosslinks, with narrow beams to avoid jamming.
Telesat Canada's Nimiq television broadcasting satellite was placed into a 7050 km x 35790 km x 15.9 degree transfer orbit. The Nimiq was to use its liquid apogee engine (Royal Ordnance Leros 1) to reach geosynchronous orbit. Telesat Canada also operated the Anik Canadian domestic communications satellites, the first of which was launched in 1972. Positioned in geosynchronous orbit at 91 deg W in 1999. As of 4 September 2001 located at 91.11 deg W drifting at 0.002 deg W per day. As of 2007 Mar 9 located at 91.18W drifting at 0.012W degrees per day.
The launch vehicle delivered its H-10-3 third stage and the Telkom 1 payload into a 221 km x 35687 km x 7.0 degree geosynchronous transfer orbit 21 minutes after launch. Telkom 1 was owned by PT Telkomunikasi of Indonesia and was a successor to the Palapa series of satellites. Mass of Telkom 1 was 1700 kg in geosynchronous orbit after its on-board engine made the apogee burn. Stationed at 108 deg E. Positioned in geosynchronous orbit at 108 deg E in 1999. As of 3 September 2001 located at 107.98 deg E drifting at 0.011 deg W per day. As of 2007 Mar 11 located at 107.98E drifting at 0.014W degrees per day.
Geosynchronous communications satellite. Stationed at 112 deg E. Positioned in geosynchronous orbit at 112 deg E in 1999. As of 31 August 2001 located at 115.99 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 116.12E drifting at 0.008W degrees per day.
Geosynchronous communications satellite. Stationed at 75 deg E. Positioned in geosynchronous orbit at 75 deg E in 1999. As of 2 September 2001 located at 74.98 deg E drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 75.00E drifting at 0.004W degrees per day.
Provided C and Ku-band communications services for GE Americom, replacing Spacenet 4. Stationed at 101 deg W. Positioned in geosynchronous orbit at 74 deg W in 1999. As of 5 September 2001 located at 101.12 deg W drifting at 0.008 deg W per day. As of 2007 Mar 11 located at 101.02W drifting at 0.004W degrees per day.
Geosynchronous communications satellite for the ACES consortium (PSN of Indonesia, PLDT of the Phillipines, Lockheed Martin, and Jasmine of Thailand). The satellite had two large 12-m diameter L-band antennae for cellular telephone relay. Stationed at 123 deg E. Positioned in geosynchronous orbit at 123 deg E in 2000. As of 5 September 2001 located at 122.97 deg E drifting at 0.023 deg W per day. As of 2007 Mar 10 located at 123.10E drifting at 0.005W degrees per day.
Imager for Magnetopause to Aurora Global Exploration was a MIDEX (mid-sized Explorer mission) developed by NASA-Goddard and the SWRI (Southwest Research Institute) of San Antonio, Texas. The spin-stabilised spacecraft carried a set of neutral atom and ultraviolet imagers, and antennae to study radio wavelength emissions from the magnetosphere plasma. The RPI radio plasma imager has four long wire antennae which will be deployed to a span of half a kilometre.
Direct Broadcasting satellite. GE Americom satellite to provide cable TV distribution coverage to the USA. Equipped with 24 C-band transponders. Its dry mass was 912 kg and it carried 1023 kg of fuel at launch. The satellite is an A2100A model built by Lockheed Martin/Lockheed, the first lightweight A2100 with a mass about half that of earlier A2100 satellites. By September 19 GE 7 was in a 35,832 x 35,869 km x 0.1 deg orbit drifting over 146 deg W. Stationed at 137 deg W. Positioned in geosynchronous orbit at 137 deg W in 2000. As of 4 September 2001 located at 136.92 deg W drifting at 0.003 deg E per day. As of 2007 Mar 9 located at 137.03W drifting at 0.000E degrees per day.
Launch attempt on September 20 scrubbed. The NOAA polar orbit weather satellite, an Advanced Tiros N with a suite of imaging and sounding instruments. The two-stage Titan II launch vehicle, serial 23G-13, put NOAA-L into a suborbital -2500 x 800 km x 98.0 deg trajectory. The spacecraft's Thiokol Star 37XFP solid motor fired at apogee to circularize the sun-synchronous orbit at 800 km.
Ku-band communications satellite to provide broadcast services for eastern Asia. Stationed at 108 deg E. Positioned in geosynchronous orbit at 108 deg E in 2000. As of 4 September 2001 located at 108.22 deg E drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 108.21E drifting at 0.011W degrees per day.
N-SAT-110, also known as Superbird 5, was jointly owned by SCC (Space Communications Corporation of Tokyo) and JSat (Japan Satellite Systems). SCC controlled the vehicle on orbit. The satellite carried 24 Ku-band transponders. By October 15 N-SAT-110 was in a 35610 x 35752 km x 0.1 deg orbit drifting past 109 deg E. Stationed at 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 2000. As of 4 September 2001 located at 110.06 deg E drifting at 0.012 deg W per day. As of 2007 Mar 11 located at 110.07E drifting at 0.007W degrees per day.
Communications satellite. Stationed at 72 deg W. The GE 6 was a Lockheed Martin A2100 series satellite with a mass of 3552 kg at launch and 1900 kg dry. It was to provide broadcast and data services in North America. The DM3 upper stage made two burns and placed the GE 6 in a 5850 x 35726 km x 18.7 deg intermediate transfer orbit at 0441 UTC on October 22. Positioned in geosynchronous orbit at 72 deg W in 2000. As of 3 September 2001 located at 72.01 deg W drifting at 0.008 deg W per day. As of 2007 Mar 11 located at 72.00W drifting at 0.005W degrees per day.
The Delta stage 2 entered a 153 x 418 km x 37 deg parking orbit followed by a 172 x 1144 km second orbit; the PAM-D solid upper stage then fired to give SVN 41 a 20457 km apogee. The Thiokol Star 37FM solid kick motor was fired prior to November 13 to place the spacecraft in its final circular 20,000 km orbit. Placed in Plane F Slot 1 of the GPS constellation.
GE 8 was a C-band TV and data distribution satellite for GE Americom. The Lockheed Martin A2100A spacecraft had a launch mass of 2015 kg, a dry mass of 919 kg, and was equipped with 24 C-band transponders. By December 26 GE 8 had reached an 18656 x 35760 km x 0.4 deg orbit on its way to geostationary orbit. It was jointly owned by AT&T Alascom for Alaskan communications, and was also called Aurora III. Americom and Alascom were originally both RCA subsidiaries. Alascom continued to use the Americom network while GE operated the satellite. The 2.2 tonne (with fuel) spacecraft carried 24 C-band transponders to provide voice, video, and broadband data communications to the contiguous USA, Alaska, and the Caribbean after parking over 139 deg-W longitude. Positioned in geosynchronous orbit at 146 deg W in 2001 As of 5 September 2001 located at 139.01 deg W drifting at 0.000 deg W per day. As of 2007 Mar 11 located at 139.03W drifting at 0.003E degrees per day.
Military Communications satellite. Launch delayed from October 30, December 14, 2000, and February 2 and February 24, 2001. The Milstar DFS 4 satellite (the second Milstar Block 2) provided secure communications for the US Department of Defense, with UHF, EHF and SHF band transmitters. Titan 4B-41 with core stage K-30 took off from Cape Canaveral and placed Milstar and the Centaur TC-22 upper stage in a suborbital trajectory. TC-22 then ignited to enter a 200 km parking orbit, and after two more burns delivered Milstar to geosynchronous drift orbit. Small engines on board the Milstar placed it at its targeted geostationary position. USA 157, a 4.5 tonne spacecraft, was the first in the Milstar 2 series which was capable of higher data rates and was more secure against disabling efforts.
Launch delayed from September 25, October1. National Reconnaissance Office payload that was placed into a sun-synchronous orbit. It was speculated that the payload was an Improved Crystal imaging satellite. That would imply an operational orbit of 150 x 1050 km x 97.9 deg orbit. The satellite belonged to the National Reconnaissance Office's fleet of Earth Imaging System (EIS) satellites. A BBC website reported a resolution of 10 cm in the images. (A commonly used name for the EIS satellites was Advanced Keyhole.) The first member of the EIS fleet was USA 144 (1999-028A), launched in May 1999.
Military Communications satellite. Launch delayed from December 2001. The Titan core stage shut down 9 min after launch on a suborbital trajectory, and separated from the upper stage, Centaur TC-19. TC-19 made three burns to parking orbit, geostationary transfer orbit, and finally geostationary orbit. It then released Milstar Flt-5. Milstar provided secure communications in the EHF, SHF and UHF bands and would be stationed over European longitudes. As of 2007 Feb 16 located at 29.98E drifting at 0.014W degrees per day.
Mobile Telephony satellite. Return to flight after GEM solid booster failure on GBI launch. Launch delayed from February 8, 9 and 10. Five Motorola Iridium satellites were launched for Iridium Satellite LLC, the new company that bought out the bankrupt Iridium LLC. This was the first system replenishment launch since the bankruptcy.
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.
Ariane mission V150 placed Lockheed Martin A2100-class satellite NSS 7 satellite into orbit. The satellite was owned by New Skies, an Intelsat spinoff, and carried a C/Ku band telecoms payload. The spacecraft was in a 24200 x 35706 km x 0.7 deg orbit by April 24, on its way to geosynchrnous orbit. As of 2007 Mar 9 located at 22.01W drifting at 0.010W degrees per day.
Launch delayed from August 2001. The refurbished Titan 2 missile put the NOAA M satellite on a suborbital trajectory of about -2500 x 820 km x 98 deg. at 1829 UTC. At 1837 UTC the NOAA M propulsion module fired its ATK/Thiokol Star 37XFP solid motor for the orbit insertion burn, followed by a hydrazine trim burn to put the satellite in an 807 x 822 km x 98.8 deg operational orbit. NOAA M became NOAA 17 on entering service with the US National Oceanic and Atmospheric Administration as the primary morning weather satellite, supplementing the NOAA 16 afternoon satellite. Built by Lockheed Martin, NOAA M carried weather imagers and microwave and infrared sounders, as well as a SARSAT search-and-rescue package. It had an on-orbit mass of 1475 kg.
Launch delayed from late November, then December 12. The Dutch New Skies Satellites' NSS-6 telecommunications spacecraft was developed by Lockheed Martin Commercial Space Systems. It was to be positioned at 95 deg E to provide broadcasting and business services coverage of the Pacific Rim, Australia, India, the Middle East and southern Africa. As of 2007 Mar 11 located at 95.01E drifting at 0.008W degrees per day.
Dummy EKV payload. Launch delayed from August, September, and December 18, 2003. Booster Verification Test -5 tested a three-stage booster configuration for use with the Missile Defense Agency's Ground-based Midcourse Defense System. Built by Lockheed Martin Corp., the booster was one of two slated for use with the GMD system. The system was designed to intercept and destroy long-range ballistic missiles.
Americom 10 (AMC-10) was a replacement satellite for Satcom C3. It was to be located at 135 deg W. The C-band satellite, to be accompanied by AMC-11 later in 2004, were designed to support SES Americom's cable network in the United States, Canada, the Caribbean, and Mexico. The satellite had a design life of 15 years and carried 24 x 36 MHz C-band transponders. As of 2007 Mar 10 located at 134.97W drifting at 0.005E degrees per day.
Communications satellite for SES Americom, equipped with Ku-band and Ka-band transponders. The Briz-M upper stage made three burns, then released the satellite on October 15 at 03:58 GMT into a 7132 x 35780 km x 18.6 deg orbit. AMC-15's on-board engine would be used to maneuver the spacecraft into its final geostationary orbit. As of 2007 Mar 11 located at 105.02W drifting at 0.003W degrees per day.
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 85� 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.
Delayed from November 9, 2004; January 19, March 18, 2005. Military Autonomous Rendezvous Technology. It tested navigation technologies for rendezvous that directly measured relative position to the target satellite. It was have to rendezvoused with several defunct American satellites. However it was only known to have conducted operations with its own Minotaur upper stage
Delayed from December 2004; February 1, March 17, 2005. Moved up from May 20 2005. Then delayed from May 4, July 29, August 26, September 22, 2005. Became operational at 23:30 GMT on 16 December. First GPS Block IIR-M version, which added extra navigation signals for both civil and military users. The NASA-funded L2C tracking demonstration was managed by JPL and explored the use of a new Civilian code signal (L2C). The data was collected with Trimble NetRS receivers L2C-enabled firmware. The sites were globally distributed: South Africa, Norway, Antarctica, Hawaii, and Alaska.
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.
Astra 1L provided direct-to-home broadcast services to Europe from its location at 19.2� East. It also strengthened the SES in-orbit backup system, extended fleet coverage from the Canary Islands eastwards up to the Russian border, and allowed Astra 2C to be moved from 19.2� East to 28.2� to fulfill high capacity demand from the U.K. and Ireland. Astra 1L was equipped with 29 Ku + 2 Ka active transponders, which would be reduced to 27 active transponders after its first five years of operation.
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
Sirius 4 carried Ku-band and Ka-band communications payloads for Nordic, Baltic and East European communications. Three upper-stage burns placed Sirius 4 into a 6916 km x 35478 km x 17.4 deg geostationary transfer orbit. A series of maneuvers by the satellite using its own Leros engine maneuvered the satellite into geosynchronous orbit, stationed at 5 deg East.
The Briz M stage failed during its second burn, shutting down by 2 minutes 13 seconds early, leaving the satellite in a 770 km x 26447 km x 49.2 deg orbit. The spacecraft separated and raised this to 772 km x 35576 km x 49.0 deg, but operational geostationary orbit could not be attained and the satellite was a writeoff. AMC 14 had a total mass at launch of 4140 kg of which 2130 kg was propellant. The final orbit attained was an inclined orbit at geostationary altitude.
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