 | HS 601
|
Class: Communications. Destination: Geosynchronous Orbit. Nation: USA. Agency: Hughes Communications Inc. Manufacturer: Hughes. 3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimbaled momentum bias wheels. Typically 1658 kg nitrogen tetroxide & MMH in four spheres. Spin-stabilized in transfer orbit. Twin solar wings of three 2.16 x 2.54 m panels carrying large area silicon cells on Kevlar substrate to satisfy 3.3 kW requirement. Eclipse protection provided by Nickel hydrogen batteries. 18 eclipse protected transponders, plus six spares with 63W TWTA. 10.75-10.95 Ghz FSS (&12.5 Ghz BSS) down Ku-band beams, 26 Mhz bandwidth, EIRP 50 dBW min, orthogonal polarization, operating in the FSS range Design Life: 15 years min. Typical orbit: Geostationary. Length: 2.29 m (7.51 ft). Maximum Diameter: 2.54 m (8.33 ft). Span: 18.30 m (60.00 ft). Mass: 4,135 kg (9,116 lb). Main Engine: R-4D. Associated Launch Vehicle: Ariane 42L, Ariane 42P, Ariane 44L, Ariane 44LP, Ariane 44P, Atlas I, Atlas II, Atlas IIA, Atlas IIAS, Atlas IIIB, CZ-2E, Delta 3, Delta 7000, Proton 8K82K / 11S861-01, Shuttle.
HS 601 Chronology
- 1992 October 28 - Galaxy 7 - Program: Galaxy. Launch Site: Kourou. Launch Vehicle: Ariane 42P. Mass: 2,968 kg (6,543 lb). Perigee: 35,917 km (22,317 mi). Apogee: 35,968 km (22,349 mi). Inclination: 1.50 deg. Period: 1,444.10 min. Duration: 2,947.00 days.
Geostationary at 91 deg W. The Galaxy 7 satellite failed on November 22, 2000, the third such satellite to fall victim to a design flaw in the on-board computers. Positioned in geosynchronous orbit at 91 deg W in 1992-1999 As of 1 September 2001 located at 32.55 deg E drifting at 2.022 deg W per day. As of 2007 Mar 10 located at 141.47W drifting at 2.077W degrees per day.
- 1993 December 18 - DBS 1 - Program: DirecTV. Launch Site: Kourou. Launch Vehicle: Ariane 44L. Mass: 2,860 kg (6,300 lb). Perigee: 35,775 km (22,229 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Stationed at 101.2 deg W. DirecTV, Inc. is a subsidiary of Hughes Communications and offers commercial satellite television service to the US. The orbital part of the system consists of 3 Hughes-built geosynchronous satellites. Broadcast services began in mid-1994. Competitors include the similar Primestar and USSB services, as well as older C-band satellite services and cable TV companies. Spacecraft: DirecTV uses the Hughes HS-601 spacecraft design.3-Axis stabilised, zero momentum biased control system. Two solar arrays (4 panels each side) span 31 meters and generate 4.3 kW power. Payload: The 2.5 m diameter graphite transmit reflector performs beam shaping.16 x 120 watt Ka-Band (12.2 - 12.7 GHz) transponders with 48-53 dBw EIRP and 24 MHz bandwidth. Power is higher in areas with heavy rain. The high power combined with Reed Solomon error correction coding allow the use of small 18 inch antennas by customers.
Financial/Operational:
FCC approved Direct Broadcast Satellites in 1986. By 1997 DirecTV had 2.6 million of 5.0 million US direct broadcast television subscribers. Direct Broadcast Satellites cost $ 175 million each and have 150 video channels. Positioned in geosynchronous orbit at 101 deg W in 1994-1999; 110 deg W in 1999-2000 As of 6 September 2001 located at 109.78 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 72.51W drifting at 0.011W degrees per day.
- 1993 May 12 - Astra 1C - Program: Astra. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 2,790 kg (6,150 lb). Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Stationed at 1.2 deg E. TV distribution services to Western Europe and the Canary Islands under franchise from the Grand Duchy of Luxembourg. Contracted and controlled by the private company formed in 1985 called Société Europíenne des Satellites (SES). This is the third in a series of 4 medium power satellites, and will act primarily as Astra 1A's backup. Spacecraft: HS-601 platform.3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimballed momentum bias wheels.1658 kg nitrogen tetroxide & MMH in four spheres. Spin-stabilised in transfer orbit. Twin solar wings of three 2.16 x 2.54 m panels carrying large area silicon cells on Kevlar substrate to satisfy 3.3 kW requirement. Eclipse protection provided by Nickel hydrogen batteries. Payload: 18 eclipse protected transponders, plus six spares with 63W TWTA 10.95-11.200 Ghz down Ku-band European beams in 250 Mhz band adjacent (below) to Astra 1A, 26 Mhz bandwidth, eirp 50 dBW min, orthogonal polarisation, operating in the FSS range Positioned in geosynchronous orbit at 19 deg E in 1993-1999 As of 5 September 2001 located at 19.21 deg E drifting at 0.002 deg W per day. As of 2007 Mar 11 located at 4.54E drifting at 0.051E degrees per day.
- 1994 December 1 - Panamsat 3 - Program: Panamsat. Launch Site: Kourou. Launch Vehicle: Ariane 42P. FAILURE: Stage 3 gas generator.
- 1994 November 1 - Astra 1D - Program: Astra. Launch Site: Kourou. Launch Vehicle: Ariane 42P. Mass: 2,924 kg (6,446 lb). Perigee: 35,773 km (22,228 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.0200 deg. Period: 1,436.00 min.
European DBS and radio. Stationed at 19.29 deg E. TV distribution services to Western Europe and the Canary Islands under franchise from the Grand Duchy of Luxembourg. Contracted and controlled by the private company formed in 1985 called Société Europíenne des Satellites (SES). This is the last in a series of 4 medium power satellites, and will act primarily as Astra 1B and 1C's backup. It will also carry four 12.5 Ghz BSS transponders that can be combined for HDTV. Spacecraft: HS-601 platform.3-axis unified ARC 22 N and one Marquardt 490 N bipropellant thrusters, Sun and Barnes Earth sensors and two 61 Nms 2-axis gimballed momentum bias wheels.1658 kg nitrogen tetroxide & MMH in four spheres. Spin-stabilised in transfer orbit. Twin solar wings of three 2.16 x 2.54 m panels carrying large area silicon cells on Kevlar substrate to satisfy 3.3 kW requirement. Eclipse protection provided by Nickel hydrogen batteries. Payload: 18 eclipse protected transponders, plus six spares with 63W TWTA 10.75-10.95 Ghz FSS (&12.5 Ghz BSS) down Ku-band European beams in 250 Mhz band adjacent (below) to Astra 1C, 26 Mhz bandwidth, eirp 50 dBW min, orthogonal polarisation, operating in the FSS range Positioned in geosynchronous orbit at 19 deg E in 1995-1998; 28 deg E in 1998; 19 deg E in 1998-1999; 28 deg E in 2000.- As of 3 September 2001 located at 24.18 deg E drifting at 0.006 deg E per day. As of 2007 Mar 10 located at 23.50E drifting at 0.008W degrees per day.
- 1995 August 3 - Panamsat 4 - Program: Panamsat. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 3,043 kg (6,708 lb). Perigee: 35,776 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
16 C-Band, 24 Ku-Band transponders; 320 radio + 120 DirecTV channels. Stationed at 68.5 deg E. Positioned in geosynchronous orbit at 68 deg E in 1995-1999 As of 5 September 2001 located at 72.03 deg E drifting at 0.003 deg W per day. As of 2007 Mar 11 located at 72.00E drifting at 0.003W degrees per day.
- 1995 December 15 - Galaxy 3R - Program: Galaxy. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIA. Mass: 2,980 kg (6,560 lb). Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Stationed at 95 deg W; 24 C-band, 24 Ku-band transponders; TV for Caribbean and Central America. Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option. Positioned in geosynchronous orbit at 95 deg W in 1996-1999 As of 3 September 2001 located at 95.05 deg W drifting at 0.008 deg W per day. As of 2007 Mar 9 located at 132.80W drifting at 0.084W degrees per day.
- 1995 January 25 - Apstar 2 - Program: Apstar. Launch Site: Xichang. Launch Vehicle: CZ-2E. FAILURE: Shortcomings in the guidance system lead to the vehicle not anticipating the true effects of hoizontal wind-shear once the mountains surrounding the launch site were cleared. This caused the nose fairing to collapse and the spacecraft to be destroyed.
Because the Apstar failure happened a few seconds later than Optus, the consequences were catastrophic. The vehicle was destroyed, and the falling wreckage landed on a village down-range of the launch site, killing at least 20 and perhaps as many as 120 people.
- 1996 February 1 - Palapa C-1 - Program: Palapa. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIAS. Perigee: 35,777 km (22,230 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
30 C-band, 6 Ku-band transponders. Geostationary at 150.4E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 113 deg E in 1996; 150 deg E in 1996-1999 As of 5 September 2001 located at 50.03 deg E drifting at 0.006 deg E per day. As of 2007 Mar 11 located at 38.04E drifting at 0.007E degrees per day.
- 1998 August 27 - Galaxy 10 - Program: Galaxy. Launch Site: Cape Canaveral. Launch Vehicle: Delta 3. FAILURE: Due to guidance system induced oscillation all solid motor gimbal hydraulic fluid exhausted after only 71 seconds of flight. Range safety detroyed booster 75 seconds into flight at 16 km altitude. Mass: 3,876 kg (8,545 lb).
Built by Hughes/El Segundo for Panamsat. The satellite carried 24 C-band and 24 Ku-band transponders to provide US/Caribbean coverage, and was to have replaced the ageing SBS-5 satellite at 123 deg West. Replenishing the Galaxy/PAS constellation was a high priority for Panamsat following the loss of Galaxy 4 and problems with Galaxy 7. Galaxy 11 was not scheduled to go up until the first launch of the Sea Launch Zenit-3SL in early 1999, and this booster was in limbo due to legal problems with unauthorised transfer of technical data from Boeing to Russia. In addition there were several PAS satellites awaiting launch over the next year on Proton and Ariane vehicles.
- 1998 August 30 - Astra 2A - Program: Astra. Launch Site: Baikonur. Launch Vehicle: Proton 8K82K / 11S861-01. Perigee: 35,766 km (22,223 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
The first burn of the Proton's Block DM3 put the spacecraft into a 220 x 36,007 km x 51.6 deg transfer orbit. Astra 2A satellite was a Hughes HS-601, owned by Societe Europeene de Satellites, based in Luxembourg. Luxembourg has not registered any of the Astra satellites with the United Nations, in violation of treaty requirements. Geostationary at 28.3 degrees E. Used HS-601 XIPS ion engine for station keeping. Positioned in geosynchronous orbit at 28 deg E in 1998-1999 As of 4 September 2001 located at 28.21 deg E drifting at 0.001 deg W per day. As of 2007 Mar 10 located at 28.20E drifting at 0.028W degrees per day.
- 1998 December 22 - PAS 6B - Program: Panamsat. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 3,475 kg (7,661 lb). Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
The Ariane third stage placed the PAS 6B into a 228 km x 35717 km x 7.0 degree orbit. The satellite’s on board rocket system will move it into its final geostationary position over South America. PAS 6B will provide direct TV broadcasting service in replacement of PAS 6, a Loral satellite which had problems with its solar arrays. The new satellite had 32 Ku-band transponders. Positioned in geosynchronous orbit at 43 deg W in 1999. As of 3 September 2001 located at 43.17 deg W drifting at 0.020 deg W per day. As of 2007 Mar 9 located at 43.11W drifting at 0.015W degrees per day.
- 1998 December 6 - Satmex 5 - Program: Morelos. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 4,135 kg (9,116 lb). Perigee: 35,774 km (22,228 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
The Ariane placed the Satmex 5 satellite into a 211km x 21516 km x 7.0 degree orbit from which the satellite was to use its on-board engine to reach geostationary orbit. Satmex 5 was operated by Satellites Mexicanos S.A. de C.V, which took over the Morelos constellation from Mexican Secretaria de Comunicaciones y Transportes. Satmex 5 replaced Morelos 2 and carried the XIPS ion engine station-keeping system. Positioned in geosynchronous orbit at 116 deg W in 1998-1999 As of 5 September 2001 located at 116.79 deg W drifting at 0.008 deg W per day. As of 2007 Mar 10 located at 116.81W drifting at 0.002W degrees per day.
- 1998 March 16 - USA 138 - Program: UHF. Launch Site: Cape Canaveral. Launch Vehicle: Atlas II. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 3.30 deg. Period: 1,436.10 min.
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.
- 1998 October 20 - USA 140 - Program: UHF. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIA. Mass: 3,200 kg (7,000 lb). Perigee: 35,773 km (22,228 mi). Apogee: 35,806 km (22,248 mi). Inclination: 3.80 deg. Period: 1,436.20 min.
The orbit at burnout of the Centaur was 286 km x 25866 km x 27.0 degree. Modification of the orbit to a geostationary 38,300 km circular x 0.0 degree inclination was accomplished by the Marquardt R-4D liquid propellant motor on the HS-601 spacecraft. The satellite carried UHF and EHF transponders for naval communications, and a Ka-band Global Broadcast Service video relay package. Launch mass of 3200 kg dropped to 1550 kg once geostationary orbit was reached. UHF F/O F9 was placed over the Atlantic Ocean in geosynchronous orbit at 174 deg W in 1998; 22 deg W in 1999.Additional Details: USA 140 (12350).
- 1999 February 16 - JCSAT-6 - Program: JCSAT. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIAS. Mass: 2,900 kg (6,300 lb). Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day.
- 1999 March 21 - Asiasat 3S - Program: Asiasat. Launch Site: Baikonur. Launch Vehicle: Proton 8K82K / 11S861-01. Mass: 3,463 kg (7,634 lb). Perigee: 35,780 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.10 deg.
A replacement for Asiasat 3, placed in the wrong orbit by a Proton launch in 1997, Asiasat 3S carried C and Ku band transponders. The Blok DM3 upper stage placed it a 9,677 km x 35,967 km x 13.1 deg geosynchronous transfer orbit. Asiasat's on-board R4D apogee engine was to be used to raise perigee to geostationary altitude. Mass in transfer orbit was 3,463 kg, down to 2,500 kg after insertion in geostationary orbit. Operated in geosynchronous orbit at 105 deg E from 1999. As of 4 September 2001 located at 105.52 deg E drifting at 0.008 deg E per day. As of 2007 Mar 11 located at 105.46E drifting at 0.017W degrees per day.
- 1999 May 5 - Orion 3 - Program: Orion. Launch Site: Cape Canaveral. Launch Vehicle: Delta 3. FAILURE: Engine failure at ignition for second burn of Centaur stage. Perigee: 2,456 km (1,526 mi). Apogee: 2,529 km (1,571 mi). Inclination: 19.80 deg. Period: 138.60 min.
The Centaur RL-10B-2 second stage engine's combustion chamber ruptured at the beginning of the second burn. The hot gases already in the chamber vented, putting the stage/spacecraft assembly into an uncontrollable tumble. The Orion 3 communications satellite ended up in a useless parking orbit of 162 km x 1378 km x 29.5 deg. It was to have served the Asia-Pacific region for Loral Orion with 33 Ku-band and 10 C-band transponders.
- 1999 October 10 - DirecTV 1R - Program: DirecTV. Launch Site: Kiritimati. Launch Vehicle: Zenit-3SL. Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg.
Second successful Zenit-3SL flight from the Odyssey launch platform in the Pacific Ocean at 154 deg W, 0 deg N. First flight to carry a commercial payload. The satellite used its R-4D apogee engine to enter geostationary orbit at 81.6 deg W. Finally stationed at 101 deg W. Positioned in geosynchronous orbit at 81 deg W in 1999. As of 5 September 2001 located at 101.19 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 100.87W drifting at 0.007W degrees per day.
- 2000 April 19 - Galaxy 4R - Program: Galaxy. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 3,668 kg (8,086 lb). Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg.
Galaxy 4R carried 28 Ku-band and 28 C-band transponders. After insertion in a standard 219 x 32007
km x 7.0 deg geostationary transfer orbit, Galaxy 4R's R-4D apogee engine raised orbit to 35765 x 35792 km x 0.1 deg by April 27 and was over 67 deg W by late April. Final destination was 99 deg W. The Galaxy satellites provide US domestic telecommunications services. 4R replaces the original Galaxy 4H which failed in May 1998, putting pagers out of action across the USA. Stationed at 99 deg W. Positioned in geosynchronous orbit at 73 deg W in 2000. As of 5 September 2001 located at 98.99 deg W drifting at 0.016 deg W per day. As of 2007 Mar 11 located at 76.88W drifting at 0.001E degrees per day.
- 2000 February 18 - Superbird 4 - Launch Site: Kourou. Launch Vehicle: Ariane 44LP. Mass: 4,057 kg (8,944 lb). Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg.
Provided geosynchronous communications services for the Space Communications Corporation of Japan. Carried 23 Ku-band and 6 Ka-band transponders, and was equipped with a Marquardt R4D apogee engine and XIPS ion propulsion stationkeeping system. Stationed at 162 deg E. Positioned in geosynchronous orbit at 162 deg E in 2000. As of 4 September 2001 located at 162.01 deg E drifting at 0.003 deg W per day. As of 2007 Mar 9 located at 161.98E drifting at 0.004W degrees per day.
- 2000 January 25 - Galaxy 10R - Program: Galaxy. Launch Site: Kourou. Launch Vehicle: Ariane 42L. Mass: 1,987 kg (4,380 lb). Perigee: 35,785 km (22,235 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg.
Geosynchronous communications satellite launched to supplement Panamsat's Galaxy cable TV distribution constellation. It carried Ku and C band transponders and was to be stationed at 127 deg W. A replacement for Galaxy 10, lost on the first Delta 3 launch failure. Stationed at 123 deg W. Positioned in geosynchronous orbit at 123 deg W in 2000. As of 3 September 2001 located at 122.99 deg W drifting at 0.002 deg E per day. As of 2007 Mar 11 located at 123.03W drifting at 0.000E degrees per day.
- 2000 June 30 - TDRS 8 - Program: STS. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIA. Mass: 3,180 kg (7,010 lb). Perigee: 35,773 km (22,228 mi). Apogee: 35,800 km (22,200 mi). Inclination: 5.40 deg. Period: 1,436.10 min.
Launch delayed from June 29. First Advanced Tracking and Data Relay Satellite, using a Hughes HS 601 satellite bus. It included an S-band phased array antenna and two Ku/Ka band reflectors 4.6 meters in diameter. The satellite was launched into a a 167 x 577 km x 28.3 deg parking orbit at 13:05 GMT. The Centaur upper stage made a second burn at 13:21 GMT, releasing the satellite into a subsynchronous transfer orbit of 237 x 27,666 km x 27.0 deg. The satellite's own Primex/Marquardt R4D liquid apogee engine would be used to maneuver the satellite into its final geosynchronous orbit. Stationed at 151 deg W. Positioned in geosynchronous orbit at 150 deg W in 2000. As of 5 September 2001 located at 149.99 deg W drifting at 0.014 deg E per day. As of 2007 Mar 11 located at 145.38E drifting at 3.007W degrees per day.
- 2001 June 16 - Astra 2C - Program: Astra. Launch Site: Baikonur. Launch Vehicle: Proton 8K82K / 11S861-01. Mass: 3,728 kg (8,218 lb). Perigee: 35,768 km (22,225 mi). Apogee: 35,805 km (22,248 mi). Inclination: 0.10 deg. Period: 1,436.10 min.
Launch delayed from June 11. Astra 2C was a European (SES - Societe Europeene des Satellites, Luxembourg) geosynchronous communications Boeing 601HP spacecraft. The 3.7 tonne (including 1.2 tonne of fuel), 8 kW satellite was the fifth in the Astra series. It carried 32 Ku-band transponders to provide voice, video, and data links to Western Europe through a pair of 3 m diameter dishes, after parking over 28.2 deg-E longitude. As of 5 September 2001 located at 19.13 deg E drifting at 0.005 deg W per day. As of 2007 Mar 10 located at 19.23E drifting at 0.024W degrees per day.
- 2001 June 19 - ICO F-2 - Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIAS. Mass: 2,750 kg (6,060 lb). Perigee: 10,385 km (6,452 mi). Apogee: 10,389 km (6,455 mi). Inclination: 45.00 deg. Period: 360.10 min.
Launch delayed from June 5. The ICO-2 satellite was launched by British New ICO (formerly ICO Global Communications) to provide mobile communications and data/Internet services at S-band, supporting 4500 simultaneous calls. The Boeing BSS-601M satellite was similar to the standard geostationary 601 model except that it omitted the R-4D apogee engine and associated fuel, and had a larger payload section. Launch mass was 2700 kg; dry mass was around 2200-2400 kg with the remainder being station-keeping fuel. The AC-156 launch vehicle's Centaur stage reached a 167 x 10099 km x 44.6 deg transfer orbit 10 minutes after launch. A second burn 1.5 hours later put ICO-2 into a circular 10,100 km orbit. The first ICO satellite was launched in March 2000 but failed to reach orbit. ICO-2 was used for testing of the ICO system before the remaining satellites would be launched. Unlike the Iridium and Globalstar constellations, ICO proposed to use a small number of large satellites. The ICO fleet, anticipated to consist of 10 satellites, was to enable relay in S- and C-bands of voice and internet communications from/to land and ocean based mobile telephones. With a total power of 5 kW, ICO F2 was to enable a simultaneous capacity in 4,500 channels.
- 2001 May 15 - PAS 10 - Launch Site: Baikonur. Launch Vehicle: Proton 8K82K / 11S861-01. Mass: 37,125 kg (81,846 lb). Perigee: 35,777 km (22,230 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Launch delayed from April 4. PAS 10 (PanAmSat 10) was an American geosynchronous communications spacecraft. The 3.7 tonne (with fuel) satellite carried 48 transponders (24 in C-band and 24 in Ku-band) to provide direct-to-home video channels to Europe, Middle-East, and South Africa after parking over 68.5 deg-E longitude. PAS 10 replaced PAS 4. As of 5 September 2001 located at 68.50 deg E drifting at 0.001 deg E per day. As of 2007 Mar 9 located at 68.45E drifting at 0.002W degrees per day.
- 2002 December 5 - TDRS 10 - Program: STS. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIA. Mass: 3,190 kg (7,030 lb). Perigee: 35,765 km (22,223 mi). Apogee: 35,804 km (22,247 mi). Inclination: 7.00 deg. Period: 1,436.00 min.
Delayed from October 29, November 21 and 23. The third and final Advanced Tracking and Data Relay Satellite satellite separated from the Centaur upper stage 30 minutes after launch. This completed the $800 million, three satellite contract. Last launch of the Atlas 2A booster. Flight delayed from October 29, November 21 and 23. As of 2007 Mar 10 located at 40.92W drifting at 0.012E degrees per day.
- 2002 March 8 - TDRS 9 - Program: STS. Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIA. Mass: 3,192 kg (7,037 lb). Perigee: 35,758 km (22,218 mi). Apogee: 35,811 km (22,251 mi). Inclination: 8.30 deg. Period: 1,436.00 min.
Launch delayed from October 31, November 13 and 26, 2001 and February 6 due to contract dispute with Boeing over performance of earlier satellites of the series. The Centaur upper stage entered a 167 x 578 km parking orbit and then placed the payload into a 247 x 29135 km x 27.1 deg subsynchronous transfer orbit. NASA's TDRS-I (TDRS-9) data relay satellite used a Boeing BSS-601 bus and was to provide S, Ku and Ka band communications for the Shuttle and International Space Station. After launch a problem developed with the fuel supply from one of the satellite's four propellant tanks. The tanks were paired, so losing one tank cuts the propellant supply in half. A test burn of the General Dynamics R-4D apogee motor raised the orbit to 433 x 29146 km x 26.4 deg on March 11 and a larger perigee burn raised the apogee to geostationary altitude, 429 x 35800 km, on March 13. A further burn on March 19, raised the orbit to 3521 x 35789 km and lowered the inclination to 21.4 deg. A burn on March 25 raised the orbit further to 8383 x 35811 km and lowered inclination to 17.4 deg. As of 2007 Mar 11 located at 62.04W drifting at 0.008W degrees per day.
- 2003 April 12 - AsiaSat 4 - Launch Site: Cape Canaveral. Launch Vehicle: Atlas IIIB. Mass: 4,042 kg (8,911 lb). 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 October 1 - Horizons 1 (Galaxy 13) - Launch Site: Kiritimati. Launch Vehicle: Zenit-3SL. Mass: 4,060 kg (8,950 lb). Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min.
Delayed from late 2002, September 27 2003. The satellite carried both C-band and Ku-band communications payloads. The C-band payload was referred to as Galaxy 13; the Ku-band payload was jointly owned by Panamsat and the Japanese JSAT company and was called Horizons-1. Horizons-1 was to provide digital data services between the Americas and Asia via a relay station in Hawaii. As of 2007 Mar 11 located at 127.00W drifting at 0.002E degrees per day.
- 2006 December 11 - Measat 3 - Program: Measat. Launch Site: Baikonur. Launch Vehicle: Proton 8K82M. Mass: 4,900 kg (10,800 lb). Perigee: 35,782 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Malaysian communications satellite, to be stationed at 91.5° East together with Measat 1, covering South Asia, Malaysia and Indonesia, and supplementing Measats 1 and 2 launched ten years earlier. The Proton booster released the satellite in a 416 x 35807 x 49.1 deg geosynchronous transfer orbit. The Boeing 601HP 3 axis stabilized spacecraft, had a design lifetime of 15 years. C-band 24 active transponders using 65-watt TWTAs; Ku-band 24 active transponders using 120-watt TWTAs . End of life power of 9.8 kW provided by two solar wings, each with 4 panels of triple-junction gallium arsenide solar cells. A 445N liquid apogee motor circularised the spacecraft in geosynchronous orbit, and 12 x 10 N bipropellant thrusters provided stabilization and stationkeeping. Length in orbit with solar panels deployed 26.2 m; width, with antennas deployed, 7.7 m; stowed diameter 3.8 m. Mass in geostationary orbit after apogee motor maneuver at beginning of life 3220 kg. As of 2007 Mar 11 located at 91.49E drifting at 0.012W degrees per day.
- 2006 May 24 - GOES-13 - Launch Site: Cape Canaveral. Launch Vehicle: Delta IV Medium. Mass: 3,199 kg (7,052 lb). Perigee: 35,779 km (22,231 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.50 deg. Period: 1,436.00 min.
GOES-13 carried weather imager and sounder instruments, a space environment monitor, and a soft X-ray solar imaging telescope. Mass was 1543 kg empty. It joined GOES 10 (operating as GOES-WEST),
GOES 12 (operating as GOES-EAST) and GOES 11 (on standby, set to replace GOES-10 on June 27). As of 2007 Mar 11 located at 105.26W drifting at 0.008W degrees per day.
Bibliography and Further Reading - Vladimirov, A, Novosti kosmonavtiki, "Tablitsa zapuskov RN 'Proton' i 'Proton K'", 1998, Issue 10, page 25.
- Kaesmann, Ferdinand, et. al., Journal of the British Interplanetary Society, "Proton - Development of A Russian Launch Vehicle", 1998, Volume 51, page 3.
- McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Essential internet newsletter recording worldwide weekly space events. Accessed at: http://www.planet4589.org/jsr.html.
- 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.
|