3-axis stabilised. Hydrazine propulsion system. Two large solar panels with 1-axis articulation provide 3900W BOL. 26 C-Band / 10-14 Ku-Band transponders.18,000 telephone calls and 3 colour TV broadcasts simultaneously. Or up to 112,500 telephone circuits using digital circuit multiplication equipment (DCME).7A: 26 C-Band and 14 Ku-Band transponders.22,500 telephone calls and 3 colour TV broadcasts simultaneously. Three independently steerable, high-powered, Ku-band spot beams. Independently steerable C-band spot beam coverage.
Design Life: 10-15 years. Total Mass: 4,180 kg.
Japanese domestic business communications; 158 deg E.
Launched with BS-2X. Targeted for Geosynch orbit.
Stationed at 162 deg E. Domestic communications. Launching organization Arianespace. Launch time 2358 GMT.
Stationed at 158 deg E. Domestic communications. Launching states: Japan and France. Launch time 2248 GMT.
International communications. The Intelsat 7 and 7A series were nearly identical except for an increase in the number of Ku-band transponders in the 7A series. Spacecraft: 3-axis stabilised. Hydrazine propulsion system. Two large solar panels with 1-axis articulation provide 3900W BOL. Payload: 7: 26 C-Band and 10 Ku-Band transponders.18,000 telephone calls and 3 colour TV broadcasts simultaneously. Or up to 90,000 telephone circuits using digital circuit multiplication equipment (DCME).7A: 26 C-Band and 14 Ku-Band transponders.22,500 telephone calls and 3 colour TV broadcasts simultaneously. Or up to 112,500 telephone circuits using DCME. Three independently steerable, high-powered, Ku-band spot beams. Independently steerable C-band spot beam coverage.
50 cm cube; Space Technology and Research Vehicle; included solar cell tests.
Stationed at 176.96 deg E. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option.
Stationed at 66.0 deg E. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option.
Stationed at 50.1 deg W. Launch vehicle put payload into supersynchronous earth orbit with MRS trajectory option.
Stationed at 53.1 deg W.
Stationed at 131.9 deg E.
Geostationary at 128.9E.
GEO. 26 C-band, 14 K-band transponders. Geostationary at 0.9W.
36 transponders Geostationary at 50.0W.
Geosynchronous. Stationed over 118.7W Launch vehicle put payload into subsynchronous earth orbit with MRS trajectory option.
Geosynchronous. Stationed over 97.0W
Geosynchronous. Stationed over 43.2W
Geosynchronous. Stationed over 146.0E
Geosynchronous. Stationed over 76.5E
Geostationary at 68.7 degrees E.
The Proton launch vehicles Block DM3 fourth stage put the Panamsat PAS 8 into a 6784 km x 35941 km x 17.3 degree transfer orbit. PAS 8 had 24 C-band and 24 Ku-band transponders and was to be located over the Pacific after its R-4D apogee engine manoeuvred the orbit to geostationary altitude and inclination. Geostationary at 166.1 degrees E.
Loral Skynet's Telstar 6 had a mixed C and Ku band communications payload. The Block DM3 upper stage released Telstar 6 in a 6638 km x 35,756 km x 17.4 degree geosynchronous transfer orbit. After the first burn of its on-board R-4D engine on February 18, Telstar 6 was in a 15,037 km x 35,800 km x 7.9 deg transfer orbit heading for its final geosynchronous slot at 93 deg W
The Centaur second stage put Echostar 5 into a supersynchronous transfer orbit of 131 km x 45526 km x 26.6 degrees. The satellite's own engine put it into the final geosynchronous orbit. Echostar 5 was a Ku-band satellite, part of the Dish Network. Stationed at 110 deg W.
Telstar 7, owned by Loral Skynet, had 24 C-band and 24 Ku-band transponders. Dry mass was 1537 kg. After placement in final geosynchronous orbit it provided communications for North America from a position at 129 degrees East longitude. Stationed at 129 deg W.
Satellite used for international communications; complement the Telstar satellites operated by Loral Skynet. Stationed at 15 deg W.
Multi-functional Transportation Satellite intended to provide communications and air traffic control for the Japanese transportation ministry and a meteorological data for the Japanese Meteorological Agency. The spacecraft had a mass of 1223 kg dry and was a follow-on to the GMS (Himawari) weather satellite series.
US civilian geostationary weather satellite in the Geostationary Operational Environmental Satellite series. It was the first GOES launch on the Atlas II launch vehicle (the Atlas I having been phased out). Built by SS/Loral, based on the FS-1300 bus. It was equipped with one solar panel array and a counter-boom with a solar sail. The satellite carried well as an imaging radiometer and an X-ray detector to monitor solar activity. Stationed at 106 deg W.
Digital Audio Radio Satellite, used for transmission of S-band radio broadcasts direct to receivers in cars in the United States. Sirius 1 was inserted into an initial 6,166 x 47110 km x 63.4 deg transfer orbit by the Proton-K's Blok DM3 upper stage. The satellite's R4D liquid apogee engine made several burns to raise the orbit to 24,388 x 47,097 km x 63.3 deg by July 8. This elliptical, inclined 24 hour orbit had a 24 hour period, designed to keep the satellite between longitude 60W and 140W, with apogee over the northern hemisphere. Stationed at 66 deg W.
Sirius Radio's Sirius 2 was launched into a 144 x 168 km x 64.8 deg parking orbit. The Blok DM3 stage then made two burns to deliver Sirius 2 to an elliptical 6192 x 47057 km x 63.4 deg orbit. The was to provide digital radio broadcasts to mobile users in North America. Stationed at 64 deg W.