Mission type | Communications |
---|---|
Operator | Intelsat |
COSPAR ID | 1967-094A [1] |
SATCAT no. | 2969 [1] |
Mission duration | 3 years planned 3+1⁄2 years achieved |
Spacecraft properties | |
Spacecraft type | Intelsat II |
Bus | HS-303A |
Manufacturer | Hughes |
Launch mass | 162 kilograms (357 lb) |
BOL mass | 86 kilograms (190 lb) |
Power | 85 watts |
Start of mission | |
Launch date | September 28, 1967, 00:45:00 UTC [2] |
Rocket | Delta E1 |
Launch site | Cape Canaveral LC-17B |
Contractor | NASA |
End of mission | |
Deactivated | c. 1971 |
Orbital parameters | |
Reference system | Geocentric |
Regime | Geosynchronous |
Longitude | 176° east (1967-70) 166° west (1971) |
Perigee altitude | 35,742 kilometers (22,209 mi) |
Apogee altitude | 35,886 kilometers (22,299 mi) |
Inclination | 6.00 degrees |
Period | 23.95 hours |
Epoch | February 8, 2014, 07:56:55 UTC [3] |
Intelsat II F-4 was a communications satellite operated by Intelsat. Launched in 1967 it was operated in geostationary orbit at a longitude of 176 degrees east and later 166 degrees west. [4]
The fourth and last Intelsat II satellite to be launched, Intelsat II F-4 was built by Hughes Aircraft around the HS-303A satellite bus. It carried two transponders, which were powered by body-mounted solar cells generating 85 watts of power. [5] The spacecraft had a mass of 162 kilograms (357 lb) at launch, decreasing through expenditure of propellant to 86 kilograms (190 lb) by the beginning of its operational life.
Intelsat II F-4 was launched atop a Delta E1 rocket flying from Launch Complex 17B at the Cape Canaveral Air Force Station. The launch took place at 00:45:00 UTC on September 28, 1967, with the spacecraft entering a geosynchronous transfer orbit. [2] It fired an SVM-1 apogee motor to place itself into its operational geostationary orbit. The spacecraft was operated at a longitude of 176° east until 1970, before being moved to 166° west. In total the satellite remained in service for around three and a half years. [4]
As of February 8, 2014 the derelict Intelsat II F-4 was in an orbit with a perigee of 35,742 kilometers (22,209 mi), an apogee of 35,886 kilometers (22,299 mi), inclination of 6.00 degrees and an orbital period of 23.95 hours. [3]
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