Intelsat II F-4
| Mission type | Communications |
|---|---|
| Operator | Intelsat |
| COSPAR ID | 1967-094A[1] |
| SATCAT № | 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 | 35,742 kilometers (22,209 mi) |
| Apogee | 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]
References
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- ↑ 2.0 2.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 3.0 3.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 4.0 4.1 Lua error in package.lua at line 80: module 'strict' not found.
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