Intelsat 29e
| Names | IS-29e |
|---|---|
| Mission type | Communication |
| Operator | Intelsat |
| COSPAR ID | 2016-004A |
| SATCAT no. | 41308 |
| Website | Intelsat IS-29e |
| Spacecraft properties | |
| Spacecraft | IS-29e |
| Bus | Boeing 702MP |
| Manufacturer | Boeing |
| Launch mass | 6,552 kg (14,445 lb) |
| Dimensions | 7.5 by 3 by 2 metres (24.6 ft × 9.8 ft × 6.6 ft) |
| Power | 15.8 kW |
| Start of mission | |
| Launch date | 23:20, January 27, 2016 |
| Rocket | Ariane 5 ECA VA-228 |
| Launch site | GSC ELA-3 |
| Contractor | Arianespace |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Geosynchronous |
| Longitude | 50° West |
| Semi-major axis | 42,241.0 kilometres (26,247.3 mi) |
| Perigee | 35,864.3 kilometres (22,285.0 mi) |
| Apogee | 35,875.9 kilometres (22,292.3 mi) |
| Inclination | 0.0° |
| Period | 1,440 minutes |
| Transponders | |
| Band |
High throughput C band: 20 Ku band: 56 Ka band: 1 |
| Bandwidth |
C band: 864 MHz Ku band: 9,395 MHz Ka band: 450 MHz |
| Coverage area | CONUS, Latin America and North America |
|
|
|
Intelsat 29e, also known as IS-29e is a high throughput geostationary communications satellite designed and manufactured by Boeing on the BSS-702MP platform. It is the first satellite of the EpicNG service, and covers CONUS, Latin America and North America from the 50° West longitude, where it is replaced Intelsat 1R. It also replaced Intelsat 805 which was moved from 56.5° West to 169° East. It has a mixed C band, Ku band and Ka band payload with all bands featuring wide and the Ku also featuring spot beams.
The spacecraft was designed and manufactured by Boeing on the Boeing 702MP satellite bus. It has a launch mass of 6,552 kg (14,445 lb) and a design life of more than 15 years. When stowed for launch, the satellite measures 7.5 by 3 by 2 metres (24.6 ft × 9.8 ft × 6.6 ft).
It is powered by two wings, with four panels each, of triple-junction GsAs solar cells, that span 44 metres (144 ft) when deployed. Intelsat 29e can generate 15.8 Kw at the end of its expected life and has four Li-ion batteries.
This three axis stabilized platform has a bi-propellant propulsion system using NTO/N2O4. It has a 449 N (101 lbf) Liquid Apogee Engine for orbit raising and 22 N (4.9 lbf) and 4 N (0.90 lbf) thrusters for station keeping. The propellant tanks hold approximately 1,550 kg (3,420 lb) of N2O4 and 2,000 kg (4,400 lb) of NTO. This new series of geosynchronous satellites lack an Earth Sensor, and thus enter Earth pointing attitude based on the orbital position as determined by the star tracker.
...
Wikipedia