| |
NILESAT 101 |
NILESAT
102 |
| Launch
Information |
| Launch Date |
28 April 1998 |
17 August 2000 |
| Launch Vehicle |
Arian 4 |
| Launch Mass |
1840 Kg |
1827 Kg |
| Orbital
Information |
| Satellite Manufacturer |
MATRA MARCONI SPACE |
ASTRIUM
|
| Orbital Position |
7° West |
| Stabilization System |
3-Axis |
| Station Keeping Co-location Accuracy |
± 0.09° E-W &
± 0.07°
N-S |
| System Power Consumption (Max) |
3.02 kW |
3.06 kW |
| Expected Life Time |
15 Years |
| Payload
Information |
| EIRP (Max.) |
50.1 dBW |
| G/T (Max.) |
1.5 dB/K |
| Downlink Frequency Band (KU) |
11.7 - 12.1 GHz |
11.8 – 12.3 GHz |
| Uplink Frequency Band (KU) |
17.3 - 17.7 GHz |
17.4 – 17.9 GHz |
| No. of Transponders |
12 |
| Transponder Bandwidth |
33 MHz |
| Transponder Output Power |
100 W |
| TWTA Redundancy |
16 for 12 in each satellite |
| Polarization |
Linear |
|
Saturation
Flux Density (FGM) *
london
Horn |
-76
to -96 dBW/m2
|
-76
to –94 dBW/m2
-72.5
to –90.5 dBW/m2 |
| Transponder Gain Range |
15 dB ALC /
20 dB FGM |
13 dB ALC /
18 dB FGM |
| Operation
Information |
| Receiving Dish Diameter |
50 cm to 75 cm within the coverage area. |
| Operation Start Date |
31 May 1998 |
12 September 2000 |
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