|
Satellite
Main Technical Specifications |
|
Satellite: |
Nilesat 101 |
Nilesat 102 |
|
Launch Information |
|
Launch Date |
28 April 1998 |
17 August 2000 |
|
Launch Vehicle |
Arian 4 |
Arian 4 |
|
Launch Mass |
1840 Kg |
1825 Kg |
|
Orbital Information |
|
Satellite
Manufacturer |
MATRA MARCONI SPACE |
ASTRIUM |
|
Orbital
Position |
7° West |
7° West |
|
Stabilization
System |
3-Axis |
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 |
15 Years |
|
Payload Information |
|
EIRP (Max.) |
50.1 dBW |
50.1 dBW |
|
G/T (Max.) |
1.5 dB/K |
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 |
12 |
|
Transponder
Bandwidth |
33 MHz |
33 MHz |
|
Transponder
Output Power |
100 W |
100 W |
|
TWTA Redundancy |
16 for 12 |
16 for 12 |
|
Polarization |
Linear |
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 ** |
50 cm to 75 cm ** |
|
Operation
Start Date |
31 May 1998 |
12 September 2000 |