Technical Specifications
Note: The following
information is provided for information only. If you are interested in procuring a
satellite or satellite bus, we recommend that you contact the manufacturer directly using
the information above.
| StarBus
Satellite Platform * |
CORE BUS FEATURES |
| Dry Mass |
1,230 lb
558 kg |
| Payload Mass Capability |
441 lb
200 kg |
| Redundancy |
full dual string |
| Orbit |
Geosynchronous |
| Typical Mission Lifetime |
10 years with Ps>0.86 |
| Delivery |
30 months from ARO |
| Launch Vehicle |
Delta II, Ariane, Proton, Long
March |
STRUCTURE |
| Bus Dimensions (H x W x L) |
68.9 in x 66.9 in
x 70.9 in
1.75 m x 1.7 m x 1.8 m |
| Payload Support Dimensions |
39.4 in x 39.4 in
x 47.2 in
1.0 m x 1.0 m x 1.2 m |
| Construction |
composite / aluminum |
POWER SYSTEM |
| Payload Power |
555 W orbit avarage over 10
years |
| Bus Voltage |
24-36 VDC (nominal) |
| Solar Arrays |
4 panel silicon, 2 solar
tracking wings |
| Batteries |
2x 52 AmpHr, NiH2 |
ATTITUDE CONTROL SYSTEM |
| Stability Mode |
3 axis momentum bias,
nadir oriented |
Pointing Capabilities
Control
Knowledge
Rate / Stability |
± 0.2 deg. (R/P)
< 0.1 deg. (R/P)
< 0.001 deg. / sec |
COMMAND & DATA HANDLING SYSTEM |
| Flight Processor |
MIL-STD-1750A |
| Rad Tolerant |
100 K rad |
| Interface Architecture |
MIL-STD 1553B, CCSDS |
| S-Band Uplink Rate |
2 Kbps |
| S-Band Downlink Rate |
1 Mbps |
* Note: All values from Orbital Sciences
|
