| PegaStar Satellite Platform * |
CORE BUS FEATURES |
| Dry Mass |
298.6 lb
135.4 kg |
| Payload Mass Capability |
1,256 lb (max)
570 kg (max) |
| Redundancy |
partial
(0.89 reliability @ 1 year) |
| Orbit |
400 - 2500 km
all inclinations |
| Typical Mission Lifetime |
3 -5 years |
| Delivery |
36 months from ARO |
| Launch Vehicle |
Pegasus, Taurus |
STRUCTURE |
| Bus Dimensions (H x W x L) |
38.2 in (dia)
x 39.8 in (hexagonal)
0.97 m (dia) x 1.01 m (hexagonal) |
| Payload Support Dimensions |
46.1
in (dia) x 48.0 in (Pegasus)
1.17 m (dia) x 1.22 m (Pegasus)53.9
in (dia) x 90.9 in (Taurus)
1.37 m (dia) x 2.31 m (Taurus) |
| Construction |
aluminum honeycomb |
POWER SYSTEM |
| Payload Power |
60 W orbit avarage |
| Bus Voltage |
28 +/- 6 VDC
(nominal) |
| Solar Arrays |
6 panel silicon |
| Batteries |
2x 10 AmpHr, NiH2 CPV's |
ATTITUDE CONTROL SYSTEM |
| Stability Mode |
momentum bias,
sun pointed |
Pointing Capabilities
Control
Knowledge
Position |
0.59
0.56
100 m |
COMMAND & DATA HANDLING SYSTEM |
| Flight Processor |
68302 |
| Rad Tolerant |
Yes |
| Data Storage Capacity |
256 MBytes |
| Interface |
MIL-STD 1553,
RS-422/RS-485, CCSDS |
| S-Band Rx/Tx Rates |
2 kbps / 2
Mbps |
| Interface |
STDN or SGLS |
OPTIONS |
| Full Redundancy |
increases
Ps above 80% at 3 years |
| Increased Power |
povides
>70 W orbit average by adding more powerful arrays and batteries |
| Articulated
Arrays |
enable
bus to support nadir oriented missions in all orbit inclinations |
| Zero Momentum
Attitude Control |
supports
pointing and slewing with 0.3 pointing |
| Enhanced IMU |
improves
attitude control and knowledge and increases reliability |
| Enhanced
Attitude Sensor |
provides
0.01 pointing knowledge by adding star tracker |
| Increased Data
Storage |
replaces
256 Mbyte Data Recorder with 16 Gbits |
| X-Band Downlink |
supports
science data rates from 2 to 150 Mbps |
| UHF Downlink |
provides
downlink telemetry to low-cost ground station at user site |
| Propulsion |
adds
68 kg of hydrazine with average specific impulse of 220 sec |
| Three Point
Launch Vehicle Interface |
enables
shared launch with Orbital MicroStar spacecraft |
