Orbital LEOStar-2 Bus - Manual (Page 4)

Orbital Sciences Corporation
45101 Warp Drive • Dulles, Virginia 20166 • www.orbital.com
©2014 Orbital Sciences Corporation FS006_06_2998
LEOStar
™
-2 Bus
Spacecraft Features
Spacecraft Mass: 150 kg to 500 kg (with propellant)
Launch Vehicle Pegasus ® XL, Taurus ® , Minotaur, Delta II and
Compatibility: Falcon
Design Life:
Up to 5 years
Orbit Options: LEO: 450-1,000 km altitude, 5 ° -110 °
inclination. Adaptable to HEO, GEO and
deep space.
Geolocation: <12 m @ 90% Circular Error, post processing
(optional)
Operations: Simultaneous data acquisition by payload(s)
and data transmission capability
Onboard Data Scalable to 1,600 Gbit in data recorder and
Storage Capability: 32 Gbit in flight computer
Delivery:
30-36 months after receipt of order
Attitude Control Subsystem
ADCS Approach:
S-band at 2 mbps, optional X-band at 15
mbps
Pointing Accuracy: <15 arcsec/axis available (3 σ)
Pointing Knowledge: <6 arcsec/axis available (3 σ)
Pointing Stability: <1 arcsec per second
Agility: Slew rate up to 1 ° /sec per axis (standard),
Slew rate >3 ° /sec per axis (optional)
Propulsion: Blowdown monopropellant hydrazine; up to
140 kg propellant (optional)
Communications
Payload Data
Downlink:
2 Mbps S-band (standard), up to 150 Mbps
X-band (optional)
Command Uplink: 2 Kbps S-band (standard), up to 128 Kbps
(optional)
Payload Accomodation
External Volume:
Up to 1.388 m3 in Pegasus XL
Maximum Payload 210 kg (463 lb.) (standard), up to 550 kg
Mass:
(1,213 lb.) (optional)
Maximum Payload 118 W orbit average (standard), up to 2 kW
Power: (optional)
Interface
Architecture:
RS-422/RS-485, LVDS, MIL-STD-1553
For more information, please contact:
[email protected]
(703) 406-5000
Aeronomy of Ice in the Mesosphere (AIM) satellite
SORCE solar irradiance monitoring satellite
Galaxy Evolution Explorer (GALEX) satellite