Owner manual

Orbital Sciences Corporation
45101 Warp Drive
•
Dulles, Virginia 20166
•
www.orbital.com
©2014 Orbital Sciences Corporation FS010_11_3316
LEOStar
™
-3 Bus
Spacecraft Features
Spacecraft Mass: 1,169 kg (typical)
Propellant Load: 353 kg (typical)
Launch Vehicle
Compatibility: Minotaur IV, Antares, Delta II, Delta IV, Falcon 9, Atlas V
Design Life: 7-10 years
Orbit Options: LEO, interplanetary
Total Radiation
Dose: 25 krad
Delivery of
Spacecraft Bus
Months after
Authorization
to Proceed (ATP): 21-36 months
Total Schedule,
Integrated Satellite
Months from ATP
to Launch: 36-48 months
Attitude Control Subsystem
Stabilization: 3-axis
Pointing Control: 120 arcsec, 1σ
Pointing Knowledge: <5 arcsec
Timing Accuracy: 40
µs
Orbit Knowledge: 33 m, 1σ
Max Maneuver Rate: 0.125
°
/sec
Propulsion: Blowdown monopropellant hydrazine
Communications
Payload Data
Downlink: 2 Mbps S-band (standard), up to 740 Mbps X-band
(optional), 320 Mbps Ka-band
Command Uplink: S-band
Space-to-Space
Mission Data: Optional Laser (LCT)
Payload Accomodation
Instrument Mass: up to 4,000 kg
Instrument Orbit
Average Power: 775 W
Onboard Instrument
Data Storage: 160 Gb
• Onboard solid state mission data
storage available to 3100 Gb
• Mission wide band data downlink on
X or Ku-band; rates to 740 Mbps
• Commercial uplink command
encryption available
• Precision attitude knowledge, control,
and jitter performance
• Highly agile Earth and space pointing;
slew rates to 3
°
/sec
• Extremely low EM emissions to
accommodate sensitive instruments
• Various thermal control options,
including instrument isolation
• Propulsion sizing and propellant
capacity options, including none
• Conguration options support other
orbits and special missions
• On-orbit operations using Orbital's
Mission Operations Centers
FACTS AT A GLANCE
LEOStar-3 Structure
Payload Flexure
Interface and GN&C
Optical Bench, Nominal
Instrument Volume:
1.8 x 1.8 x 1.4 m
Primary
and
Secondary
Structure
Frame Assembly
Propulsion Subsystem
Structure
Launch Vehicle
Adapter