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Leostar, 3 bus, Facts at a glance – Orbital LEOStar-3 Bus User Manual

Page 4: Spacecraft features

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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, 1

σ

Pointing Knowledge:

<5 arcsec

Timing Accuracy:

40 µs

Orbit Knowledge:

33 m, 1

σ

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

• Configuration 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