Orbital GEOStar-2 Bus - Manual (Page 4)

Orbital Sciences Corporation
45101 Warp Drive • Dulles, Virginia 20166 • www.orbital.com
©2014 Orbital Sciences Corporation FS004_06_2998
Shared Launch Opportunities
Due to the size and mass envelope of the satellite, the GEOStar-2 Bus is
compatible with almost all commercially available launch vehicles, maximizing
opportunity for launch and access to space. While dedicated or single
launch services are more readily available, the GEOStar-2 Bus targets shared
launch opportunities, where launch cost and launch-sharing opportunities are
favorable.
Mission Services
Customers can purchase the GEOStar-2 Bus spacecraft bus alone, or as part
of a turn-key service that includes an integrated payload, network operations
center and launch vehicle. Orbital conducts spacecraft commissioning from its
own ground station prior to transferring spacecraft control to the customer’s
operations center.
Mission Life
The satellite is designed with conservative margin beyond 15 years, taking
into account for the severe geosynchronous radiation environment. The typical
limitation of mission duration is on-board fuel for orbit maintenance station-
keep. However, fuel life can be optimized and extended to more than 15 years,
based on launch vehicle selection.
Heritage
The GEOStar-2 Bus fills a market niche for small, high power geosynchronous
communications spacecraft. Orbital’s first application of the GEOStar-2 Bus
design, N-STAR c, was successfully launched in July 2002 on an Ariane
rocket. Since then, Orbital has launched 27 GEOStar-2 Bus spacecraft with
three in production.
Versatility
Several available options augment the basic bus to provide improved pointing,
more payload power, secure communications, higher downlink data rates or
enhanced payload computing power.
Orbital’s Dulles, Virginia satellite manufacturing facility
Specifications
Core Bus Features
Bus Dry Mass: 800-1,500 kg
Max. Launch Mass: 3,325 kg
Payload Mass Capability: 500 kg
Orbit:
Geosynchronous
Typical Mission Lifetime: >15 years
Delivery:
24 months (typical) after
receipt of order
Launch Vehicle
Compatibility:
Ariane, Soyuz, Land
Launch, Proton, H2A,
Falcon-9, Sea Launch
Structure
Bus Dimensions (HxWxL): 1.75 m x 1.7 m x 1.8 m
Construction:
Composite/Al
Power Subsystem
Payload Power: Up to 5,550 W orbit
average @ 15 years
Bus Voltage: 24-36 VDC (nominal)
Solar Arrays: Multi-junction GaAs cells
Batteries: Li-Ion
Attitude Control Subsystem
Stability Mode: 3-axis; zero momentum
Propulsion Subsystem
Transfer Orbit System: Liquid bi-propellant
On Orbit:
Monopropellant (hydrazine)
Command & Data Handling Subsystem
Flight Processor: MIL-STD-1750A
Interface Architecture: MIL-STD 1553B, CCSDS
GEOStar
™
-2 Bus
More Information
Mr. Amer Khouri
Vice President of Marketing, Global Communications
(703) 948-8600, [email protected]