Orbital LEOStar-2 User Manual

LEOStar™-2 Bus
An affordable, versatile, small-to-medium size spacecraft bus suitable for SMEX, MIDEX, ESSP, and Discovery class missions. Compatible with launch vehicles such as Pegasus®, Minotaur, and Delta.
LEO
Satellite Bus
Orbital’s LEOStar-2 series of spacecraft have supported multiple missions for commercial and
government customers over the past ten years. The current LEOStar-2 product line has an enviable
on-orbit performance record with four on-orbit and three more in production.
FACTS AT A GLANCE
There are eight LEOStar-2 spacecraft
delivered to customers with three
currently in design and production.
Design
Originally designed for the Pegasus XL launch vehicle, Orbital’s LEOStar-2 spacecraft bus provides a
exible, high performance platform for space and earth scientic, remote sensing, and other commercial
applications on a variety of launch vehicles (Pegasus, Minotaur and Delta). The avionics architecture has
been congured for both single-string and redundant applications, supporting missions with durations
up to ten years. LEOStar-2 can accommodate various instrument interfaces, deliver up to 2 kW orbit
average payload power, and support payloads up to 500 kg. Performance options include redundancy,
propulsion capability, high data rate communications, and high-agility/high-accuracy pointing.
Payload Accomodations
The exible LEOStar-2 spacecraft bus has been adapted to a variety of space science, remote sensing,
and technology validation missions. The spacecraft employs a compact avionics suite housed within a
hexagonal bus platform, enabling Orbital to deliver a signicant launch vehicle fairing volume for multiple
instruments. Our modular approach to the spacecraft platform and instrument deck enables parallel
integration and testing, reducing overall delivery schedule. With the LEOStar-2, Orbital has regularly
delivered attitude control better than 15 arc-seconds, with attitude knowledge less than 6 arc-seconds.
Through the inclusion of higher performance actuators, we can achieve greatly improved agility.
LEOStar-2 "Firsts"
• The Dawn planetary spacecraft is
the rst operational application of
electric Ion propulsion, the rst to orbit
a body in the asteroid belt, and the
planetary bodies.
• The GALEX satellite performed the
rst ultraviolet all-sky survey covering
approximately 1 million galaxies.
• The NuSTAR satellite's X-ray
instrument produces images 100
times the sensitivity and 10 times
the resolution of previous X-ray
observatories.
Dulles, Virginia SMF Gilbert, Arizona SMF
LEOStar™-2 Bus
Mission Services
Customers can procure the LEOStar-2 spacecraft bus alone
or as part of a “turn-key” service that includes mission design,
instrument/payload integration, satellite environmental test, launch
services, early orbit checkout, and mission operations, including
instrument data delivery to principal investigators. Orbital has the
end-to-end capability to build, integrate, test, launch and operate
missions.
Production Approach
Using mature designs, proven assembly procedures, and
established vendor sources, the LEOStar-2 bus can be developed
well within 36 months after receipt of order.
Heritage
Currently, Orbital has four LEOStar based satellites on-orbit
and has three in production. First developed for the GeoEye,
OrbView-3, and OrbView-4 commercial high-resolution imagery
system, the LEOStar-2 spacecraft has own in a redundant
conguration for NASA’s SORCE mission, in a selectively
redundant conguration for NASA’s GALEX mission, and in a
single-string conguration for NASA's AIM and NuSTAR missions.
Currently LEOStar-2 programs include the OCO-2, TESS and
ICON spacecraft. Science applications include atmospheric
monitoring, solar irradiance monitoring, and astronomical
exploration. With appropriate modication, we have also adapted
this bus for JPL’s Dawn interplanetary mission, currently en route
to the asteroid Ceres.
The Orbiting Carbon Observatory-2 (OCO-2) spacecraft in Orbital's Gilbert, Arizona satellite manufacturing facility.
Options
• Avionics components, actuators, or sensors to improve system
capability and increase mission reliability and lifetime
• Expanded on-board solid state memory and X-band downlink for
increased payload data storage and high rate data transfer
• Hydrazine propulsion capability to enable orbit maneuvers and
increase mission lifetime
• Spacecraft operations and data delivery
Additional Features
• Modular Design – Flexibility in design (ACS sensor and actuator
selection, payload unique data services), assembly, integration
and testing
• Low Cost with High Experience – As a world leader in developing
and manufacturing affordable mission solutions, Orbital can
deliver highly capable ight systems under tight cost and
schedule constraints
The NuSTAR satellite in Orbital's Dulles, Virginia satellite manufacturing facility.
LEOSTAR-2 PROGRAMS
ICON
Mission: Space Weather Launch: 2017, Pegasus Status: In design
TESS
Mission: Exoplanet Exploration Launch: 2017, TBD Status: In design
Orbiting Carbon Observatory-2 (OCO-2)
Mission: Atmospheric Monitoring Launch: 2014, Delta II Status: At launch site
Nuclear Spectroscopic Telescope Array (NuSTAR)
Mission: X-ray Detection of Black Holes Launch: 2012, Pegasus XL Status: Operational
Glory
Mission: Atmospheric and Solar Irradiance Monitoring Launch: 2011, Taurus XL Status: Lost due to LV failure
Orbiting Carbon Observatory (OCO)
Mission: Atmospheric Monitoring Launch: 2009, Taurus XL Status: Lost due to LV failure
Aeronomy of Ice in the Mesosphere (AIM)
Mission: Atmospheric Monitoring Launch: 2007, Pegasus XL Status: Baseline mission complete, currently in extended operations
OrbView-3
Mission: Remote Sensing Launch: 2003, Pegasus XL Status: Spacecraft de-orbited after image sensor failure
Galaxy Evolution Explorer (GALEX)
Mission: Astronomical Exploration Launch: 2003, Pegasus XL Status: Mission complete
Solar Radiation and Climate Experiment (SORCE)
Mission: Solar Irradiance Measurement
Launch: 2003, Pegasus XL Status: Baseline mission complete, currently in extended operations
and Monitoring
OrbView-4
Mission: Remote Sensing Launch: 2001, Taurus Status: Lost due to LV failure
LEOStar™-2 Bus
Spacecraft Features
Spacecraft Mass: 150 kg to 500 kg (with propellant)
Launch Vehicle Pegasus
Compatibility: Falcon
Design Life: Up to 5 years
Orbit Options: LEO: 450-1,000 km altitude, 5
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 (3σ)
Pointing Knowledge: <6 arcsec/axis available (3σ)
Pointing Stability: <1 arcsec per second
Agility: Slew rate up to 1
Slew rate >3
Propulsion: Blowdown monopropellant hydrazine; up to
140 kg propellant (optional)
®
XL, Taurus®, Minotaur, Delta II and
°
-110°
°
/sec per axis (standard),
°
/sec per axis (optional)
Galaxy Evolution Explorer (GALEX) satellite
SORCE solar irradiance monitoring satellite
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
Orbital Sciences Corporation
45101 Warp Drive
Dulles, Virginia 20166
www.orbital.com
Aeronomy of Ice in the Mesosphere (AIM) satellite
For more information, please contact:
science@orbital.com (703) 406-5000
©2014 Orbital Sciences Corporation FS006_06_ 2998
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