Orbital Antares - Manual

Overview
Designed to provide responsive, low-cost, and reliable access to space, Antares is a two-stage
vehicle (with optional third stage) that provides low-Earth orbit (LEO) launch capability for payloads
weighing over 5,000 kg. Internally funded by Orbital, Antares completed a risk reduction mission and a
demonstration of commercial re-supply services for the International Space Station (ISS) under a NASA
Commercial Orbital Transportation Services (COTS) agreement in 2013. Antares currently is under
contract for eight Commercial Resupply Missions (CRS) to deliver cargo to the International Space
Station, the first of which was completed in early 2014. The Antares launch system utilizes Orbital's
proven MACH avionics system and many management approaches, engineering standards, production
and test processes common to Orbital’s family of highly successful small-class Pegasus
® , Taurus ® ,
and Minotaur launch vehicles. These proven launch technologies, along with hardware from one of the
world’s leading launch vehicle integrators, combine to provide cost-effective access to a variety of orbits
for civil, commercial and military medium-class payloads.
Design, manufacturing and testing of Antares is taking place in Dulles, Virginia and Chandler, Arizona.
Key Features
Medium-class space launch vehicle
utilizes proven systems from other
Orbital product lines and Zenit heritage
Over 5,000 kg to low-Earth orbit
Designed to achieve a 95% or greater
launch reliability
Mission Partners
Orbital Sciences Corporation
Prime integrator, systems engineering,
avionics, primary structure, testing and
software. Overall Stage 1 development
and integration.
KB Yuzhnoye/Yuzhmash
Stage 1 core design, production
and verification
Aerojet (Rocketdyne)
Stage 1 engines
ATK
Stage 2 motor
FACTS AT A GLANCE
Antares
™
Medium-Class Space Launch Vehicle
Medium Class
• Incorporates both solid and liquid stages and
flight-proven technologies to meet medium-
class mission requirements
• Provides substantial payload performance
into a variety of low inclination low-Earth and
sun-synchronous orbits and interplanetary
trajectories
• Streamlined vehicle/payload integration and
testing via simplified interfaces reduce time from
encapsulation to lift-off
• 3.9 meter fairing accommodates large payloads
• Capable of launching single and multiple
payloads
• Initial launch successfully conducted April 21,
2013 from Wallops Flight Facility (WFF), Virginia
• Also compatible with the Western Range at
Vandenberg Air Force Base (VAFB),
Eastern Range at Cape Canaveral Air Force
Station (CCAFS) and the Kodiak Launch
Complex (KLC)
LAUNCH
VEHICLE