American orbital launch vehicle. Orbital version. Selected by NASA under the COTS program in January 2008 in place of the cancelled Kistler for post-shuttle ISS resupply missions. Uses half-length shuttle SRB as first stage; proven Castor-120 as second stage; new Castor-30 as third stage; and Oribtal Adjusment Module from Lockheed's cancelled Athena launcher as a fourth stage.
LEO Payload: 6,000 kg (13,200 lb) to a 350 km orbit at 51.60 degrees. Payload: 2,800 kg (6,100 lb) to a GTO.
AKA: Athena III; Satellite Launch Vehicle.
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Payload: 6,000 kg (13,200 lb).
Apogee: 350 km (210 mi).
ALV Family of small low-cost all-solid-propellant launch vehicles, which use numerous off-the-shelf components and require minimal ground support More...
Associated Manufacturers and Agencies
Castor 30 Solid propellant rocket stage developed for use on space launch vehicles. More...
OAM Hydrazine propellant rocket stage. Loaded/empty mass 714/360 kg. Thrust 0.88 kN. Vacuum specific impulse 222 seconds. Monopropellant final stage providing precise orbital injection. Pressure-fed, indefinite number of restarts. More...
Shuttle RSRM Solid propellant rocket stage. Loaded/empty mass 590,000/88,000 kg. Thrust 11,520.00 kN. Vacuum specific impulse 267 seconds. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. More...
SR118 Solid propellant rocket stage. Loaded/empty mass 53,020/4,211 kg. Thrust 1,606.59 kN. Vacuum specific impulse 286 seconds. Modification of Peackeeper ICBM first stage. More...
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