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.
No Engines: 4.
Status: Out of production.
More... - Chronology...
Gross mass: 714 kg (1,574 lb).
Unfuelled mass: 360 kg (790 lb).
Height: 1.00 m (3.20 ft).
Diameter: 2.30 m (7.50 ft).
Span: 2.30 m (7.50 ft).
Thrust: 882 N (198 lbf).
Specific impulse: 222 s.
Burn time: 1,500 s.
Number: 10 .
MR-107 Redmond hydrazine monopropellant rocket engine. 0.257 kN. Spacecraft and upper stage attitude control and dV corrections, Delta 2, Titan 2, PAM D, SICBM, HAS/Peace Courage, Atlas roll control module, STEP, Pegasus. Isp=236s. First flight 1990. More...
Associated Launch Vehicles
Athena-3 American all-solid orbital launch vehicle. Planned but never flown heavier-lift version of Athena. More...
Athena-1 American all-solid orbital launch vehicle. Basic version of the Athena with a Castor 120 first stage, Orbus second stage, and OAM Orbital Adjustment Module. More...
Athena-2 American all-solid orbital launch vehicle. The Athena-2 version featured a Castor 120 first stage, Castor 120 second stage, Orbus third stage, and OAM Orbital Adjustment Module. More...
Satellite Launch Vehicle 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. More...
Hydrazine Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. More...
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