N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 163,000/8,000 kg. Thrust 2,428.31 kN. Vacuum specific impulse 302 seconds.
Cost $ : 13.000 million. No Engines: 2.
Status: Retired 2005.
Gross mass: 163,000 kg (359,000 lb).
Unfuelled mass: 8,000 kg (17,600 lb).
Height: 26.37 m (86.51 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 2,428.31 kN (545,906 lbf).
Specific impulse: 302 s.
Specific impulse sea level: 250 s.
Burn time: 164 s.
Number: 57 .
More... - Chronology...
Associated Countries
Associated Engines
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LR87-11 Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964. More...
Associated Launch Vehicles
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Titan 405A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit SDS and NOSS-2 payloads from Cape Canaveral. More...
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Titan 403A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit Lacrosse, SDS and NOSS-2 payloads from Vandenberg. More...
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Titan 404A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of heavy-weight, low altitude KH-12 and Improved CRYSTAL payloads from Vandenberg. More...
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Titan 404B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. More...
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Titan 403B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. More...
Associated Propellants
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N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...
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