Solid propellant rocket stage. Loaded/empty mass 251,427/40,827 kg. Thrust 6,227.00 kN. Vacuum specific impulse 265 seconds.
Cost $ : 19.720 million.
Status: Retired 1992.
Gross mass: 251,427 kg (554,301 lb).
Unfuelled mass: 40,827 kg (90,008 lb).
Height: 27.56 m (90.41 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 6,227.00 kN (1,399,885 lbf).
Specific impulse: 265 s.
Specific impulse sea level: 240 s.
Burn time: 114 s.
Number: 62 .
More... - Chronology...
Associated Countries
Associated Engines
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UA1206 CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982. More...
Associated Launch Vehicles
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Titan 34D American orbital launch vehicle. Stretched Titan core designed for use with 5 1/2 segment solid rocket motors. IUS (Interim/Inertial Upper Stage) solid upper stages, Transtage, or used without upper stages. More...
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Commercial Titan 3 American orbital launch vehicle. Commercial version of Titan 34D military booster. It differed in having a lengthened second stage and a 4 m diameter payload shroud to handle shuttle-class or Ariane-type dual payloads. More...
Associated Propellants
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Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
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