Encyclopedia Astronautica
UA1206


CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982.

Thrust (sl): 5,639.500 kN (1,267,810 lbf). Thrust (sl): 575,074 kgf. Propellant Formulation: PBAN.

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).
Thrust: 6,226.90 kN (1,399,863 lbf).
Specific impulse: 265 s.
Specific impulse sea level: 240 s.
Burn time: 114 s.
Number: 38 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • 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...

Associated Manufacturers and Agencies
  • CSD American manufacturer of rocket engines. Chemical Systems Division, USA. More...

Associated Propellants
  • 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...

Associated Stages
  • Titan UA1206 Solid propellant rocket stage. Loaded/empty mass 251,427/40,827 kg. Thrust 6,227.00 kN. Vacuum specific impulse 265 seconds. More...

Home - Browse - Contact
© / Conditions for Use