Encyclopedia Astronautica
Titan USRM


Solid propellant rocket stage. Loaded/empty mass 357,239/52,040 kg. Thrust 7,560.68 kN. Vacuum specific impulse 286 seconds.

Cost $ : 33.330 million.

AKA: Upgraded Solid Rocket Motor.
Status: Study 1991.
Gross mass: 357,239 kg (787,577 lb).
Unfuelled mass: 52,040 kg (114,720 lb).
Height: 33.54 m (110.03 ft).
Diameter: 3.20 m (10.40 ft).
Span: 3.20 m (10.40 ft).
Thrust: 7,560.68 kN (1,699,709 lbf).
Specific impulse: 286 s.
Specific impulse sea level: 259 s.
Burn time: 140 s.
Number: 38 .

More... - Chronology...


Associated Countries
Associated Engines
  • USRM Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strap-on booster for Titan 4B. First flight 1997. More...

Associated Launch Vehicles
  • Nerva 2 American nuclear-powered orbital launch vehicle. Version of 1960's nuclear fission engine proposed in 1990's. More...
  • Timberwind American nuclear-powered orbital launch vehicle. DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements. More...
  • Titan 404B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. More...
  • Titan 403B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. 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...

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