Encyclopedia Astronautica
ESBM


Solid propellant rocket stage. Loaded/empty mass 10,810/1,030 kg. Thrust 189.20 kN. Vacuum specific impulse 293 seconds.

Status: Out of production.
Gross mass: 10,810 kg (23,830 lb).
Unfuelled mass: 1,030 kg (2,270 lb).
Height: 3.00 m (9.80 ft).
Diameter: 2.30 m (7.50 ft).
Span: 2.30 m (7.50 ft).
Thrust: 189.20 kN (42,534 lbf).
Specific impulse: 293 s.
Burn time: 150 s.
Number: 10 .

More... - Chronology...


Associated Countries
Associated Engines
  • SRM-1 CSD solid rocket engine. 181.5 kN. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. Isp=296s. First flight 1982. 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...

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...

Home - Browse - Contact
© / Conditions for Use