Encyclopedia Astronautica
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.

Thrust (sl): 70.500 kN (15,849 lbf). Thrust (sl): 7,191 kgf. Chamber Pressure: 58.00 bar. Area Ratio: 64. Propellant Formulation: HTPB.

Gross mass: 10,841 kg (23,900 lb).
Unfuelled mass: 1,134 kg (2,500 lb).
Height: 3.15 m (10.33 ft).
Diameter: 2.34 m (7.67 ft).
Thrust: 181.50 kN (40,803 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 115 s.
Burn time: 152 s.
Number: 84 .

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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...
  • 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 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
  • ESBM Solid propellant rocket stage. Loaded/empty mass 10,810/1,030 kg. Thrust 189.20 kN. Vacuum specific impulse 293 seconds. More...
  • IUS-1 Solid propellant rocket stage. Loaded/empty mass 10,841/1,134 kg. Thrust 181.50 kN. Vacuum specific impulse 296 seconds. More...
  • TOS Solid propellant rocket stage. Loaded/empty mass 10,960/1,130 kg. Thrust 185.10 kN. Vacuum specific impulse 296 seconds. IUS-2 stage with simplified electronics. More...

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