Encyclopedia Astronautica
SR118


Solid propellant rocket stage. Loaded/empty mass 53,020/4,211 kg. Thrust 1,606.59 kN. Vacuum specific impulse 286 seconds. Modification of Peackeeper ICBM first stage.

Cost $ : 7.000 million.

Status: Out of production.
Gross mass: 53,020 kg (116,880 lb).
Unfuelled mass: 4,211 kg (9,283 lb).
Height: 10.70 m (35.10 ft).
Diameter: 2.36 m (7.74 ft).
Span: 2.36 m (7.74 ft).
Thrust: 1,606.59 kN (361,177 lbf).
Specific impulse: 286 s.
Specific impulse sea level: 229 s.
Burn time: 83 s.
Number: 25 .

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Associated Countries
Associated Engines
  • Castor 120 Thiokol solid rocket engine. 1650 kN. Isp=280s. Motor similar in size to the Peacekeeper missile stage 1 motor; filled the gap between Castor 4A and the large segmented motors. First flight 1989. 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...
  • Satellite Launch Vehicle American orbital launch vehicle. Orbital version. Selected by NASA under the COTS program in January 2008 in place of the cancelled Kistler for post-shuttle ISS resupply missions. Uses half-length shuttle SRB as first stage; proven Castor-120 as second stage; new Castor-30 as third stage; and Oribtal Adjusment Module from Lockheed's cancelled Athena launcher as a fourth stage. 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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