Encyclopedia Astronautica
Alcor


Solid propellant rocket stage. Loaded/empty mass 520/50 kg. Thrust 35.59 kN. Vacuum specific impulse 230 seconds. Masses, specific impulse estimated.

Status: Retired 1977.
Gross mass: 520 kg (1,140 lb).
Unfuelled mass: 50 kg (110 lb).
Height: 1.37 m (4.49 ft).
Diameter: 0.46 m (1.50 ft).
Span: 0.46 m (1.50 ft).
Thrust: 35.59 kN (8,001 lbf).
Specific impulse: 230 s.
Burn time: 30 s.
Number: 51 .

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Associated Countries
Associated Engines
  • Alcor Aerojet solid rocket engine. Originally developed for the Air Force as a third Stage for the Athena sounding rocket; in some applications known as Zebra. One of its main attractions was a very high mass fraction First flight 1960. More...

Associated Launch Vehicles
  • Astrobee 500 American sounding rocket. Three stage vehicle consisting of 1 x Genie + 1 x Alcor + 1 x Asp More...
  • Blue Scout Jr American suborbital launch vehicle. Four stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor + 1 x Cetus More...
  • Astrobee 1500 American sounding rocket. Three stage vehicle consisting of 2 x Recruit + 1 x Aerojet Jr + 1 x Alcor More...
  • Astrobee 200 American sounding rocket. Two stage vehicle consisting of 1 x Genie + 1 x Alcor More...
  • RAM B American all-solid orbital launch vehicle. Three stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor More...
  • Athena RTV American test vehicle. The Athena was designed to simulate the re-entry environment of an intercontinental ballistic missile and was one of the few examples of sustained interstate missile tests within the United States. More...
  • Strypi VI American target missile. Four stage vehicle consisting of 2 x Recruit + 1 x Castor + 1 x ? + 1 x ? More...
  • Strypi VIIAR American target missile. Four stage vehicle consisting of 2 x Recruit + 1 x Castor 2 + 1 x Alcor + 1 x Alcyone 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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