Encyclopedia Astronautica
Antares 1A


Solid propellant rocket stage. Loaded/empty mass 1,225/294 kg. Thrust 60.50 kN. Vacuum specific impulse 256 seconds.

Cost $ : 4.000 million.

Status: Retired 1970.
Gross mass: 1,225 kg (2,700 lb).
Unfuelled mass: 294 kg (648 lb).
Height: 3.38 m (11.08 ft).
Diameter: 0.78 m (2.55 ft).
Span: 0.78 m (2.55 ft).
Thrust: 60.50 kN (13,600 lbf).
Specific impulse: 256 s.
Specific impulse sea level: 233 s.
Burn time: 39 s.
Number: 40 .

More... - Chronology...


Associated Countries
Associated Engines
  • X-254 Thiokol solid rocket engine. 60.5 kN. Isp=256s. Used on Blue Scout 1, Blue Scout 2, Blue Scout Junior, Scout X-1. First flight 1960. More...

Associated Launch Vehicles
  • Scout X American suborbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1A + 1 x Castor + 1 x Antares + 1 x Altair More...
  • Scout X-1 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1B + 1 x Castor + 1 x Antares + 1 x Altair 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...
  • Blue Scout 1 American suborbital launch vehicle. Air Force version of Scout used for suborbital tests. More...
  • Blue Scout 2 American all-solid orbital launch vehicle. Air Force version of Scout used for suborbital and orbital military tests. More...
  • Scout X-1A American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 1B + 1 x Castor + 1 x Antares + 1 x Altair + 1 x Cetus More...
  • RAM B American all-solid orbital launch vehicle. Three stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor More...
  • Wasp American sounding rocket. Wasp research and develoment chaff and parachute rockets were used to obtain wind soundings to 260,000 m, fired by Naval Ordnance Missile Test Facility at WSPG. 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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