Encyclopedia Astronautica
Altair 2


Solid propellant rocket stage. Loaded/empty mass 275/37 kg. Thrust 22.24 kN. Vacuum specific impulse 266 seconds.

Cost $ : 0.700 million.

Status: Retired 1973.
Gross mass: 275 kg (606 lb).
Unfuelled mass: 37 kg (81 lb).
Height: 2.53 m (8.30 ft).
Diameter: 0.64 m (2.09 ft).
Span: 0.64 m (2.09 ft).
Thrust: 22.24 kN (5,000 lbf).
Specific impulse: 266 s.
Specific impulse sea level: 242 s.
Burn time: 28 s.
Number: 46 .

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Associated Countries
Associated Engines
  • X-258 Thiokol solid rocket engine. 22.2 kN. Isp=266s. Kick stage motor for Delta D, Scout A, Scout X-4. First flight 1963. More...

Associated Launch Vehicles
  • Scout X-4 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair 2 More...
  • Scout X-2B American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 1D + 1 x Castor + 1 x Antares 2 + 1 x Altair 2 More...
  • Thor Delta C American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x Altair 2 More...
  • Scout X-4A American all-solid orbital launch vehicle. Five stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair 2 + 1 x Cetus More...
  • Delta D American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2 More...
  • Delta E American orbital launch vehicle. Thor augmented with 3 x Castor 2 motors with Delta E and Altair 2 upper stage. More...
  • Scout A American all-solid orbital launch vehicle. All-solid low cost lightweight launch vehicle. More...
  • Scout A-1 American all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x Algol 2C + 1 x Castor 2 + 1 x Antares 2 + 1 x Altair 2 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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