Encyclopedia Astronautica
SLV-2


ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979.

Thrust (sl): 216.000 kN (48,558 lbf). Thrust (sl): 22,026 kgf. Chamber Pressure: 43.00 bar. Area Ratio: 14.

Gross mass: 4,900 kg (10,800 lb).
Unfuelled mass: 1,750 kg (3,850 lb).
Height: 6.35 m (20.83 ft).
Diameter: 0.80 m (2.62 ft).
Thrust: 267.00 kN (60,023 lbf).
Specific impulse: 267 s.
Specific impulse sea level: 216 s.
Burn time: 40 s.
Number: 8 .

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Associated Countries
See also
Associated Launch Vehicles
  • SLV Indian all-solid orbital launch vehicle. More...

Associated Manufacturers and Agencies
  • ISRO Indian manufacturer of rockets, spacecraft, and rocket engines. Indian Space Research Organization, India. 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
  • ASLV-2 Solid propellant rocket stage. Loaded/empty mass 4,400/800 kg. Thrust 304.00 kN. Vacuum specific impulse 276 seconds. More...
  • SLV-2 Solid propellant rocket stage. Loaded/empty mass 4,900/1,750 kg. Thrust 267.01 kN. Vacuum specific impulse 267 seconds. More...

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