ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979.
Thrust (sl): 62.200 kN (13,983 lbf). Thrust (sl): 6,344 kgf. Chamber Pressure: 43.00 bar. Area Ratio: 24.
Gross mass: 1,500 kg (3,300 lb).
Unfuelled mass: 440 kg (970 lb).
Height: 2.30 m (7.50 ft).
Diameter: 0.82 m (2.69 ft).
Thrust: 90.70 kN (20,390 lbf).
Specific impulse: 277 s.
Specific impulse sea level: 190 s.
Burn time: 45 s.
Number: 8 .
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Associated Countries
See also
Associated Launch Vehicles
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SLV Indian all-solid orbital launch vehicle. More...
Associated Manufacturers and Agencies
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ISRO Indian manufacturer of rockets, spacecraft, and rocket engines. Indian Space Research Organization, India. More...
Associated Propellants
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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
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ASLV-3 Solid propellant rocket stage. Loaded/empty mass 1,710/650 kg. Thrust 90.70 kN. Vacuum specific impulse 277 seconds. More...
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SLV-3 Solid propellant rocket stage. Loaded/empty mass 1,500/440 kg. Thrust 90.70 kN. Vacuum specific impulse 277 seconds. More...
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