ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979.
Thrust (sl): 5.690 kN (1,279 lbf). Thrust (sl): 580 kgf. Chamber Pressure: 29.00 bar. Area Ratio: 31.
Gross mass: 360 kg (790 lb).
Unfuelled mass: 98 kg (216 lb).
Height: 1.50 m (4.90 ft).
Diameter: 0.66 m (2.16 ft).
Thrust: 26.80 kN (6,025 lbf).
Specific impulse: 283 s.
Specific impulse sea level: 60 s.
Burn time: 33 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-4 Solid propellant rocket stage. Loaded/empty mass 512/195 kg. Thrust 35.00 kN. Vacuum specific impulse 281 seconds. More...
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SLV-4 Solid propellant rocket stage. Loaded/empty mass 360/98 kg. Thrust 26.83 kN. Vacuum specific impulse 283 seconds. More...
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