Encyclopedia Astronautica
LK-1


Solid propellant rocket stage. Loaded/empty mass 13,990/1,240 kg. Thrust 774.00 kN. Vacuum specific impulse 268 seconds. Lengthened version of Shavit/RSA-3 rocket motor. For lower stage use with 17.1:1 nozzle. Fitted with 23.6:1 nozzle for upper stage use specific impulse increases to 279 seconds, length to 8.4 m, and empty and gross mass are increased by 135 kg.

Status: Development ended 2001.
Gross mass: 13,990 kg (30,840 lb).
Unfuelled mass: 1,240 kg (2,730 lb).
Height: 7.50 m (24.60 ft).
Diameter: 1.35 m (4.42 ft).
Span: 1.50 m (4.90 ft).
Thrust: 774.00 kN (174,002 lbf).
Specific impulse: 268 s.
Specific impulse sea level: 250 s.
Burn time: 55 s.
Number: 5 .

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Associated Countries
Associated Engines
  • LK-1 IAI solid rocket engine. 774 kN. In production. Isp=272s. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use inceased Isp to 279 seconds, First flight 1995. More...

Associated Launch Vehicles
  • Shavit 1 Israeli all-solid orbital launch vehicle. Shavit 1 is an improved version of the original Shavit with a stretched first stage motor. More...
  • LeoLink LK-1 Satellite launcher derived from planned Israeli Shavit-2 launch vehicle, but with rocket motors and major components built in USA to qualify for US contracts. 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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