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LK-1 engine
IAI solid rocket engine. In production. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use increased Isp to 279 seconds, First flight 1995. Solid propellant rocket stage. 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.

AKA: LK-1. Status: In production. Number: 4 . Thrust: 774.00 kN (174,002 lbf). Specific impulse: 272 s. Specific impulse sea level: 250 s. Burn time: 55 s.

Fitted with 23.6:1 nozzle for upper stage use length was 8.4 m, and empty and gross mass were increased by 135 kg.

Area Ratio: 9. Propellant Formulation: HTPB.



Country: Israel. Launch Vehicles: Shaviyt 1, LeoLink LK-1, LeoLink LK-2. Propellants: Solid. Stages: LK-1 engine. Agency: IAI.

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