Engine Model: LK-1. Designer: IAI. Propellants: Solid. Thrust(vac): 774.000 kN (174,002 lbf). Isp: 272 sec. Isp (sea level): 250 sec. Burn time: 55 sec. Chambers: 1. Area Ratio: 9.00. Country: Israel. Status: In production. First Flight: 1995. Last Flight: 2004. Flown: 4.00. Lengthened version of Shavit/RSA-3 rocket motor. For lower stage use with 9:1 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.
LK-1 used on Rocket Stages