This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: IAI. Used on stages: LK-1. Used on launch vehicles: Shavit 1, LeoLink LK-1, LeoLink LK-2. Propellants: Solid Thrust(vac): 79,000 kgf. Isp: 272 sec. Isp (sea level): 250 sec. Burn time: 55 sec. Chambers: 1. Area Ratio: 9.00. Country: Israel. Status: Development. Comments: 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.
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Last update 12 March 2001.
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© Mark Wade, 2001 .