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.

LEO Payload: 550 kg. to: 200 km Orbit. at: 0.0 degrees. Payload: 415 kg. to a: Sun synchronous, 800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 60,000 kgf. Total Mass: 30,500 kg. Core Diameter: 1.4 m. Total Length: 20.9 m. Launch Price $: 15.00 million. in 1999 price dollars.

• Stage Number: 1. 1 x LK-1 Gross Mass: 13,990 kg. Empty Mass: 1,240 kg. Thrust (vac): 79,000 kgf. Isp: 268 sec. Burn time: 55 sec. Isp(sl): 250 sec. Diameter: 1.4 m. Span: 1.5 m. Length: 7.5 m. Propellants: Solid No Engines: 1. LK-1

• Stage Number: 2. 1 x LK-1 Gross Mass: 13,990 kg. Empty Mass: 1,240 kg. Thrust (vac): 79,000 kgf. Isp: 268 sec. Burn time: 55 sec. Isp(sl): 250 sec. Diameter: 1.4 m. Span: 1.5 m. Length: 7.5 m. Propellants: Solid No Engines: 1. LK-1

• Stage Number: 3. 1 x RSA-3-3 Gross Mass: 2,048 kg. Empty Mass: 170 kg. Thrust (vac): 6,000 kgf. Isp: 298 sec. Burn time: 94 sec. Diameter: 1.3 m. Span: 1.3 m. Length: 2.6 m. Propellants: Solid No Engines: 1. RSA-3-3

• Stage Number: 4. 1 x LK-4 Gross Mass: 237 kg. Empty Mass: 71 kg. Thrust (vac): 41 kgf. Isp: 200 sec. Burn time: 800 sec. Diameter: 1.6 m. Span: 1.6 m. Length: 1.3 m. Propellants: Hydrazine No Engines: 1. LK-4

• 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.