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, and a Castor-120 motor as the first stage.

LEO Payload: 1,550 kg. to: 200 km Orbit. at: 0.0 degrees. Payload: 1,200 kg. to a: Sun synchronous, 800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 148,000 kgf. Total Mass: 70,000 kg. Core Diameter: 2.3 m. Total Length: 26.4 m. Launch Price $: 20.00 million. in 1999 price dollars.

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