LeoLink LK-1

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 (1,210 lb) to a 200 km orbit. Payload: 415 kg (914 lb) to a 800 km SSO. Launch Price $: 15.000 million in 1999 dollars.

Stage Data - LeoLink LK-1

• Stage 1. 1 x LK-1. Gross Mass: 13,990 kg (30,840 lb). Empty Mass: 1,240 kg (2,730 lb). Thrust (vac): 774.000 kN (174,002 lbf). Isp: 268 sec. Burn time: 55 sec. Isp(sl): 250 sec. Diameter: 1.35 m (4.42 ft). Span: 1.50 m (4.90 ft). Length: 7.50 m (24.60 ft). Propellants: Solid. No Engines: 1. Engine: LK-1. Status: Development 2002. Comments: 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.

• Stage 2. 1 x LK-1. Gross Mass: 13,990 kg (30,840 lb). Empty Mass: 1,240 kg (2,730 lb). Thrust (vac): 774.000 kN (174,002 lbf). Isp: 268 sec. Burn time: 55 sec. Isp(sl): 250 sec. Diameter: 1.35 m (4.42 ft). Span: 1.50 m (4.90 ft). Length: 7.50 m (24.60 ft). Propellants: Solid. No Engines: 1. Engine: LK-1. Status: Development 2002. Comments: 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.

• Stage 3. 1 x RSA-3-3. Gross Mass: 2,048 kg (4,515 lb). Empty Mass: 170 kg (370 lb). Thrust (vac): 58.800 kN (13,219 lbf). Isp: 298 sec. Burn time: 94 sec. Diameter: 1.30 m (4.20 ft). Span: 1.30 m (4.20 ft). Length: 2.60 m (8.50 ft). Propellants: Solid. No Engines: 1. Engine: RSA-3-3. Status: Out of Production. Comments: Data accurate. Source: Missile exhibit and placards, AF Museum, South Africa. ARC/Rafael AUS 51 is identical.

• Stage 4. 1 x LK-4. Gross Mass: 237 kg (522 lb). Empty Mass: 71 kg (156 lb). Thrust (vac): 402 N (90 lbf). Isp: 200 sec. Burn time: 800 sec. Diameter: 1.56 m (5.11 ft). Span: 1.56 m (5.11 ft). Length: 1.30 m (4.20 ft). Propellants: Hydrazine. No Engines: 1. Status: Development 2002. Comments: Upper stage for orbital insertion of Shavit or Leolink payloads.