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Shavit
All-solid orbital launch vehicle. Family: Jericho. Country: Israel. Status: Active. Manufacturer's Designation: NEXT.

Satellite launcher derived from Jericho II MRBM, essentially identical to South African RSA-3.

NEXT was a variant with an improved upper stage for proposed launch from Wallops Island, USA (launch from Israel is only possible into retrograde orbits since due East launch would be over territory of adjacent countries).

Manufacturer: IAI. Launches: 7. Failures: 2. Success Rate: 71.43%. First Launch Date: 1988-09-19. Last Launch Date: 2007-06-10. Launch data is: continuing. LEO Payload: 160 kg (350 lb). to: 366 km Orbit. at: 143.00 degrees. Apogee: 1,400 km (800 mi). Associated Spacecraft: Ofeq 1-2. Liftoff Thrust: 412.700 kN (92,779 lbf). Total Mass: 23,630 kg (52,090 lb). Core Diameter: 1.35 m (4.42 ft). Total Length: 18.00 m (59.00 ft). Launch Price $: 15.000 million. in: 1999 price dollars.

  • Stage1: 1 x RSA-3-1. Gross Mass: 10,215 kg (22,520 lb). Empty Mass: 1,100 kg (2,400 lb). Motor: 1 x RSA-3-1. Thrust (vac): 456.000 kN (102,512 lbf). Isp: 265 sec. Burn time: 52 sec. Length: 6.30 m (20.60 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
  • Stage2: 1 x RSA-3-2. Gross Mass: 10,971 kg (24,186 lb). Empty Mass: 1,771 kg (3,904 lb). Motor: 1 x RSA-3-2. Thrust (vac): 476.600 kN (107,144 lbf). Isp: 277 sec. Burn time: 52 sec. Length: 6.40 m (20.90 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
  • Stage3: 1 x RSA-3-3. Gross Mass: 2,048 kg (4,515 lb). Empty Mass: 170 kg (370 lb). Motor: 1 x RSA-3-3. Thrust (vac): 58.800 kN (13,219 lbf). Isp: 298 sec. Burn time: 94 sec. Length: 2.60 m (8.50 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
Version:

Shavit 1. Status: Active. Manufacturer's Designation: NEXT.

Shavit 1 is an improved version of the original Shavit with a stretched first stage motor.

Launches: 5. Failures: 2. First Launch Date: 1995-04-05. Last Launch Date: 2007-06-10. LEO Payload: 225 kg (496 lb). to: 366 km Orbit. at: 143.00 degrees. Apogee: 1,400 km (800 mi). Associated Spacecraft: Ofeq 3, Ofeq 5. Liftoff Thrust: 760.000 kN (170,850 lbf). Total Mass: 30,000 kg (66,000 lb). Core Diameter: 1.35 m (4.42 ft). Total Length: 18.00 m (59.00 ft). Launch Price $: 15.000 million. in: 1999 price dollars.

  • Stage1: 1 x LK-1. Gross Mass: 13,990 kg (30,840 lb). Empty Mass: 1,240 kg (2,730 lb). Motor: 1 x LK-1. Thrust (vac): 774.000 kN (174,002 lbf). Isp: 268 sec. Burn time: 55 sec. Length: 7.50 m (24.60 ft). Diameter: 1.35 m (4.42 ft). Propellants: Solid.
  • Stage2: 1 x RSA-3-2. Gross Mass: 10,971 kg (24,186 lb). Empty Mass: 1,771 kg (3,904 lb). Motor: 1 x RSA-3-2. Thrust (vac): 476.600 kN (107,144 lbf). Isp: 277 sec. Burn time: 52 sec. Length: 6.40 m (20.90 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
  • Stage3: 1 x RSA-3-3. Gross Mass: 2,048 kg (4,515 lb). Empty Mass: 170 kg (370 lb). Motor: 1 x RSA-3-3. Thrust (vac): 58.800 kN (13,219 lbf). Isp: 298 sec. Burn time: 94 sec. Length: 2.60 m (8.50 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
Version:

LeoLink LK-1. Status: Development ended 2001.

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: 200 km Orbit. Payload: 415 kg (914 lb). to a: Sun synchronous, 800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 600.000 kN (134,880 lbf). Total Mass: 30,500 kg (67,200 lb). Core Diameter: 1.35 m (4.42 ft). Total Length: 20.90 m (68.50 ft). Launch Price $: 15.000 million. in: 1999 price dollars.

  • Stage1: 1 x LK-1. Gross Mass: 13,990 kg (30,840 lb). Empty Mass: 1,240 kg (2,730 lb). Motor: 1 x LK-1. Thrust (vac): 774.000 kN (174,002 lbf). Isp: 268 sec. Burn time: 55 sec. Length: 7.50 m (24.60 ft). Diameter: 1.35 m (4.42 ft). Propellants: Solid.
  • Stage2: 1 x LK-1. Gross Mass: 13,990 kg (30,840 lb). Empty Mass: 1,240 kg (2,730 lb). Motor: 1 x LK-1. Thrust (vac): 774.000 kN (174,002 lbf). Isp: 268 sec. Burn time: 55 sec. Length: 7.50 m (24.60 ft). Diameter: 1.35 m (4.42 ft). Propellants: Solid.
  • Stage3: 1 x RSA-3-3. Gross Mass: 2,048 kg (4,515 lb). Empty Mass: 170 kg (370 lb). Motor: 1 x RSA-3-3. Thrust (vac): 58.800 kN (13,219 lbf). Isp: 298 sec. Burn time: 94 sec. Length: 2.60 m (8.50 ft). Diameter: 1.30 m (4.20 ft). Propellants: Solid.
  • Stage4: 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. Length: 1.30 m (4.20 ft). Diameter: 1.56 m (5.11 ft). Propellants: Hydrazine.
Version:

LeoLink LK-2. Status: Development ended 2002.

As Leolink LK-1, but with a Castor-120 motor as the first stage.

LEO Payload: 1,550 kg (3,410 lb). to: 200 km Orbit. Payload: 1,200 kg (2,600 lb). to a: Sun synchronous, 800 km, 98.5 deg orbital trajectory. Liftoff Thrust: 1,450.000 kN (325,970 lbf). Total Mass: 70,000 kg (154,000 lb). Core Diameter: 2.30 m (7.50 ft). Total Length: 26.40 m (86.60 ft). Launch Price $: 20.000 million. in: 1999 price dollars.

Shavit Chronology

1988 September 19 - 09:32 GMT - Palmachim -. LV Model: Shavit . Shaviyt 1 Ofeq-1 Mass: 155 kg (341 lb). Spacecraft: Ofeq 1-2. Agency: Israeli Space Agency. Perigee: 250 km (150 mi). Apogee: 1,149 km (713 mi). Inclination: 142.90 deg. Period: 98.80 min. First Israeli launch; possibly experimental surveillance mission. Experimental satellite 'Offeq-1'. Launch time 0934 GMT. Location: site on the coast south of Tel-Aviv. Launching organization: Israel Aircraft Industries, Ltd (IAI) and Israeli Space Agency (ISA). Function: 1) Experimentation in generation of solar power; 2) Experimentation in transmission reception from space; 3) Verification of system's ability to withstand vacuum and weightless conditions; 4) Data collection on space environment conditions and Earth's magnetic field.

1990 April 3 - 12:02 GMT - Palmachim -. LV Model: Shavit . Shaviyt 2 Ofeq-2 Mass: 160 kg (350 lb). Spacecraft: Ofeq 1-2. Agency: Israeli Space Agency. Perigee: 149 km (92 mi). Apogee: 251 km (155 mi). Inclination: 143.20 deg. Period: 88.50 min. Communication experiments.

1995 April 5 - 11:16 GMT - Palmachim -. LV Model: Shavit 1 . Shaviyt 1 3 Ofeq-3 Mass: 189 kg (416 lb). Spacecraft: Ofeq 3. Agency: Israeli Space Agency. Perigee: 366 km (227 mi). Apogee: 694 km (431 mi). Inclination: 143.40 deg. Period: 94.50 min.

1998 January 22 - 12:56 GMT - Palmachim -. LV Model: Shavit 1 . Shaviyt 1 4 FAILURE: Launch vehicle failed during second stage burn. Ofeq-4 Spacecraft: Ofeq 3. Agency: Israeli Space Agency. Fell in Mediterranean Sea.

2002 May 28 - 15:25 GMT - Palmachim -. LV Model: Shavit 1 . Shaviyt 1 5 Ofeq-5 Mass: 300 kg (660 lb). Spacecraft: Ofeq 5. Agency: Tsahal (Israel). Perigee: 370 km (220 mi). Apogee: 757 km (470 mi). Inclination: 143.50 deg. Period: 95.90 min. Military Observation satellite. Return to flight of the Shavit booster following a lauanch failure. Launch delayed from third quarter 2001. The three-stage Shavit rocket took off from Palmachim Air Force Base on the Israeli coast and flew westward to put the satellite in a retrograde orbit. The AUS-51 third stage solid motor entered a 262 x 774 km x 143.5 deg orbit and separated from the Ofeq satellite. Both coasted up to apogee at around 1620 UTC when Ofeq made a burn to increase its velocity by 33 m/s, raising the orbit to 369 x 771 km x 143.5 deg.

2004 September 6 - Palmachim -. LV Model: Shavit 1 . Shaviyt 1 6 FAILURE: Third stage orientation failure at 270 seconds into the flight. Ofeq-6 Mass: 300 kg (660 lb). Spacecraft: Ofeq 5. Agency: Tsahal. Military observation satellite failed to reach orbit. Finanical loss estimated by Israeli press as $ 100 million.

2007 June 10 - 23:40 GMT - Palmachim -. LV Model: Shavit 1 . Shaviyt 1 7 Ofeq-7 Mass: 300 kg (660 lb). Spacecraft: Ofeq 5. Agency: Tsahal. Perigee: 340 km (210 mi). Apogee: 576 km (357 mi). Inclination: 141.80 deg. Period: 93.80 min. Israeli optical reconnaisance satellite, evidently using an improved version of the Shavit booster and probably heavier and more capable than its predecessors.

Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • McDowell, Jonathan, Jonathan's Space Report (Internet Newsletter), Harvard University, Weekly, 1989 to Present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: http://msl.jpl.nasa.gov/home.html.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
  • Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
  • NASA/GSFC Orbital Information Group Website, Web Address when accessed: http://oig1.gsfc.nasa.gov/.
  • Space-Launcher.com, Orbital Report News Agency. Web Address when accessed: http://www.orbireport.com/Log.html.
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