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Shaviyt
Part of Jericho Family
Shavit
Shavit
Credit: © Mark Wade
Israeli all-solid orbital launch vehicle. Satellite launcher derived from Jericho II MRBM, essentially identical to South African RSA-3.

AKA: NEXT;Shavit. Status: Active. First Launch: 1988-09-19. Last Launch: 1990-04-03. Number: 2 . Payload: 160 kg (350 lb). Thrust: 412.70 kN (92,779 lbf). Gross mass: 23,630 kg (52,090 lb). Height: 18.00 m (59.00 ft). Diameter: 1.35 m (4.42 ft). Apogee: 366 km (227 mi).

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).

LEO Payload: 160 kg (350 lb) to a 366 km orbit at 143.00 degrees. Launch Price $: 15.000 million in 1999 dollars.

Stage Data - Shavit

  • Stage 1. 1 x RSA-3-1. Gross Mass: 10,215 kg (22,520 lb). Empty Mass: 1,100 kg (2,400 lb). Thrust (vac): 456.000 kN (102,512 lbf). Isp: 265 sec. Burn time: 52 sec. Isp(sl): 240 sec. Diameter: 1.30 m (4.20 ft). Span: 2.30 m (7.50 ft). Length: 6.30 m (20.60 ft). Propellants: Solid. No Engines: 1. Engine: RSA-3-1. Status: Out of Production. Comments: Source: Missile exhibit and placards, AF Museum, South Africa.
  • Stage 2. 1 x RSA-3-2. Gross Mass: 10,971 kg (24,186 lb). Empty Mass: 1,771 kg (3,904 lb). Thrust (vac): 476.600 kN (107,144 lbf). Isp: 277 sec. Burn time: 52 sec. Isp(sl): 220 sec. Diameter: 1.30 m (4.20 ft). Span: 1.30 m (4.20 ft). Length: 6.40 m (20.90 ft). Propellants: Solid. No Engines: 1. Engine: RSA-3-2. Status: Out of production. Comments: Source: Missile exhibit and placards, AF Museum, South Africa. Empty mass includes 583 kg for payload shroud, guidance, orientation and spin-up platform that positions stage 3 and payload for final orbital insertion burn.
  • 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.



Family: all-solid, orbital launch vehicle. Country: Israel. Spacecraft: Ofeq 1-2, Ofeq 3, Ofeq 5. Projects: Ofeq. Launch Sites: Palmachim. Stages: RSA-3-1, RSA-3-2, RSA-3-3. Agency: IAI. Bibliography: 2, 4, 42, 455, 552, 554, 6, 61.
Photo Gallery

Shavit LaunchShavit Launch


Shavit Post-Boost BuShavit Post-Boost Bu


Shavit Apogee Kick MShavit Apogee Kick M



1988 September 19 - . 09:32 GMT - . Launch Site: Palmachim. LV Family: Jericho. Launch Vehicle: Shaviyt.
  • Ofeq-1 - . Mass: 155 kg (341 lb). Nation: Israel. Agency: ISA. Program: Ofeq. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ofeq 1-2. Decay Date: 1989-01-14 . USAF Sat Cat: 19519 . COSPAR: 1988-087A. Apogee: 1,149 km (713 mi). Perigee: 250 km (150 mi). Inclination: 142.9000 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 - . Launch Site: Palmachim. LV Family: Jericho. Launch Vehicle: Shaviyt.
  • Ofeq-2 - . Mass: 160 kg (350 lb). Nation: Israel. Agency: ISA. Program: Ofeq. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ofeq 1-2. Decay Date: 1990-07-09 . USAF Sat Cat: 20540 . COSPAR: 1990-027A. Apogee: 251 km (155 mi). Perigee: 149 km (92 mi). Inclination: 143.2000 deg. Period: 88.50 min. Communication experiments. .


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