شاويت!!!

واضح آرشیو وب فارسی:فان پاتوق: اين يك مقاله در مورد لانچر اسراييلي شاويت(پرتاب گر - ماهواره بر و...)ساخت اسراييل ملعونه.كه بر اساس موشك جريكو ساخته شده .من انرژي ترجمه نداشتم يه جوونمرد ترجمش كنه.با عرض پوزش

The global market trend towards the use of smaller satellites for remote sensing, telecommunications, science and other commercial, civilian and military applications is the major driver for MLM the Systems Division of Israel Aircraft Industries (IAI) to offer orbit insertion services using its SHAVIT family of satellite launchers.
IAI/MLM"s Division SHAVIT launcher offers various options for launching small satellites into Low Earth Orbit (LEO). The launch system is based on flight-proven hardware and software, and a unique integration and launch concept. These reduce significantly launch preparation time, and, consequently lower overall launch costs.

MLM developed, produced and launched the SHAVIT launcher that is responsible for placing Israel"s OFEQ satellites in space including OFEQ 5 that was launched Westward on 28th of May 2002 at 18:25 pm (Israel time).

SHAVIT is a three-stage satellite launcher, powered by three solid fuel rocket motors. The first two stages lift the launcher to an altitude of approximately 110 km. From this point, the launcher continues to gain height while coasting up to approximately 250 km, where the launcher positions itself and ejects the satellite shroud. After the separation of the main instrumentation compartment and while the launcher is spinning, the third stage motor is ignited. Thus, the satellite is inserted accurately into its transfer orbit at an altitude of approximately 260 km. Some analysts have speculated that the Jericho 2 is simply is the first two stages of the Shavit SLV.

Shavit is a 3-stage solid launcher whose 2 first stages are inherited from Jericho 2. All three stages use solid motors. The first- and second-stage motors were identical with differences in the expansion ratio of the nozzles. The third stage motor built by Raphael. The two first stages have a composit structure. They are identical and weigh 13 tons. The third stage is spherical, with a titanium structure. It weighs 2,6 tons and its 59 kN motor burns during 92.5 seconds. The equipment case with its rotation table is located under the third stage and is jettisoned before its ignition.

The Shavit-1 has an upgraded first stage. The first stage is stretched for higher propellant load. The Shavit launches take place from the Palmahim air force base, south of Tel Aviv.
A planned commercial Shavit upgrade called Next. This name is no longer used, and this proposed upgrade configuration is now called Shavit-2. Both first and second stages of the Shavit-2 use the stretched motor design of the Shavit-1 first stage. The third stage may be a standard AUS-51 motor built under license by Atlantic Research Corp.

IAI/MLM Division leads the Israeli space industry into the international commercial satellite launching market. Through strategic alliances, and constantly improving its launcher diversity, MLM continues to pursue multi-sensor micro satellite and airborne launching capabilities further improving its competitive position in this market.

SHAVIT utilizes a unique set of launch preparation equipment. It is largely independent of the launch site and provides full testing of the launcher on the launch pad. This configuration enables satellite launch from different launch sites, according to customer requirements.

The LEOLINK program was initiated to market IAI/MLM Division"s launch services for the global market using the current LK-A (Shavit 1) launcher, while developing LK-1 and LK-2, its next generation launchers:

LK-A - For 350kg-class satellites in 240x600km elliptical polar orbits.
LK-1 - For 350kg-class satellites in 700km circular polar orbits.
LK-2 - For 800kg-class satellites in 700km circular polar orbits
A Shavit LK air launched satellite launcher is being proposed by ISA and Israel Aircraft Industries. The booster would be a standard Shavit-1 without a first stage that would be dropped from a Hercules C-130 aircraft.
The LK-1 is closely based on the Shavit-2, a planned follow-on to the Shavit-1, but the motors and other components will be built in the United States. The LK-2 is a larger vehicle that will use a Thiokol Castor 120 motor as its first stage. The third stage may be either a standard AUS-51 motor built under license by Atlantic Research Corp., or a Thiokol Star 48 motor. All launch vehicles have a small monopropellant hydrazine fourth stage.

Shavit (RSA-3)

Stage Engines Thrust s.l. Isp s.l. Thrust vac Isp vac Propellant Burn time Flow rate Total Imp
- - kN N*s/kg kN N*s/kg tons s t/s MN*s
1 ATSM-9 412,6 2334 456,0 2579 9,10 51,5 0,1767 23,5
2 ATSM-9 471,1 2697 9,10 52,1 0,1747 24,5
3 AUS-51 58,8 2864 1,895 92,5 0,0205 5,4

Shavit-1

Stage Engines Thrust s.l. Isp s.l. Thrust vac Isp vac Propellant Burn time Flow rate Total Imp
- - kN N*s/kg kN N*s/kg tons s t/s MN*s
1 ATSM-13 552,5 2363 610 2608 12,75 54,5 0,2338 33,2
2 ATSM-9 564 2707 9,10 43,7 0,2082 24,6
3 AUS-51 59,3 2898 1,895 92,5 0,0205 5,5

Shavit-2 (LK-1)

Stage Engines Thrust s.l. Isp s.l. Thrust vac Isp vac Propellant Burn time Flow rate Total Imp
- - kN N*s/kg kN N*s/kg tons s t/s MN*s
1 ATSM-13 704,5 2452 775 2697 12,75 44,4 0,2872 34,4
2 ATSM-13 835 2736 12,75 41,8 0,3050 34,9
3 AUS-51 59,3 2898 1,895 92,5 0,0205 5,5

Shavit-3 (LK-2)
Stage Engines Thrust s.l. Isp s.l. Thrust vac Isp vac Propellant Burn time Flow rate Total Imp
- - kN N*s/kg kN N*s/kg tons s t/s MN*s
1 Castor 120 1483,7 2481 1650,3 2760 49,024 82 0,5980 135,3
2 ATSM-13 835 2736 12,75 41,8 0,3050 34,9
3 AUS-51 59,3 2898 1,895 92,5 0,0205 5,5
4 PEPT-420 0,40 2246 (?) 0,071 400 0,0002 0,16

Israel Space Agency (I.S.A.) Shavit
(RSA-3) Shavit-1
(LK-A) Shavit-2
(LK-1) Shavit-3
(LK-2)
Overall
Vehicle Operational from 19.09.1988 05.04.1995
to 15.09.1994 28.05.2002
Orbital flights 3 3 0 0
Payload weight t Mission 0,160 Mission 0,225 LEO 0,55 LEO 1,55
Gross liftoff weight t 23,39 27,25 31,40 72,30
Gross propellant weight t 20,10 23,75 27,40 63,67
Total length m 15,43 17,70 20,87 26,40
Max. diameter (span) m 2,30 2,30 2,30 2,36
Total liftoff thrust (s.l.) kN 412,7 552,5 704,5 1.484
Total impulse (vac) MN*s 53,4 63,3 74,8 175,7
Fairing Total length m 3,35 3,35 5,40 5,40
Diameter m 1,35 1,35 1,56 1,56
Total weight t 0,057 0,057 0,108 0,108
Stage 3 Name AUS-51 AUS-51 AUS-51 AUS-51
Length m 1,15 (2,13) 1,15 (2,13) 1,15 (2,13) 2,13
Diameter m 1,30 1,30 1,30 1,30
Liftoff weight t 2,574 2,574 2,574 2,574
Propellant weight t 1,895 1,895 1,895 1,895
Engines Rafael Rafael ARC/Rafael ARC/Rafael
Propellant solid solid HTPB solid HTPB solid HTPB
Total thrust (vac) kN 58,8 59,3 59,3 59,3
Specific impulse (vac) N*s/kg 2864 2898 2898 2898
Burn time s 92,5 92,5 92,5 92,5
Total impulse (vac) MN*s 5,4 5,5 5,5 5,5
Stage 2 Name TAAS TAAS TAAS TAAS
Length m 5,68 5,68 7,95 7,95
Diameter m 1,35 1,35 1,35 1,35
Liftoff weight t 10,388 10,388 14,126 14,126
Propellant weight t 9,100 9,100 12,750 12,750
Engines ATSM-9 ATSM-9 ATSM-13 ATSM-13
Propellant solid solid HTPB solid HTPB solid HTPB
Total thrust (vac) kN 471,1 564 835 835
Specific impulse (vac) N*s/kg 2697 2736 2736 2736
Burn time s 52 44 42 42
Total impulse (vac) MN*s 24,5 24,6 34,9 34,9
Stage 1 Name TAAS TAAS TAAS Castor 120
Length m 5,25 7,52 7,52 10,95 (9,02)
Diameter m 1,35 1,35 1,35 2,36
Liftoff weight t 10,215 13,990 13,990 53,900
Propellant weight t 9,100 12,750 12,750 49,024
Engines ATSM-9 ATSM-13 ATSM-13 Thiokol
Propellant solid solid HTPB solid HTPB solid HTPB
Total thrust (s.l.) kN 412,7 552,5 704,5 1.483,7
Specific impulse (s.l.) N*s/kg 2334 2363 2452 2481
Burn time s 51,5 54,5 44,5 82
Total impulse (vac) MN*s 23,5 33,2 34,4 135,3

Launcher Mission Date Intern. Design Spacecraft Mass (t)
Shavit LEO 19.09.1988 1988-87 Ofeq 1 0,156
LEO 03.04.1990 1990-27 Ofeq 2 0,160
LEO 15.09.1994 failed Ofeq 0,189

Shavit-1 LEO 05.04.1995 1995-18 Ofeq 3 0,225
LEO 22.01.1998 failed Ofeq 4 0,250
LEO 28.05.2002 2002-25 Ofeq 5 0,300

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