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Anti-Ballistic Missiles I

SOLO HERMELIN

Update 08.01.10

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Table of Content

SOLO Anti – Ballistic Missiles

Ballistic Missiles of the Third World Iran’s Ballistic Missiles

North Korea's Ballistic Missiles

Ballistic Missile CharacteristicsUSA Ballistic Missile Defense

Military Services and National Labs 1944 - 1983

Project Nike

Safeguard Program

Strategic Defense Initiative Organization (SDIO) 1983 – 1994

Nike-Hercules Missile Nike Zeus A

Nike-Ajax

Nike Zeus B

Sprint LIM-49A Spartan

SDIO ProgramsStandard Missile

Aegis Ballistic Missile Defense SystemUSA Ballistic Missile Defense System Airborne Laser (ABL)

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SOLO Anti – Ballistic Missiles

Radars for Ballistic Missile Defense

Homing Overlay TestsMcDonnell Douglas HEDI (High Endo-atmospheric Defense Interceptor) ERIS (Exo-atmospheric Reentry Interceptor Subsystem)

FLAGE (Flexible Lightweight Agile Guided Experiment) TestingERINT (Extended Range Interceptor)Patriot System LEAP (Lethal Exo-atmospheric Projectile) Testing:Ground Based Interceptor [GBI]THAAD (Target High Altitude Area Defense)

MEADS (Medium Extended Air Defense System)

Missile Defense Agency (MDA) 2001 - Ballistic Missile Defense Organization (BMDO) 1994 – 2001

Space Based Infrared System

Kinetic Energy Interceptor (KEI)

Anti – Ballistic II

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SOLO

References

Anti – Ballistic Missiles

Arrow Missile System

Aster Missile

RUSIA’s Anti - Ballistic Missiles

SH-01 'Galosh' anti-ballistic missilesRussia’s S-300 Family

Anti – Ballistic II

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Shahab 3Credit - © Mark Wade

http://www.astronautix.com/lvs/shahab3.htm

http://www.fas.org/nuke/guide/iran/missile/shahab-3.htm

Sharab-3 SRBM Launch

The Iranian Shahab-3 ballistic missile means Meteor-3 or Shooting Star-3 in Farsi [alternatively designated Zelzal (Earthquake)] is derived from the 1,350-1,600 kilometer range North Korean No-dong missile. The Shahab-3 reportedly has a range of between 1,350 and 1,600 kilometers and is capable of carrying a 1,000-760 kilogram warhead.

Iranian Shahab 3B Missile test fire

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http://www.globalsecurity.org/wmd/world/iran/shahab-1.htm

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SOLO Anti – Ballistic Missileshttp://www.globalsecurity.org/wmd/world/iran/images/shahab-3-vick1.jpg

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SOLO Anti – Ballistic Missileshttp://www.globalsecurity.org/wmd/world/iran/images/shahab-3-vick1.jpg

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http://www.globalsecurity.org/wmd/world/iran/images/shahab-3-vick1.jpg

Shahab-3, 3A/ Zelzal-3

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http://www.globalsecurity.org/wmd/world/iran/images/shahab-4-vick1.jpg

Shahab-4

The Iranian Shahab-4 missile is believed to be a derivation of the 1,350-1,600 kilometer range North Korean No-dong -A missile delivering a 1,158 - 550 kilograms warhead and the follow on Taep’o-dong-1/Paekdosan-1 (TD-1) launch vehicle. In recent years the Iranian’s have indicated that the Space booster varient was having solid motor boosters added to the design originally considered among other unspecified design changes.

http://www.globalsecurity.org/wmd/world/iran/shahab-4.htm

Iran's Ballistic Missile Capabilities

Iran - Missiles

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http://www.globalsecurity.org/wmd/world/iran/images/iris-design-heritage.jpg

Shahab-3D, IRIS http://www.globalsecurity.org/wmd/world/iran/iris.htm

The Shahab-3D is not the Shahab-3 nor is it the original Iranian Shahab-4 design, better known as the North Korean Taep’o-dong-1/NKSL-1 which has a range of 1,240 miles (1,995.16 km) but is perhaps one of several other possibilities. The Iranian statement that the Shahab-3D was powered by both liquid and solid propellant suggest that this is indeed a different missile design from the Shahab-3 which is known to be based on the North Korean No-dong-A design a single stage liquid propellant ballistic missile. It is also known that the Shahab-3 single engine is started by a solid propellant cartage that is expended ever before lift off. This however does not explain the introduction of solid propellant on this launch vehicle variant. This indication of the presence of solid propellant suggest the introduction of the Iranian “IRIS” so called satellite launch vehicle or at least its precursor sounding rocket for the Iranian space program “IRIS” launch vehicle. Potentially the IRIS launch vehicle combination could also serve as an (ASAT) anti-satellite launch vehicle.

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http://www.globalsecurity.org/wmd/world/dprk/images/nkir-missile-overview.jpg

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Designation Stages Propellant Range IOC Inventory Alternate Name

Mushak - 120 1 solid 130 km ? Iran – 130, Nazeat 10,

Mushak - 160 1 solid 160 km Fateh-110/NP-110

Mushak - 200 1 solid 200 km Zilzal - 2

Shahab - 1 1 liquid 300 km 1995 50 - 300 Scud - B

Shahab - 2 1 liquid 500 km 50 - 150 Scud - C

Shahab - 3 1 liquid 1,300 km 2002 25 - 100 Zilzal - 3

Shahab - 4 2 liquid 2,000 km 0

IRIS 1 liquid/solid 3,000 km 2005 Shahab – 3D

X-55 LACM 1 jet engine 3,000 km 2001 12

Shahab - 5 3 liquid 5,500 km

Shahab - 6 3 liquid 10,000 km

http://www.globalsecurity.org/wmd/world/iran/missile.htm

Iran’s Ballistic Missiles

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SOLO Anti – Ballistic Missiles

North Korea's Ballistic Missiles

Type/Designation Range (km) Payload (kg) Origin Comments

Scud – B 300 1,000 USSR

Scud – C Variant 500 700 Indigenous

Nodong - 1 1,000 700 – 1,000 Indigenous

Nodong - 2 1,500 770 Indigenous

Taepodong - 1 1,500 – 2,000 1,000 Indigenous Combined Nodong and Scud, tested 31.08.1998

Taepodong - 2 3,500 – 5,5000

1,000 Indigenous

North Korea's missile capabilities

A Look Back at N. Korea's Missile Development Program

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SOLO Anti – Ballistic Missileshttp://www.globalsecurity.org/wmd/world/dprk/images/nkir-missile-overview.jpg

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AlHusein Ghauri

Nodong

R27

Scud B

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Ballistic Missile Characteristics

Velicov, et al.”Weaponry in Space: The Dilemma of Security”, MIR, 1986Table: IEEE Spectrum Special Issue, September 1997

Ground Range (km)

Burnout Velocity (km/s)

Burn Time (s) Burnout Altitude (km)

Apogee (km) Total Flight Time

(min)

100 1.0 40 - 30 15 - 10 30> 2

300 1.7 70 - 60 35 - 25 100> 6

600 2.4 90 - 60 60 - 40 150> 4

1,000 2.9 110 - 70 80 - 50 230 8

3,000 4.9 140 - 80 120 - 100 650 14

10,000 7.2 300 - 170 220 - 180 1300 30

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SOLO Anti – Ballistic Missileshttp://www.missilethreat.com/repository/doclib/IWGreport.pdf

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http://www.missilethreat.com/repository/doclib/IWGreport.pdf

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SOLO Anti – Ballistic Missileshttp://www.missilethreat.com/repository/doclib/IWGreport.pdf

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SOLO Anti – Ballistic Missileshttp://www.missilethreat.com/repository/doclib/IWGreport.pdf

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Details

Anti – Ballistic Missiles

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http://www.cbc.ca/news/background/us_missiledefence/

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SOLO Anti – Ballistic MissilesProject Nike

Project Nike began in 1944 when the War Department demanded a new air defense system to combat the new jet aircraft, as existing gun-based systems proved largely incapable of dealing with the speeds and altitudes at which jet aircraft operated. Two proposals were accepted. Bell Labs offered Project Nike. A much longer-ranged collision-course system was developed by General Electric, named Project Thumper, eventually delivering the BOMARC missile. Bell's proposal would have to deal with bombers flying at 500 mph (800 km/h) or more at altitudes of up to 60,000 ft (20,000 m). At these speeds, even a supersonic rocket is no longer fast enough to be simply aimed at the target. The missile must "lead" the target to ensure it hits it before it runs out of fuel. This means that the missile and target cannot be tracked in a single radar, increasing the complexity of the system. One part was well developed. By this point, the US had considerable experience with lead-calculating analog computers, starting with the British Kerrison Predictor and a series of increasingly capable U.S. designs. For Nike, three radars were used. The acquisition radar searched for a target to be handed over to the Target Tracking Radar (TTR) for tracking. The Missile Tracking Radar (MTR) tracked the missile by way of a transponder, as the missile's radar signature alone was not sufficient. The MTR also commanded the missile by way of pulse-position modulation, the pulses were received, decoded and then amplified back for the MTR to track. Once the tracking radars were locked the system was able to work automatically following launch, barring any unexpected occurrences. The computer compared the two radars directions, along with information on the speeds and distances, to calculate the intercept point and steer the missile. The entirety of this system was provided by the Bell System's electronics firm, Western Electric. The Douglas-built missile was a two stage missile using a solid fuel booster stage and a liquid fueled (IRFNA/UDMH) second stage. The missile could reach a maximum speed of 1,000 mph (1,600 km/h), an altitude of 70,000 ft (21 km) and had a range of 25 miles (40 km). The missile contained an unusual three part payload, with explosive fragmentation charges at three points down the length of the missile to help ensure a fatal hit. The missile's limited range was seen by critics as a serious flaw, because it often meant that the missile had to be sited very close to the area it was protecting. After bickering between the Army and the Air Force (see the Key West Agreement), all longer-range systems were turned over to the Air Force in 1948. They merged their own long-range research with Project Thumper, while the Army continued to develop Nike. In 1950 the Army formed the Army Anti-Aircraft Command (ARAACOM) to operate batteries of anti-aircraft guns and missiles. ARAACOM was renamed the US Army Air Defense Command (USARADCOM) in 1957. It adopted a simpler acronym, ARADCOM, in 1961.

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SOLO Anti – Ballistic Missiles

Project Nike

Missile Nike Ajax Nike Hercules Nike Zeus A Nike Zeus B(XLIM – 49A)

Spartan

(LIM – 49A)

Length 10.36 m over.

6.41m 2nd stage

12.53 m over.

8.18m 2nd stage13.5 m 14.7 m 16.8 m

Diameter 0.30m 0.8 m booster

0.53m 2nd stage0.91 m 0.91 m 1.09 m

Fin Span 1,22 m 3.5 m booster

1.88m 2nd stage2.98 m 2.44 m 2.98 m

Mass 1,116 kg launch

523 kg 2nd stage

4,850 kg launch

2,505 kg 2nd stage4,980 kg 10,300 kg 13,100 kg

Max Speed Mach 2.25 Mach 3.65 > Mach 4 > Mach 4 > Mach 4

Range 40 km 140 km 320 km 400 km 740 km

Ceiling 21,300 m 45,700 m ? 280 km 560 km

First Stage Liquid-fuel 263 kN, 2.5 s

Hercules M42

978 kN

Thiokol TX-135

1,800 kN

Thiokol TX-135

2,000 kN

Thiokol TX-500

2,200 kN

2nd Stage Liquid-fuel 11.8kN, 21 s

Thiokol M30

44.4 kN

? Thiokol TX-238 Thiokol TX-454

3th STAGE - - - Thiokol TX-239 Thiokol TX-239

Nike Ajax

Nike Hercules

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SOLO Anti – Ballistic Missiles

Project Nike

Missile Nike Ajax Nike Hercules Nike Zeus A Nike Zeus B(XLIM – 49A)

Spartan

(LIM – 49A)

First Stage Liquid-fuel 263 kN, 2.5 s

Hercules M42

978 kN

Thiokol TX-135

1,800 kN

Thiokol TX-135

2,000 kN

Thiokol TX-500

2,200 kN

2nd Stage Liquid-fuel 11.8kN, 21 s

Thiokol M30

44.4 kN

? Thiokol TX-238 Thiokol TX-454

3th STAGE - - - Thiokol TX-239 Thiokol TX-239

Warhead Conventional

3 warheads (2 layers of ¼ in steel cubes

Nose: M2 (2kg)

Mid: M3 (42kg)

Aft: M4 (27kg)

T-45 HE (500kg) with

272kg of HBX-6 M17 blast-fragmentation

Nuclear warhead only

Nuclear warhead only

Nuclear warhead only

Warhead Nuclear

Conventional warhead only

W-31 nuclear

2 kt (M-97)

20 kt (M-22)

40 kt (M-23)

W-31 nuclear W-50 thermonuclear

400 kt

W-71 thermonuclear

5 Mt

AT&T Archives: Nike Zeus Missile System

Weird NJ Nike Missile Bases

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Nike-Hercules Missile

Nike-Hercules Missile, designation MIM-14 (initially SAM-N-25) was a solid fuel propelled surface-to-air missile, used by US and NATO armed forces for high- and medium-altitude air defense. It could also be employed in a surface-to-surface role. The Nike-Hercules system, a follow-up to the Nike-Ajax missile, was developed during the Cold War to destroy enemy bombers and enemy bomber formations, as well as serve as an anti-ballistic missile system. Western Electric, Bell Laboratories, and Douglas Aircraft Company were chief contractors for the system.

Manu factors Western Electric

Bell Laboratories

Douglas Aircraft

First Stage Hercules M42 solid- fuel cluster

978 kN (220 klbf)

Second stage Thiokol M30

solid- fuel cluster

44.4 kN (10 klbf)

Length 12.53 m overall, 8.18 m 2nd stage

Diameter 0.8 m booster, 0.53 m 2nd stage

Fin Span 3.5 m booster, 1.88 2nd stage

Mass 4850 kg at launch,

2505 kg 2nd stage

Max Speed Mach 3.65 (ca. 4,470 km/h)

Range 140 km

Ceiling 45,700 m

Warhead Conventional

T-45 HE of 500 kg (272 kg HBX-E blast-fragmentation)

Warhead Nuclear

W31 nuclear2 kt (M-97), 20kt (M-22), 40 kt (M-23)

http://en.wikipedia.org/wiki/Nike-Hercules_Missile

Nike Hercules Missile Test Firing Return to TOC

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SOLO Anti – Ballistic MissilesNike Zeus A

The Nike Zeus A is aerodynamically very similar to the Nike Hercules, just scaled up. However, the Nike Zeus A was designed for a very different mission - it was designed to perform an interception of ballistic missile RVs at high altitude. Like Nike Hercules, it was a two stage missile but instead of using the Nike Ajax booster, a new booster was used which was the largest single chamber solid rocket motor produced in the US at that time delivering over 450 000lb of thrust.The Nike Zeus A had a very short life as it only had a small number of launchers before being replaced by the Nike Zeus B. As a result, some sources claim that this was in fact a flight test article for the booster and not actually a Nike Zeus missile at all. I find this hard to understand as the 2nd stage is new, or at least the fins have been redesigned (especially when comparing it to a Nike Hercules), indicating some design work had taken place for this missile.The capability of the missile was constrained by the 200 mile range restriction that was issued by Secretary of Defense Wilson in 28 November 1956. This restriction was rescinded 12 months later once Sputnik 1 had orbited the earth. This then allowed the US Army to then develop the Nike Zeus B which overcame some of the limitations already present and known in the Nike Zeus A.

Length 13.5 m

Diameter 0.91 m

Fin Span 2.98 m

Mass 4,980 kg

Max Speed > Mach 4

Range 320 km

Ceiling ?

First Stage Thiokol TX-135

1,800 kN

2nd Stage Thiokol

Guidance Radio - Control

Warhead W-31 nuclear

20 kt

http://www.nuclearabms.info/NikeZeus.html

Nike Zeus Missile

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SOLO Anti – Ballistic MissilesNike Zeus B

Nike Zeus B was a far more capable missile than the A version due to a number of factors. It had a greater range, it was a three stage missile and it was designed to intercept targets outside the atmosphere. The main reason for this missile being developed was due to the dropping of the range restriction that had been imposed during 1956/7. By increasing the range, the missile could defend a much larger area which meant that fewer installations were required which provided some cost savings while still maintaining a defence. The first stage was the same as that of Zeus A, but everything after that was new. The second stage had a slightly smaller diameter than the booster, while the third stage was slightly smaller again. The large fins that were so prominent on the Zeus A sustainer were gone, and replaced with small vanes at the top of the missile which provided some control while in the atmosphere. Once the missile had left the atmosphere control was obtained through the 3rd stage motor. Target destruction was obtained through the use of a nuclear warhead. This warhead was tested during 1962 at Christmas Island in the Pacific Ocean.

With the Nike-X ABM system, studies went into an extended range version of the Zeus B, and that missile was called Nike Zeus EX. It was renamed as Spartan when Nike-X was renamed as Sentinel in 1967.

Missile Nike Zeus B(XLIM – 49A)

Spartan

(LIM – 49A)

Length 14.7 m 16.8 m

Diameter 0.91 m 1.09 m

Fin Span 2.44 m 2.98 m

Mass 10,300 kg 13,100 kg

Max Speed > Mach 4 > Mach 4

Range 400 km 740 km

Ceiling 280 km 560 km

First Stage Thiokol TX-135

2,000 kN

Thiokol TX-500

2,200 kN

2nd Stage Thiokol TX-238 Thiokol TX-454

3th STAGE Thiokol TX-239 Thiokol TX-239

Warhead Nuclear

W-50 thermonuclear

400 kt

W-71 thermonuclear

5 Mt

http://www.nuclearabms.info/NikeZeus.html

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SOLO Anti – Ballistic MissilesSafeguard Program

The Safeguard Program was a United States Army anti-ballistic missile system developed in the late 1960s. Safeguard was designed to protect U.S. ICBM missile sites from counterforce attack, thus preserving the option of an unimpeded retaliatory strike. Safeguard used much of the same technology of the earlier Sentinel Program, which had been designed to protect U.S. cities.Sentinel was developed but never deployed. Safeguard was planned for several sites within the United States, but only one was completed. Until the Ground-Based Midcourse Defense system was deployed, the Stanley R. Mickelsen Safeguard complex in Nekoma, North Dakota, with the separate long-range detection radar located further north near the town of Cavalier, North Dakota, was the only operational anti-ballistic missile system ever deployed by the United States. It defended Minuteman ICBM silos near Grand Forks AFB, North Dakota. Safeguard consisted of the long range Spartan and the short range Sprint missiles the Perimeter Acquisition Radar (PAR) and computer system.

Image of the Stanley R. Mickelsen Safeguard complex.

Perimeter Acquisition Radar (PAR)

http://en.wikipedia.org/wiki/Safeguard_Program

Stanley R. Mickelsen Safeguard complex in Nekoma, North Dakota

Safeguard Missile Program

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SOLO Anti – Ballistic Missiles

The Sprint was a United States Army anti-ballistic missile, developed as part of the Nike-X program, later redesignated the Sentinel program. Sentinel never became operational, but the technology was deployed briefly in a downsized version called the Safeguard program. Sprint was a two-stage, solid-fuel surface-to-air missile armed with a W66 enhanced radiation thermonuclear warhead. The Sprint, like the Spartan, was in operational service for only a few months in the Safeguard program, from October 1975 to early 1976. A combination of high costs, congressional opposition, questionable efficacy and the Anti-Ballistic Missile Treaty resulted in a very short operational period.

Manufacturer Martin Marietta

First Stage Hercules X-265

2950 kN (650 klbf) for 1.2 s

Second Stage Hercules X-271

Length 8.20 m overall

Diameter 1.35 m

Wingspan

Mass 3,500 kg

Range 40 km

Ceiling 30 km

Max Speed >Mach 10 (7,500 mph)

Guidance System

Radio Command

Warhead W-66 nuclear low Kt, enhance

radiation

Introduction date

IOC: 1972

Aerial image of Remote Sprint Launch Site No. 2.

Sprint

ABM Spartan and Sprint

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http://srmsc.org/images/002707l0.gif

http://www.srmsc.org/images/004530l0.jpg

Spartan and Sprint missile models

Dual launch of Sprint missiles during a salvo test at Meck island

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SPRINT Missile

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LIM-49A Spartan

Manufacturer Western Electric & McDonnell Douglas

First Stage Thiokol TX-500

2,200 kN

Second Stage Thiokol TX-454

Third Stage Thiokol TX-239

Launch Mass 13,100 kg (29,000lb)

Length 16.8 m (55 ft 2 in)

Diameter 1.08 m (3 ft 7 in)

Wingspan 2.98 m (9 ft 9.6 in)

Speed > Mach 4

Range 740 km (460 mi)

Flying Altitude 560 km (350 mi)

Warhead W-71 nuclear, 5 Mt

Guidance Radio Command

Launch platform Silo

The Spartan, designation LIM-49A, was a United States Army anti-ballistic missile. It was a three-stage, solid-fuel surface-to-air missile that carried a 5 megaton W71 thermonuclear warhead to intercept incoming warheads at high altitude. The missile was launched from an underground silo, and radio command guided. The warhead was designed to destroy incoming nuclear weapons by X-ray flux rather than by blast. This very kill mechanism was, however, a major cause contributing to the phase-out of the nuclear-warheads in the antiaircraft and anti-ballistic missile rockets - a high-altitude nuclear explosion produced a strong electromagnetic pulse (EMP) that would destroy unhardened (i.e. unshielded) electronic devices, especially those working on the solid state component base, like transistors, integrated circuits etc. The higher integration and subtler the parts, the more damage from the EMP-induced currents in the circuitry would occur, causing damage to computers, data and communication networks, power-generating plants and grids, air traffic control systems, etc. The Spartan missile was in operational service for only a few months, from October 1975 to early 1976. A combination of high costs and the SALT I treaties made the missiles an unattractive bargain.

Spartan Anti Missile Systems

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http://www.srmsc.org/images/002705l1.gifhttp://www.srmsc.org/images/001018l0.jpg

LIM 49A - SPARTAN Missile

http://www.smdc.army.mil/SMDCPhoto_Gallery/Eagle/Sep_Oct07/10%20(3).jpg

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http:www.fas.org/spp/starwars/road.pdf

Tim

elin

e

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SOLO Anti – Ballistic MissilesStrategic Defense Initiative Timeline

http://en.wikipedia.org/wiki/Strategic_Defense_Initiative

Reagan Discusses the Strategic Defense Initiative

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3 Project and proposals 4 Ground-based programs 4.1 Extended Range Interceptor (ERINT) 4.2 Homing Overlay Experiment (HOE) 4.3 Exoatmospheric Reentry-vehicle Interception System (ERIS) 5 Directed-energy weapon (DEW) programs 5.1 X-ray laser 5.2 Chemical laser 5.3 Neutral Particle Beam 5.4 Laser and mirror experiments 5.5 Hypervelocity Rail Gun (CHECMATE) 6 Space-based programs 6.1 Space-Based Interceptor (SBI) 6.2 Brilliant Pebbles 7 Sensor programs 7.1 Boost Surveillance and Tracking System (BSTS) 7.2 Space Surveillance and Tracking System (SSTS) 7.3 Brilliant Eyes 7.4 Other sensor experiments 8 Countermeasures

Strategic Defense Initiative

http://en.wikipedia.org/wiki/Strategic_Defense_Initiative

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The following table summarizes the SM-1/2 block numbers and RIM-66 designation suffix letters for the Standard MR missile.

RIM-66A SM-1MR Block I-IV

RIM-66B SM-1MR Block V

RIM-66C SM-2MR Block I (Aegis)

RIM-66D SM-2MR Block I (Tartar)

RIM-66E SM-1MR Block VI (RIM-66E-1/3/7/8), VI A (RIM-66E-5), VI B (RIM-66E-6)

RIM-66G SM-2MR Block II (Aegis)

RIM-66H SM-2MR Block II (Aegis/VLS)

RIM-66J SM-2MR Block II (Tartar)

RIM-66K SM-2MR Block III (RIM-66K-1), III A (RIM-66K-2) (Tartar)

RIM-66L SM-2MR Block III (RIM-66L-1), III A (RIM-66L-2) (Aegis)

RIM-66M SM-2MR Block III (RIM-66M-1), III A (RIM-66M-2), III B (RIM-66M-5) (Aegis/VLS)

http://www.designation-systems.net/dusrm/m-66.html

Standard Missile

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Standard Missile

Standard Missile Family Commemorates 60 Years of Innovation

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Data for RIM-66B/C, except where noted:

RIM-66B SM-1MR RIM-66C SM-2MR

Length 4.47 m (14 ft 8 in) 4.72 m (15 ft 6 in)

Finspan 1.07 m (42.3 in)

Diameter 0.34 m (13.5 in)

Weight 621 kg (1370 lb)

Speed Mach 3.5

Ceiling 24400 m (80000 ft); RIM-66A: 19800 m (65000 ft) > 24400 m (80000 ft)

Range 46 km (25 nm); RIM-66A: 32 km (17 nm) 74 km (40 nm)

Propulsion Aerojet MK 56 dual-thrust solid-fueled rocket

RIM-66A: Aerojet MK 27; RIM-66G/.../M: Thiokol MK 104

Warhead MK 90 blast-fragmentation;

RIM-66A: MK 51 continuous-rod MK 115 blast-fragmentation

Standard Missile

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http://www.raytheon.com/products/stellent/groups/public/documents/content/cms01_055767.pdf

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RIM-66 SM-2 Medium Range Block III/IIIA/IIIB

Primary function: surface-to-air

Contractor: Raytheon and others

Power plant: dual thrust, solid fuel rocket

Length: 15 ft., 6 in. (4.72 m)

Weight: SM-2 – 1,558 lb (708 kg)

Diameter: 13.5 in. (343 mm)

Wing span: 3 ft., 6 in. (1.08 m)

Range: 40 to 90 nautical miles (74 to 167 km)

Guidance system: semi-active radar homing (inertial guidance

with terminal IR additionally fitted in Block IIIB)

Warhead: radar and contact fuze, blast fragmentation warhead

Date deployed: 1981 (SM-2MR)

Standard Missile http://en.wikipedia.org/wiki/Standard_missile

The additional imaging IR sensor fitted to the top of the SM-2ER block 3B and 4A missiles (Raytheon)

http://www.raytheon.com/products/stellent/groups/public/documents/content/cms01_055768.pdf

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RIM-66 SM-2 Medium Range Block III/IIIA/IIIB

An un-finned RIM-67 SM2-ER sits in the magazine of the USS Mahan (DLG-11) prior to a missile launch.

General characteristics[3]

Primary function: surface-to-air

Contractor: Raytheon and others

Power plant: dual thrust, solid fuel rocket

Length: 15 ft., 6 in. (4.72 m)

Weight: SM-2 – 1,558 lb (708 kg)

Diameter: 13.5 in. (343 mm)

Wing span: 3 ft., 6 in. (1.08 m)

Range: 40 to 90 nautical miles (74 to 167 km)

Guidance system: semi-active radar homing (inertial guidance with terminal IR additionally fitted in Block IIIB)

Warhead: radar and contact fuze, blast fragmentation warhead

Date deployed: 1981 (SM-2MR)

Standard Missile http://en.wikipedia.org/wiki/Standard_missile

The additional imaging IR sensor fitted to the top of the SM-2ER block 3B and 4A missiles (Raytheon)

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RIM-156 SM-2 Extended Range (ER) Block IV

General characteristics[3]

Primary function: fleet and extended area air defense Contractor: Raytheon and others Power plant: two-staged solid-fueled rockets Length: 21 ft., 6 in. (6.55 m) with booster Weight: 3,225 lb (1466 kg) Diameter: 21 in. (533 mm) with booster Wing Span: 3 ft., 6 in. (1.08 m) Range: 100 to 200 nautical miles (185 to 370 km) Guidance system: semi-active radar homing. Inertial/command guidance with terminal IR homing in Block IV-A Warhead: radar and contact fuze, blast-fragment warhead Date deployed: 1998

Standard Missile http://en.wikipedia.org/wiki/Standard_missile

Lightweight Exo-Atmospheric Projectile (LEAP) attaches to a modified SM-2 Block IV missile used by the U.S. Navy

http://en.wikipedia.org/wiki/Anti-ballistic_missile

http://www.designation-systems.net/dusrm/m-156.html

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RIM-161 Standard Missile 3 (SM-3) Block I/IA General characteristics [4]

Primary function: Aegis Ballistic Missile Defense System Contractor: Raytheon Power plant:

First Stage: Mk72 Booster Aerojet Second Stage: MK104 Dual Thrust Rocket Motor (DTRM) Aerojet Third Stage: MK136 Third Stage Rocket Motor (TSRM) ATK Fourth Stage: Solid Divert and Attitude Control System (SDACS) ATK

Length: Weight: Diameter: 0.34 m (13.5 in) Wing Span: 1.57 m (61.8 in) Range: >270 nautical miles Guidance system: GPS / INS / Semi-active radar homing / Passive LWIR (8-15 µm) Seeker (Kill Wehicle) Warhead: Exoatmospheric Hit-to-kill Kinetic Warhead (KW) Date deployed:

A RIM-161 Standard Missile (SM-3) is launched from the Aegis cruiser USS Lake Erie

Standard Missile http://en.wikipedia.org/wiki/Standard_missile

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SM – 2MR

SM – 2ERBlock 3

SM – 2ERBlock 4

SM – 3

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Data for RIM-161A:

Length (incl. booster) 6.55 m (21 ft 6 in) Finspan 1.57 m (61.8 in) Diameter 0.34 m (13.5 in) Weight ? Speed 9600 km/h (6000 mph) Ceiling > 160 km (100 miles) Range > 500 km (270 nm) Propulsion Booster: United Techologies MK 72 solid-fueled rocketSustainer: Atlantic Research Corp. MK 104 dual-thrust solid-fueled rocket3rd stage: Alliant Techsystem MK 136 solid-fueled rocket Warhead Hit-to-kill kinetic warhead (KW)

Standard Missile

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http://www.raytheon.com/products/stellent/groups/public/documents/content/cms01_055769.pdf

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http://www.raytheon.com/capabilities/rtnwcm/groups/rms/documents/content/rtn_rms_ps_sm6_datasheet.pdf

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http://www.designation-systems.net/dusrm/m-174.html

Raytheon RIM-174 ERAM (SM-6)The U.S. Navy's RIM-156B SM-2 Block IV A TBMD (Theater Ballistic Missile Defense) missile was cancelled in December 2001. Because the RIM-156B was to have secondary AAW (Anti-Air Warfare) capability, this left a potential gap in the future long-range air defense assets of the Navy. Therefore the ERAM (Extended Range AAW Missile) program to study possible replacements for the SM-2 Block IV A was begun. The result was the Standard Missile 6 (SM-6), which is effectively an RIM-156A SM-2 Block IV missile, to which the active radar seeker of the AIM-120C-7 AMRAAM air-to-air missile has been added for terminal guidance. Because of that seeker, the ERAM acronym has since been redefined to mean Extended Range Active Missile. In February 2008, ERAM was officially designated as RIM-174A.

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Aegis Ballistic Missile Defense System

The Aegis Ballistic Missile Defense System is a US Department of Defense Missile Defense Agency program developed to provide a last line of defense against ballistic missiles. Aegis BMD (also know as Sea-Based Midcourse) is designed to intercept ballistic missiles post-boost phase and prior to reentry

The current system uses the Lockheed-Martin Aegis Weapon System and the Raytheon RIM-161 STANDARD Missile-3 (SM-3).

The AN/SPY-1 radar antennas can be seen on the front and starboard side of the superstructure of USS Lake Erie (CG-70). Country of origin: United States Introduced: 1973 Type: 3D Air-search Frequency: S band[1] Range: 100+ nm[2] Azimuth: 0-360° Elevation: Horizon-Zenith[3] Power: 4 MW (peak)

Standard Missile - 3 (SM-3) is launched from the Pearl Harbor-based Aegis cruiser USS Lake Erie. November 17, 2005

Upon the completion of the ALI program, Aegis BMD was transitioned to the production phase. The first Block I production SM-3 was delivered in October 2004 and the Aegis 3.0 update was delivered in 2005.

http://en.wikipedia.org/wiki/Aegis_Ballistic_Missile_Defense_System

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JANES: Mk 7 Weapon System 'Aegis'; GWS Mk 34; FCS Mk 99 Date Posted: 23 July 2007

AEGIS Weapon System

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Parameter Value

Operating Frequency 3.3 Ghz

Wavelength 9.1 cm

Physical Aperture Area 12 m2

Effective Aperture Area 12 m2

Number of Active Elements 5,600

Receiving Gain (with weighting) 14,000

Azimuth Beam Width 1.6º

Elevation Beam Width 1.5º

Scan Sector 90º

Search Solid Angle (one line) 0.020 str

Total Average Power 58 kW

Power-aperture Product 700 kW m2

Noise Temperature 500 ºK

Equipment Loss (Beam center) 2.8 db

Extra Loss in Search 7.2 db

Atmospheric Loss 3.8 db

Total Search Loss 13.2 db

Report of theAmerican Physical Society Study Group on

Boost-Phase Intercept Systemsfor National Missile Defence

Scientific and Technical IssuesJuly 2003

pg. 178

AN/SPY-1B Radar Characteristics

http://www.fas.org/man/dod-101/sys/ship/cg-50-valchar.gif

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Military Technology, “The Paths Ahead: Missile Defense in Asia”, Vol. XXXI, Issue 10, 2007, pg. 80

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Aegis Ballistic Missile Defense System Flight Missions (FM)http://en.wikipedia.org/wiki/Aegis_Ballistic_Missile_Defense_System

FTR-1a Kinetic Warhead

Infrared image of the FM-3 Test Target just prior to impact

FTR-1a would demonstrate exo-atmospheric avionics operation of the SM-3 Kinetic Warhead (KW) and the real-time performance of the Aegis BMD AN/SPY-1 radar. At the time this test was conducted, the KW's propulsion system, the Solid Divert and Attitude Contol System(SDACS), was still under development. Total system operation was demonstrated in FM-2

The purpose of Flight Mission (FM)-2 (Codename: Stellar Eagle) was to characterize the Aegis Weapon System and Standard Missile-3 interceptor. The mission was not required to intercept the target. On January 25, 2002, an SM-3 launched from the USS Lake Erie collided with a test target northeast of the island of Kauai. This mission marked the first intercept of a ballistic missile from a sea-based platform.

On June 13, 2002 Aegis BMD succeeded in intercepting a unitary target missiles launched from PMRF during FM-3 (Codename: Stellar Impact). The USS Lake Erie was the firing ship. This mission marked the successful completion of the Aegis LEAP Intercept program.

On November 21, 2002 Aegis BMD intercepted a unitary ballistic missile during FM-4 (Codename: Stellar Viper). FM-4 was the first Aegis BMD test to conduct the "aimpoint shift" maneuver. The aimpoint shift increases the probability that the ballistic missile ordinance is destroyed at intercept. The USS Lake Erie was the firing ship.On April 26, 2007, Aegis BMD successfully intercepted its eighth target in ten attempts. This test marked the 27th successful "Hit-to-Kill" intercept (for all MDA systems) since 2001. The USS Lake Erie was the firing ship and utilized the Aegis 3.6 Weapon System. The interceptor was the SM-3 Block-Ia. This test not only demonstrated the ability of ABMD to intercept a ballistic missile but also demonstrated the Lake Erie's ability to simultaneously track and intercept antiship missiles. This test also utilized the Solid Divert and Attitude Control System (SDACS), in the full pulse configuration. [9]

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Aegis Ballistic Missile Defense System Flight Missions (FM)http://en.wikipedia.org/wiki/Aegis_Ballistic_Missile_Defense_System

http://www.raytheon.com/products/stellent/groups/public/documents/content/cms01_055769.pdf

Flight Mission 2: January 25 2002

Flight Mission 3: June 13 2002

Flight Mission 4: November 21 2002

Flight Mission 6:

April 26 2007 Aegis BMD successfully intercepted its eighth target in ten attempts.

Aegis Ballistic Missile Defense - FTM 04-1February 24 2005

February 12 2013 Aegis BMD Stellar Eyes (FTM-20) Flight Mission Success

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The SM-3 Kinetic Warhead from Raytheon Co., pictured in artist's rendering, would destroy enemy missiles during boost phase.

The SM3 projectile in the Standard Missile 3 is based on LEAP (lightweight exoatmospheric projectile) technology developed in the 1980s for SDIO. Much of the longwave-IR technology necessary for the acquisition and tracking of very cold objects in space serves as a basis for many of our EO/IR seekers

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טיל יירוטטיל יירוטSM-3SM-3

DACSDACS

Divert and Attitude Control System

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GAS GENERATOR – MULTIPULSE

ATTITUDE CONTROL ASSEMBLY – 3 VALVES/6 THRUSTERS

MAIN THRUSTER ASSEMBLY – 2 VALVES/4 THRUSTERS

INSULATION

DIVERTERVALVE

ASSEMBLY

INTERSTAGEEXTENSION– GRAPHITE/

EPOXY

DIVERTERVALVE

ASSEMBLY

CASE– GRAPHITE/EPOXY

GUIDANCEUNIT

INTERFACE

INTERSTAGE– GRAPHITE/EPOXY

INTERSTAGE– ALUMINUM

EJ ECTORINTERFACE

SUSTAIN

PULSE 1

PULSE 2

ראש יירוטראש יירוטSM-3SM-3

DACSDACS

DACS עם הודף מוצק

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DACSDACS עדכון מצב עולמיעדכון מצב עולמיAerojetAerojet של של התפתחות מערכת הסטה ותיקון מסלולהתפתחות מערכת הסטה ותיקון מסלול ( (Divert-Attitude Control System)Divert-Attitude Control System)

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DACSDACS עדכון מצב עולמיעדכון מצב עולמיAerojetAerojetהפטנט למערכת הסטה ותיקון מסלול של הפטנט למערכת הסטה ותיקון מסלול של

(1993) (1993)

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'USA explores miniature kill vehicles for missile defence' (JDW 13 February 2002)

The Multiple Kill Vehicle holds dozens of small kill vehicles that are designed to seek out warheads in space, collide with them and destroy them(Source: US Missile Defense Agency)

ABM Multiple Kill Vehicle Raytheon (MKV-R)

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Multiple Kill Vehicle

Description: The MKV system includes a carrier vehicle with on-board sensors and kill vehicles weighing approximately 10 pounds.

In the past, MDA officials estimated that the final weight of a single miniaturized kill vehicle would end up being anywhere between two kilograms (4.5 pounds) and 10 kilograms (22 pounds). This uncertainty has led to a great deal of speculation regarding the number of kill vehicles which will actually be carried in a single launch. Officials from both MDA and Lockheed Martin have suggested in the past that two dozen kill vehicles or more could fly on a single booster.

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Multiple Kill Vehicle

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Multiple Kill Vehicle

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Multiple Kill Vehicle

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Data for SM-6 ERAM (performance data based on RIM-156A):

Length (incl. booster) 6.55 m (21 ft 6 in)

Finspan 1.57 m (61.8 in)

Diameter 0.34 m (13.5 in); booster: 0.53 m (21 in)

Weight 1500 kg (3300 lb)

Speed Mach 3.5

Ceiling 33000 m (110000 ft)

Range 240 km (130 nm)

Propulsion United Techologies MK 72 solid-fueled rocket booster

Atlantic Research Corp. MK 104 dual-thrust solid-fueled rocket sustainer

Warhead MK 125 blast-fragmentation

SM-6 ERAM, the future Standard Missile

The SM-6 ERAM (Extended Range Active Missile) is an under development upgraded version of the SM-2 designed to hit both aircraft and high performance cruise missiles. The missile combines the proven SM-2 airframe with a seeker from an AIM-120 AMRAAM missile. By utilizing the seeker from the AIM-120 AMRAAM missile, the SM-6 can offer the capability to hit targets outside the ships radar horizon, and therefore offer increased range as well as accuracy. The missile also takes advantage of both the SM-2 and AIM-120 AMRAAM's data linking capability, and because it requires very little development is expected to be inexpensive to procure.

Standard Missile

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http://www.designation-systems.net/dusrm/m-161.html

SM-3 family (projected development) Standard Missile

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SM-3 family (projected development) Standard Missile

Military Technology, “The Paths Ahead: Missile Defense in Asia”, Vol. XXXI, Issue 10, 2007, pg. 85

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http://upload.wikimedia.org/wikipedia/commons/b/bd/NuclearWarningSystemMap.png

Ballistic Missile Early Warning System

Coverage of BMEWS is shown in red, complementing the coverage provided by the PAVE PAWS system in blue. Coverage for both systems extends over the North Pole and both report back to Cheyenne Mountain Air Base in Colorado.

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Military Technology, vol. XXXI, Issue 8, 2007, pg.38

Ballistic Missile Defense System

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The United States wants to build a system that will let it knock out incoming ballistic missiles potentially coming from North Korea and Iran.

This involves using radars in Alaska and California in the US and at Fylingdales in the UK. Another radar is planned for Greenland.

Anti-missile missiles, or interceptors, are being based in Fort GreelyAlaska (40 of them) and Vanderberg AFB California (4) and the plan is to put 10 of them in Poland with an associated radar in the Czech Republic.

http://news.bbc.co.uk/2/hi/europe/6720153.stm

NUCLEAR WARHEADS RussiaLand-launched: 2,146 Sea-launched: 1,392 Air-launched: 624 USLand-launched: 1,600Sea-launched: 3,168 Air-launched: 1,098 Source: Memorandum of Understanding (MOU) data 2007

Ballistic Missile Defense System

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USA Antiballistic Missile System

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Military Technology, vol. XXXI, Issue 8, 2007, pg.32

National BMD Engagement Sequence

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http://www.ausairpower.net/APA-DEW-HEL-Analysis.html

High Energy Lasers

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http://www.ausairpower.net/APA-DEW-HEL-Analysis.html

High Energy Lasers

High Energy Laser Attack

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http://www.ausairpower.net/APA-DEW-HEL-Analysis.html

High Energy Lasers

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http://www.ausairpower.net/APA-DEW-HEL-Analysis.html

High Energy Lasers

This image shows a technician working on the optical telescope turret of the ALL HEL weapon. Note the array of ancillary optical sensors (USAF).

COIL Turret AssemblyBeam Control Subsystem

A single stage of the COIL laser

Airborne Laser Gun Boeing 747-400 YAL-1 Chemical Oxygen Iodine Laser Missile Defense

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Airborne Laser(ABL)

IEEE SpectrumSeptember 1997

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Airborne Laser(ABL)

Airborne Laser Defense Program Overview (ABL)

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Airborne Laser(ABL)

IEEE SpectrumSeptember 1997

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Airborne Laser(ABL)

IEEE SpectrumSeptember 1997

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Go toAnti-Ballistic Missiles II

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April 18, 2023 103

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TechnionIsraeli Institute of Technology

1964 – 1968 BSc EE1968 – 1971 MSc EE

Israeli Air Force1970 – 1974

RAFAELIsraeli Armament Development Authority

1974 – 2013

Stanford University1983 – 1986 PhD AA

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References

Anti – Ballistic Missiles