Anti ballistic missiles i

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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 Characteristics
USA 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 Programs
Standard Missile
Aegis Ballistic Missile Defense System
USA Ballistic Missile Defense System
Airborne Laser (ABL)

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Table of Content (continue)
Radars for Ballistic Missile Defense
Homing Overlay Tests
McDonnell Douglas HEDI (High Endo-atmospheric Defense
Interceptor)
ERIS (Exo-atmospheric Reentry Interceptor Subsystem)
FLAGE (Flexible Lightweight Agile Guided Experiment) Testing
ERINT (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 – B

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Table of Content (continue)
SOLO
References
Anti – Ballistic Missiles
Arrow Missile System
Aster Missile
RUSIA’s Anti - Ballistic Missiles
SH-01 'Galosh' anti-ballistic missiles
Russia’s S-300 Family
Anti – Ballist

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

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Shahab-3, 3A/ Zelzal-3

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

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

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

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

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http://www.cbc.ca/news/background/us_missiledefence/
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Timeline
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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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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
stage
13.5 m 14.7 m 16.8 m
Diameter 0.30m 0.8 m booster
0.53m 2nd
stage
0.91 m 0.91 m 1.09 m
Fin Span 1,22 m 3.5 m booster
1.88m 2nd
stage
2.98 m 2.44 m 2.98 m
Mass 1,116 kg launch
523 kg 2nd
stage
4,850 kg launch
2,505 kg 2nd
stage
4,980 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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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 nuclear
2 kt (M-97), 20kt (M-22), 40 kt (M-23)
http://en.wikipedia.org/wiki/Nike-Hercules_Missile
Nike Hercules Missile Test Firing
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Nike 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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Nike 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
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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Safeguard 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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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
2950kN (650
klbf) for 1.2 s
Second Stage Hercules X-271
Length 8.20m overall
Diameter 1.35m
Wingspan
Mass 3,500kg
Range 40km
Ceiling 30km
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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http://srmc.org/pdf/004431p0.pdf
SPRINT Missile
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LIM-49A Spartan
Manufacturer Western Electric &
McDonnell Douglas
2,200kN
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
Timeline

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

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

58
RIM-156 SM-2 Extended Range (ER) Block IV
General characteristics[3]
Primary function: fleet and extended area air defense
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)
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
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

59
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

60
SM – 2MR
SM – 2ER
Block 3
SM – 2ER
Block 4
SM – 3

61
Data for RIM-161A:
Length (incl. booster) 6.55 m (21 ft 6 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 rocket
Sustainer: Atlantic Research Corp. MK 104 dual-thrust solid-fueled rocket
3rd stage: Alliant Techsystem MK 136 solid-fueled rocket
Warhead Hit-to-kill kinetic warhead (KW)
Standard Missile

62

63
http://www.raytheon.com/capabilities/rtnwcm/groups/rms/documents/content/rtn_rms_ps_sm6_datasheet.pdf

64
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.
Return to TOC

65
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

66
JANES: Mk 7 Weapon System 'Aegis'; GWS Mk 34; FCS Mk 99 Date Posted: 23 July 2007
AEGIS Weapon System

67
Parameter Value
Operating Frequency 3.3Ghz
Wavelength 9.1cm
Physical Aperture Area 12m2
Effective Aperture Area 12m2
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) 0.020str
Total Average Power 58kW
Power-aperture Product 700kW m2
Noise Temperature 500ºK
Equipment Loss (Beam center) 2.8db
Extra Loss in Search 7.2db
Atmospheric Loss 3.8db
Total Search Loss 13.2db
Report of the
American Physical Society Study Group on
Boost-Phase Intercept Systems
for National Missile Defence
Scientific and Technical Issues
July 2003
pg. 178
AN/SPY-1B Radar Characteristics
http://www.fas.org/man/dod-101/sys/ship/cg-50-valchar.gif

68
AEGIS Weapon System
Military Technology, “The Paths Ahead: Missile Defense in Asia”, Vol. XXXI, Issue 10, 2007, pg. 80

69
Aegis Ballistic Missile Defense System Flight Missions (FM)
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

70
Aegis Ballistic Missile Defense System Flight Missions (FM)
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

71
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

72
‫יירוט‬ ‫טיל‬‫יירוט‬ ‫טיל‬
SM-3SM-3
DACSDACS
Divert and Attitude Control System

73
GAS GENERATOR
– MULTIPULSE
ATTITUDE CONTROL ASSEMBLY
– 3 VALVES/6 THRUSTERS
MAIN THRUSTER ASSEMBLY
– 2 VALVES/4 THRUSTERS
INSULATION
DIVERTER
VALVE
ASSEMBLY
INTERSTAGE
EXTENSION
– GRAPHITE/
EPOXY
DIVERTER
VALVE
ASSEMBLY
CASE
– GRAPHITE/EPOXY
GUIDANCE
UNIT
INTERFACE
INTERSTAGE
– GRAPHITE/EPOXY
INTERSTAGE
– ALUMINUM
EJECTOR
INTERFACE
SUSTAIN
PULSE 1
PULSE 2
‫יירוט‬ ‫ראש‬‫יירוט‬ ‫ראש‬
SM-3SM-3
DACSDACS
DACS ‫דוה םע‬‫ף‬‫דוה םע הוד‬‫ם‬‫ףדוה םע‬ ‫דוה םע‬
‫מוצק‬

74
DACSDACS ‫עולמי‬ ‫מצב‬ ‫עדכון‬‫עולמי‬ ‫מצב‬ ‫עדכון‬
‫מסלול‬ ‫ותיקון‬ ‫הסטה‬ ‫מערכת‬ ‫התפתחות‬‫מסלול‬ ‫ותיקון‬ ‫הסטה‬ ‫מערכת‬ ‫התפתחות‬‫של‬‫של‬AerojetAerojet
((Divert-Attitude Control SystemDivert-Attitude Control System((

75
DACSDACS ‫עולמי‬ ‫מצב‬ ‫עדכון‬‫עולמי‬ ‫מצב‬ ‫עדכון‬
‫של‬ ‫מסלול‬ ‫ותיקון‬ ‫הסטה‬ ‫למערכת‬ ‫הפטנט‬‫של‬ ‫מסלול‬ ‫ותיקון‬ ‫הסטה‬ ‫למערכת‬ ‫הפטנט‬AerojetAerojet
(1993(1993((

76
'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)

77
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.

78

79

80

81
Data for SM-6 ERAM (performance data based on RIM-156A):
Length (incl. booster) 6.55 m (21 ft 6 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

82

83
SM-3 family (projected development)
Standard Missile

84
SM-3 family (projected development)
Standard Missile
Military Technology, “The Paths Ahead: Missile Defense in Asia”, Vol. XXXI, Issue 10, 2007, pg. 85
Return to TOC

85
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.

86
Military Technology, vol. XXXI, Issue 8, 2007, pg.38
Ballistic Missile Defense System

87
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
Russia
Land-launched: 2,146
Sea-launched: 1,392
Air-launched: 624
US
Land-launched: 1,600
Sea-launched: 3,168
Air-launched: 1,098
Source: Memorandum of Understanding (MOU) data 2007
Ballistic Missile Defense System

88
USA Antiballistic Missile System

89

90

91

92
Military Technology, vol. XXXI, Issue 8, 2007, pg.32
National BMD Engagement Sequence

93

94
Return to TOC

95
Anti – Ballistic MissilesSOLO
http://www.ausairpower.net/APA-DEW-HEL-Analysis.html
High Energy Lasers

96
High Energy Lasers
High Energy Laser Attack

97
High Energy Lasers

98
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

99
Airborne Laser
(ABL)
IEEE Spectrum
September 1997
SOLO
Airborne Laser
(ABL)
Airborne Laser Defense Program Overview (ABL)

100
Airborne Laser
(ABL)
IEEE Spectrum
September 1997

101
Airborne Laser
(ABL)
IEEE Spectrum
September 1997
Return to TOC

102
Go to
Anti-Ballistic Missiles II
Return to TOC

August 12, 2015 103
SOLO
Technion
Israeli Institute of Technology
1964 – 1968 BSc EE
1968 – 1971 MSc EE
Israeli Air Force
1970 – 1974
RAFAEL
Israeli Armament Development Authority
1974 – 2013
Stanford University
1983 – 1986 PhD AA

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SOLO
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Anti ballistic missiles i

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