Anti-Ballistic Missile Systems

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Anti-Ballistic Missiles II
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)
Anti-Ballistic

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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)

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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

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Continue from
Anti-Ballistic I

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AN/FPS – 108 Cobra Dana
Calibration Fixture
First deployed in 1977, the AN/FPS-108 radar
operates in the 1215-1400 MHz band using a 29m
phased array antenna. The primary mission is to
track and collect data on foreign intercontinental
ballistic missile (ICBM) and submarine launched
ballistic missile (SLBM) test launches to the
Kamchatka impact area and the broad ocean impact
areas in the Pacific Ocean. The metric and signature
data collected support START 2 and INF treaty
monitoring, and scientific and technical intelligence
efforts.
Aleutian Islands
Raytheon
UHF Phased Array
30 m diameter
35,000 elements
25,000 nmi range
http://www.fas.org/spp/military/program/track/cobra_dane.htm

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AN/FPS-115 PAVE PAWS Radar
PAVE PAWS reached initial operating
capability 4 April 1980 at Otis AFB in
Massachusetts, and 15 August at Beale AFB,
California
PAVE is an Air Force program name, that,
contrary to some reports, does not have an
expansion, while PAWS stands for Phased
Array Warning System. The radar is used
primarily to detect and track sea-launched
and intercontinental ballistic missiles. The
system also has a secondary mission of Earth-
orbiting satellite detection and tracking.
Information received from the PAVE PAWS
radar systems pertaining to SLBM/ICBM and
satellite detection is forwarded to the United
States Space Command's Missile Warning
and Space Control Centers at Cheyenne
Mountain Air Force Base, Colo. Data is also
sent to the National Military Command
Center and the US Strategic Command.
http://www.fas.org/spp/military/program/track/pavepaws.htm
•UHF Phased Array
•1792 elements
•22.1 meter diameter
•3,000 nmi
PAVE PAWS

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AN/FPS-115 PAVE PAWS Radar
Peak Power 1,792 active elements at 325
watts = 582.4 kilowatts (kW)
Duty Factor 25% (11% search, 14%
track)
Average Power 145.6 kW
Effective Transmit
Gain
37.92 dB
Active Radar Diameter 22.1 m
Frequency 420 MHz – 450 MHz
Radar Detection Range 5,556 km (3,000 nmi)
Wavelength 0.69 m at 435 MHz
Sidelobs -20 dB (1st
), -30 dB (2nd
)
-- 38 dB (root mean square)
Face Tilt 20 degrees
Number of Faces 2
3 db Beam Width 2.2 degrees
Specifications
http://www.fas.org/spp/military/program/track/pavepaws.htm

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Cobra Judy Ballistic Missile Tracking Radar AN/SPQ - 11
http://en.wikipedia.org/wiki/AN/SPQ-11
Close up view of the front of Cobra Judy radar,
1983
Passive electronically scanned array 2900-3100 MHz (EF band), 22.5 foot diameter,
12,288 elements.
AN/SPQ-11 Cobra Judy

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ACTIVE PHASED ARRAY RADAR (APAR)
http://www.thales-systems.ca/projects/apar/apar.pdf
During live missile firing tests held by the Royal Netherlands Navy (RNLN) in March 2005, the
APAR radar system successfully guided two Evolved SeaSparrow Missiles (ESSM) and two
Standard Missiles (SM2) simultaneously to various targets, destroying them all.
APAR, Thales' Active Phased Array
Radar, is the world's most sophisticated
multi-function radar. Its non-rotating
antenna houses four faces that together
cover the full 360 degrees. Each face
consists of more than 3000 very small
radar transmitter/receiver (T/R)
elements, giving the radar its unique
capabilities and high operational
availability. The inherent agility of
APAR guarantees a high performance in
the most adverse conditions, under
severe electronic protection measures.
APAR makes use of Interrupted
Continuous Wave Illuminations (ICWI)
technology, a concept that has been
developed in the international Tri-lateral
Frigate Cooperation formed by the
Netherlands, Germany and Canada.
http://www.thales-nederland.nl/nl/news/archive/2005/april26-2005.shtml
http://www.netherlands-embassy.org/tromp/prapar.htm

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AN/TPS-59 (V)3 Tactical Missile Defense Radar
Developed for the United States Ballistic Missile Defense Organization
(BMDO) and the United States Marine Corps, the TPS-59 (V)3 is designed to
operate with HAWK and Patriot.
When integrated with HAWK, the TPS-59 (V)3/HAWK system is the most cost
effective TMD system currently in production with successfully validated
performance against ballistic missiles as well as air breathing threats.
The radar has been designed to be rapidly transported by truck, helicopter, or C-
130 cargo plane.
Performance
Frequency 1215 – 1400 Hz
Transmitter Power 46 kW
Tactical Ballistic Missiles
Range 400 nmi (740 km) with continuous
coverage to 106
ft (305 km)
Elevation Beam Steering -5º to 60º
Azimuth Sector Coverage 360º
Launch/Impact Point prediction 3-5 km circular probability for 50 – 750
km range TBMs
Surveillance Volume 95 x 10 nmi3
(603
x 106 km3
)
Air Breathing Targets
Range 300 nmi (555 km) with continuous
coverage to 105
ft (30.5 km)
Elevation Beam Steering -2º to 20º
Azimuth Sector Coverage 360º
Reliability
MTBF 2,000 hours
Availability 0.9947
Lockheed MartinRadars for Ballistic Missile Defense

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Upgraded Early Warning Radar (UEWR): U.S. early warning radars are large, fixed, phased-array
surveillance radars used to detect and track ballistic missiles directed into the United States. Upgrades to
America’s Early Warning Radar network will provide the existing forward-based radars with the capability to
support the NMD surveillance function. Prior to deployment of the SBIRS (Low) satellites, the UEWRs will
be used to detect and track objects during their midcourse phase, primarily to cue the more precise X-Band
Radar.

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Sea-Based X-Band Radar
Sea-Based X-Band Radar is a floating, self-propelled,
mobile radar station designed to operate in high winds
and heavy seas. It is part of the United States
Government's Ballistic Missile Defense System.
The Sea-Based X-Band Radar is mounted on a 5th
generation Norwegian-designed, Russian-built CS-50
semi-submersible twin-hulled oil-drilling platform.
Conversion of the platform was carried out at the
AMFELS yard in Brownsville, Texas; the radar mount
was built and mounted on the platform at the Kiewit
yard in Ingleside, Texas, near Corpus Christi. It will be
based at Adak Island in Alaska but can roam over the
Pacific Ocean to detect incoming ballistic missiles.
ST. LOUIS, Jan. 10, 2006 -- Boeing [NYSE: BA]
announced today the arrival in Hawaii of the Sea-
Based X-Band Radar (SBX) built for the U.S. Missile
Defense Agency. This marks an interim stop in the
vessel's transport operation, originating in the Gulf
of Mexico and maneuvering through the Straits of
Magellan, ultimately destined for Adak, Alaska.
http://cryptome.sabotage.org/sbx1-birdseye.htm
US Navy is deploying the HAARP platform SBX-1 to hit North Korea

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http://www.es.northropgruman.com/ASD/broshures/airborne/AWACS.pdf
Airborne Warning & Command System (AWACS)

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Airborne Warning & Command System (AWACS)

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Parameter Value
Operating Frequency 3.3Ghz
Wavelength 9.1cm
Physical Aperture Area 6m2
Effective Aperture Area 3.3m2
Number of Active Elements 5,000
Azimuth Beam Width 1.0º
Elevation Beam Width 5.0º
Scan Sector 360º
Search Solid Angle (one line) 0.55str
Total Average Power 30kW
Power-aperture Product 100kW m2
Noise Temperature 650ºK
Equipment Loss (Beam center) 9.0db
Extra Loss in Search 5.0db
Atmospheric Loss 3.2db
Total Search Loss 17.2db
Report of the
American Physical Society Study Group on
Boost-Phase Intercept Systems
for National Missile Defence
Scientific and Technical Issues
July 2003
pg. 179
AN/APY-2 Radar Characteristics
AWACS
http://www.airforce-technology.com/projects/e3awacs/e3awacs4.html
Boeing E-3 Sentry AWACS - An eagle-eyed watcher
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USA Anti – Ballistic Missiles

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In 1984 the US Army conducted the Homing Overlay experiments, which
demonstrated a successful intercept of a re-entry vehicle by a long-range ground-
launched surface-to-air missile.
This was followed in 1990 by the High Endoatmospheric Defense Interceptor (HEDI)
programm, which tested IR seekers at high velocity in the upper atmosphere to
determine how heating effects would affect their performance. The effects were less
than expected.
In 1991 an Exoatmospheric Re-entry vehicle Interception Systems (ERIS) flight
demonstrated a successful intercept at 925 km range and at an altitude of 270 km. A
second ERIS flight in 1992 missed the target RV by around 6 m.
A Ground Based Interceptor (GBI) programm started in 1992, was halted in
1993, and re-started again in 1995. Originally intended to provide an anti-ballistic
missile defence of the whole of the US from several sites located around the
coastline, the first design had a range of around 2,000 km. The provisions of the
1972 ABM Treaty limited the Russian Federation and the US to just one
interceptor site and 100 missiles, and in 1995 the GBI range requirement was
increased to 2,500 km so that only one launch site would be used.
Return to TOC

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Chronology of hit-to-kill missile tests, 16 Apr 1997 , George Lewis, MIT
Homing Overlay used a large, infrared homing interceptor, which unfurled
a fifteen foot diameter sets of spokes just prior to intercept. There was
controversy in 1993/94 over the revelation of a deception program in which a
small amount of explosive placed on the interceptor would be used to blow up
the interceptor following a near miss in order to deceive the Soviets into
believing a hit had been scored. Neither of the first two intercept attempts
came close enough to the target to employ the deception scheme, and it was
discontinued after the second flight. The target was also heated (to about 100
degrees F) prior to launch to enhance its IR signal.
Homing Overlay Tests
December 1982: First flight aborted
***February 7, 1983: First intercept attempt misses by large distance. Miss
attributed to anomalies in the sensor cooling system that prevented homing.
***May 28, 1983: Second intercept attempt misses by a large distance. The
interceptor began homing, but missed due to a failure in the guidance
electronics.
***December 1983: Third intercept attempt misses. A software error in the on-
board computer prevented the conversion of optical homing data into steering
commands.
***June 10, 1984: Fourth intercept attempt hits target. The closing speed was
said to be greater than 20,000 feet per second (6.1 km/sec). The target was
reportedly acquired at a range of "hundreds of miles"
http://www.nasm.si.edu/imagedetail.cfm?imageID=1201
http://www.fas.org/spp/eprint/lewis_tests.htm
Return to TOC

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McDonnell Douglas HEDI (High Endoatmospheric Defense Interceptor)
No true HEDI missiles were built, but technology for an
endoatmospheric hit-to-kill missile interceptor was tested by KITE
(Kinetic Kill Vehicle Integrated Technology Experiment) test
vehicles as part of the HEDI program. KITE was a rail-launched
missile based on the older Sprint nuclear-armed ABM (Anti-
Ballistic Missile). It was a two-stage solid-fueled rocket, powered by
a Hercules X-265 and a Hercules X-271 motor. The KKV (Kinetic
Kill Vehicle) was fitted with an infrared seeker, which was protected
behind a shroud during the initial high-speed flight through the
lower atmosphere. The KITE achieved an acceleration of over 200 G
immediately after launch.
http://www.designation-systems.net/dusrm/app4/hedi.html
The first KITE test flight ("KITE-1") on 26 January 1990 was
followed by a failed launch ("KITE-2") on 23 September 1991
and the second and last flight ("KITE-2A") on 26 August 1992.
The operational HEDI program had been cancelled in 1992, but
the KITE flights tested various system components like seeker,
guidance and control systems. However, no actual intercepts
were attempted.

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McDonnell Douglas HEDI (High Endoatmospheric Defense Interceptor)
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ERIS (Exo-atmospheric Reentry Interceptor Subsystem) Tests:
ERIS Lockheed was the prime contractor for this $500 million program, which was part
of SDIO's Ground-Based Interceptor Program. The ERIS program built on technology
developed as part of Homing Overlay.
***January 28, 1991: First intercept test. The ERIS kill vehicle reportedly hit and destroyed a mock
RV target. The dummy warhead was accompanied by 2.2 meter balloon "decoys," tethered to the
warhead about 180 meters apart, and the ERIS was told to home on the center one of the three
objects. About one second before impact, the kill vehicle deployed an inflatable octagonal kill
enhancement device. The intercept occurred at an altitude of 145 nautical miles (270 km) and at a
closing speed of greater than 30,000 mph (13.4 km/sec).
***May 11, 1991: Second intercept test aborted. About one minute before the ERIS was scheduled
to be launched the launch was called off because of a "telemetry anomaly" with the target, which
had already been launched. This failure apparently led the planned series of three intercept
attempts to be reduced to only two.
***March 13, 1992: Second intercept attempt. The ERIS failed to hit the target, reportedly missing
by "several meters." This time the target was accompanied by a single balloon "decoy." The decoy
and target were separated by about 20 meters and the kill vehicle flew between them. Discrimination
was accomplished using a one-color IR sensor, using data from the first test (and two-color IR data
was collected for use in the future) with the ERIS being programmed to intercept the cooler target.
The miss was apparently a result of two factors: a greater than anticipated separation between the
decoy and target and a late detection (by about 0.2 second) of the target relative to the decoy, which,
together with a pre-programmed one- second data collection period, left the kill vehicle with
insufficient time to maneuver to an intercept. The intercept attempt reportedly took place at an
altitude of 180 miles (290 km) and at a closing speed of 25,000 mph (11.2 km/sec).

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ERIS Tests:
In November 1985, Lockheed was awarded a contract to develop and test the ERIS (Exoatmospheric Reentry
Interceptor Subsystem) ballistic missile interceptor as part of the ground-based missile defense system within the SDI
(Strategic Defense Initiative) program. ERIS was to become an upper-tier system, complemented by the lower-tier
HEDI (High Endoatmospheric Defense Interceptor).
The ERIS test missiles consisted of the second and third stage (Aerojet General M56A1 + Hercules M57A1) of
surplus LGM-30A/B Minuteman I ICBMs, which boosted the hit-to-kill interceptor vehicle into space. Sensor and
guidance technology of the ERIS KKV (Kinetic Kill Vehicle) was based on the experience won by the earlier HOE
(Homing Overlay Experiment) tests. Because of technology improvments the ERIS KKV, which used an inflatable
octagonal "kill enhancer", was significantly smaller and lighter than the HOE KKV.
All ERIS tests used Orbital Sciences Aries missiles as delivery vehicles for the target RV (Reentry Vehicle). On the
first intercept attempt on 28 January 1991, the target RV deployed two balloon "decoys" on each side, but the KKV was
preprogrammed to home on the center target (i.e. the warhead). The RV was successfully destroyed at a closing speed
of more than 13.4 km/s (44000 fps) at an altitude of 270 km (145 nm). In the second test on 13 March 1992, the target
RV deployed a single decoy balloon and the KKV had to make the warhead/decoy decision by itself. Although the
seeker logic of the ERIS KKV reportedly identified warhead and decoy correctly, no hit was scored because target
detection was a bit late (partially because of preplanned test requirements), giving the KKV not enough time to
manoeuver to the intercept point.
Despite the partial failure of the second test, the ERIS test program was considered fully successful, and two of the
originally planned four tests were cancelled. Because of the changed world situation after the end of the Cold War, the
SDI program was somewhat reoriented in the early 1990s towards what was then called GPALS (Global Protection
Against Limited Strikes), and ERIS itself was not directly developed into an operational system. However, experience
and technology developed during ERIS was put to use in the current missile defense programs, like THAAD (Theater
High-Altitude Area Defense) and the GBI (Ground-Based Interceptor) missile of the GMD (Ground-Based Midcourse
Defense) system (formerly NMD; National Missile Defense).
http://www.astronautix.com/lvs/eris.htm

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Return to TOC

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FLAGE (Flexible Lightweight Agile Guided Experiment) Testing:
FLAGE (flexible lightweight agile guided experiment) - formerly known as
SR-HIT (small radar-homing intercept technology) -- was the predecessor of
the current Patriot PAC-3 ERINT interceptor. FLAGE was a small (9 inches
in diameter) highly-maneuverable, millimeter-wave radar-guided interceptor
intended for relatively short-range intercepts well within the atmosphere. The
missile spins during flight and its center of gravity and center of pressure are
reportedly very close together, making it inherently unstable. 216 small solid
rocket motors mounted in the missile body forward of its center of gravity
were used to achieve very high maneuverablity (reportedly about 100 Gs).
***January 20, 1984. First flight test. An unguided ballistic trajectory
flight to test missile performance and stability. Reportedly a success. First
of a planned series of nine flight tests.
***March 15, 1984. Second flight test. Non-homing test in which the
missile was to make a series of six pre-programmed maneuvers. Missile
became unstable during second maneuver, and its radome and fins were
torn off. Prior to the third test, ballast was added to improve the missile's
aerodynamic static margin.
***November 29, 1984. Third flight test. Non-homing test. The missile
reportedly successfully executed a series of preplanned maneuvers.
***Date?? Fourth flight test. Test was to be against a stationary target
suspended from a balloon.
***April 20, 1986. Fifth flight test. Target was a 44 inch diameter
aluminum sphere held in place at 12,000 feet (3.7 km) altitude by a balloon.
Test was a success, with missile passing through the target.

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FLAGE (Flexible Lightweight Agile Guided Experiment) Testing (continue) :
***June 27, 1986. Sixth flight test. First intercept attempt against a
simulated missile target, and the interceptor hit the target. The intercept
took place 7 seconds after the interceptor launch at an altitude of about
12,000 feet (3.7 km). There was no up-link to interceptor after its launch.
At intercept, FLAGE speed was 3,200 ft/sec (0.98 km/sec) and the target
speed was 3,800 ft/sec (1.16 km/sec). The target was launched from an
airplane and reportedly had an RCS of about 1 square meter. At the time
of test, it was described as the sixth test in a series of nine.
***May 21, 1987. Seventh flight test, second intercept attempt. The
FLAGE successfully intercepted a Lance ballistic missile (said to simulate
a Soviet SS-21 missile). The Lance reportedly had a much smaller radar
cross section than the previous targets. The intercept took place seven
seconds after the FLAGE launch, at an altitude of 12,000 feet (3.7 km). At
intercept, FLAGE speed was 3,200 ft/sec (0.98 km/sec) and the target
speed was less than 3,000 ft/sec (0.91 km/sec). The FLAGE radar
reportedly acquired the target 2 seconds before the intercept and 60 of the
216 small solid rocket motors were fired during the flight.
Following the seventh flight test, it was reported that a second flight
against a Lance missiles would be attempted in July 1987, and that a third
test might be conducted after the data from the first two tests against a
Lance were analyzed. However, I have not found anything indicating that
either test occurred.
Return to TOC

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ERINT Testing:
The ERINT (extended range interceptor) is similar to the FLAGE. It uses 180
small solid rocket thrusters to make rapid maneuvers.
ERINT launch at White Sands.
June 26, 1992. First flight test. Flight test without seeker, intended to test
missile aerodynamics. Missile reportedly successfully flew a 34.3 second pre-
programmed flight, including 5 G in-plane maneuvers.
Late August, 1992. Second flight test. Reportedly successful aerodynamic
flight, without seeker.
***June 8, 1993. Third flight test, first intercept attempt. The ERINT reportedly
missed a Lance missile target by a very small distance. The miss was
subsequently attributed to unexpected vibrations due to the solid rocket motor
thrusters.
***November 30, 1993. Fourth flight test, second intercept attempt. The ERINT
hit a Storm reentry vehicle (3.3 m long, 1 m base diameter) filled with 38 water-
filled canisters intended to simulate chemical weapons submunitions, and
reportedly destroyed all of them. The ERINT was said to weight 710 lbs at
takeoff and 350 at the intercept.
***February 15, 1994. Fifth flight test, third intercept attempt. ERINT hit a
Storm warhead filled with water, simulating a bulk chemical warhead,
destroying it.
June 2, 1994. Sixth flight test. ERINT successfully intercepted a simulated
aircraft target.

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BMDO/ARMY Extended Range Interceptor (ERINT), which was developed by Loral Vought, was a heat-to-kill weapon that used
impulse control/attitude control for end-game maneuvering. Aviation Week & Space Technology, January 17, 1994

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Raytheon - Patriot Air And Missile Defense System (PAC-3) Simulation
MIM-104 Patriot SAM System

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PAC – 1
MIM – 104A
PAC – 2
MIM – 104C
PAC - 3
Type Land-mobile, S-A Single-stage
Low-to-high-altitude
Single-stage,short-range
Low-to-high-altitude
Launcher 4-round, Mobile
trainable semi-trailer
4-round, Mobile
8-round, Mobile
Manufacturer Raytheon Raytheon (prime),
Lockheed, Siemens,
Mitsubishi
Lockheed Martin
Vought Systems
Status Not in production In production In production
Length 5.3 m 5.18 m 5.2 m
Diameter 41 cm 41 cm 25 cm
Wingspan 92 cm 92 cm 50 cm
Launch Weight 914 kg 900 kg 312 kg
Propulsion Single-stage solid
propellant RM
Single-stage solid
propellant RM
Single-stage solid
propellant RM
with piff-puffs control
Guidance Command guidance
and semi-active
homing, track-via
missile (TVM)
Command guidance
and semi-active
homing,
Hit-to-kill + lethality
enhancer 73 kg KE
blast-fragmentation with
proximity fuze

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PAC – 1
MIM – 104A
PAC – 2
MIM – 104C
PAC - 3
Max speed In excess of Mach 3 Mach 5 Mach 5
Time of Flight 9 sec – 3.5 min 9 sec – 3.5 min 9 sec – 3.5 min
Min altitude 60 m 60 m 60 m
Max altitude NA 24 km 10 – 15 km
Min Range NA 3 km -
Max Range
Anti-air
70 km 160 km 15 km
Max Range
Anti Missile
15 – 45 km

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Return to TOC

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LEAP (Lethal Exoatmospheric Projectile) Testing:
LEAP Testing
June 18, 1991. First hover test of LEAP (Hughes version). Seven second
flight, altitude about 10 feet, while tracking a target outside of the test hanger.
January 31, 1991. Successful 17 second hover flight of Rockwell-Boeing
LEAP.
LEAP FLIGHT TESTS.
Original plans called for a series of 8 LEAP flight tests, with closing speeds
ultimately reaching 10 km/second.
February 18, 1992. LEAP 1 test. Used Rockwell Advanced Hover Interceptor
Technology (AHIT) kill vehicle. Described as a success. There was a target, but
hitting it was not a test objective (officials claimed that actually hitting target
was only an "extra credit" objective). One objective of the test was to have the
interceptor pass within 400 meters of the target - actual closest approach was
418 meters.
***June 19, 1992. LEAP 2 test. White Sands LEAP test involving Hughes
version failed to hit target. The LEAP was supposed to receive target position
and speed data, but did not and used default values, resulting in miss. The
LEAP was able to track the target.
***LEAP 3 test. Originally scheduled for Sept. 1992, using
Rockwell LEAP. Test was apparently conducted in June 1993, with the LEAP
passing "within 7 m of a target traveling at 750 m/s." There appeared to be
little if any reporting on this test at the time it actually occurred.
LEAP 4 test was to have used Hughes LEAP, but apparently never took place.
LEAP
Lightweight Exoatmospheric
Projectile (LEAP) is a highly
modular, lightweight, space-
tested interceptor element for
the Standard Missile-3
Tactical Ballistic Missile
Defense Program.
http://www.raytheon.com/newsroom/photogal/sm3_l.htm

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Two-tiered, theatre-missile defence
The navy is utilising an evolutionary approach to theatre-
missile defence. Along with the BMDO it has developed a
synergistic two-tier defence based on the Standard Missile-2
BLK IV that has entered low-rate production. The Standard
Missile-2 BLK IVA provides a lower-tier area defence against
ballistic missiles in the atmosphere as well as against threat
aircraft and cruise missiles. A side-mounted imaging infrared
(IR) seeker provides the precise aimpoint accuracy required to
intercept small, high-velocity ballistic missile warheads. The IR
seeker also improves the missile's performance against aircraft
and cruise missiles in the presence of electronic counter
measures.
The SM-2 BLK IVA also has an improved, high- speed
autopilot, an improved forward-looking fuse, and a highly
lethal directional warhead. Although the SM-2 BLK IVA will
get direct (skin-on-skin) hits in most cases, the warhead is being
retained to ensure a kill in all scenarios, and maintain
performance against manoeuvring aircraft and cruise missiles.
http://www.global-defence.com/1997/ForwardFromSea.html

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Two-tiered, theatre-missile defence
The standard missile-LEAP (SM-LEAP) utilises the SM-2 BLK IV airframe,
control fins, MK72 booster and MK104 sustainer motor. In place of the warhead
and radar seeker, is a third- stage rocket motor (TSRM), a third-stage guidance
unit, and a lethal exo-atmospheric projectile (LEAP) kinetic kill vehicle. The
standard missile's first and second stages fly out on an intercept trajectory. After
second-stage separation, the third stage ignites and propels the LEAP towards
the predicted intercept point. All three stages provide the LEAP KKV with a
velocity of over four kilometres per second. Prior to reaching the impact zone,
the LEAP is ejected from the third stage and autonomously acquires and tracks
the ballistic missile with its advanced long-wave imaging infrared seeker. Using
a high-thrust, solid-propellant, divert-propulsion system the LEAP KKV
manoeuvres itself directly into the path of the incoming warhead. This
combination of accuracy, high velocity, and LEAP's 30-kilogramme mass
translates into as much kinetic energy as a city bus travelling at over 600 miles
per hour - more than enough to destroy a ballistic missile's warhead.
The SM-LEAP interceptor provides an upper-tier, theatre-wide defence against
ballistic missiles. SM-LEAP's high-velocity exo-atmospheric interceptor
provides very large defended areas with multiple-shot opportunities and
warheads often are destroyed prior to apogee, greatly reducing or eliminating
chemical, biological or nuclear debris in the defended area. LEAP can operate
down to an altitude of 70 kilometres, allowing it to intercept SCUD-class and
longer-range theatre ballistic missiles. In fact SCUDs spend most of their flight
time above 70 kilometres.
Hughes Missile Systems
Company's lethal exo-
atmospheric projectile (LEAP)
kinetic kill vehicle (KKV)
http://www.global-defence.com/1997/ForwardFromSea.html

46
Upper Tier Tests (Terrier/LEAP)
FTV-1: (Functional Technology Validation or Flight Test Vehicle). 24 September 1992. A
modified Terrier missile was fired from the USS Richmond S. Turner to test the high-altitude
aerodynamics of the missile. An 18" extension and ballast was added to the missile to
simulate the LEAP. No LEAP or target was involved. Test apparently considered to be a
success.
FTV-2: September 1993. Involved a SM-2 Block 3 interceptor launched from the USS Jouett.
Missile reportedly successfully ejected a mock- up of the Rockwell LEAP. Apparently no
target was involved.
***FTV-3: March 4, 1995 First intercept attempt for LEAP/Upper Tier, launched from the
USS Turner. LEAP failed to hit target because a guidance error during the second stage
caused the missile to fly too high, putting it in a position from which it could not make an
intercept. This test used the Hughes version of LEAP. Two earlier attempts (on February 10
and 12) to conduct this test were canceled at the last minute.
***FTV-4: March 28, 1995 Test of Rockwell version of LEAP, again launched from USS
Turner. The LEAP failed to hit the target, reportedly because the battery that supplied power
to the LEAP failed.
Return to TOC

47
The Ground Based Interceptor [GBI] is the weapon of the National Missile Defense
(NMD) system. Its mission is to intercept incoming ballistic missile warheads outside
the earth’s atmosphere (exo-atmospheric) and destroy them by force of the impact.
During flight, the GBI receives information from the NMD Battle Management,
Command, Control, and Communications (BMC3) to update the location of the
incoming ballistic missile, enabling the GBI onboard sensor system to identify and
home in on the target. The GBI would consist of a multi-stage solid propellant booster
and an exoatmospheric kill vehicle. No nuclear weapons would be used as part of the
NMD system.
The Ground Based Interceptor will have an acceleration profile and burnout velocity that
maximize the interceptor’s reach, consistent with the long-range capability of the
supporting sensors. The GBI payload will be an Exo-Atmospheric Kill Vehicle (EKV)
equipped with a high-sensitivity infrared seeker and an agile divert system to support
endgame intercepts of responsive threats at very high closing velocities. In addition, the
payload will be hardened to elevated doses of X-rays to allow operation in nuclear
environments. To limit the adverse effects of this environment on the interceptor, the
defense battle management will distribute the engagements within the available
battlespace; the larger the battlespace, the wider the separation, and the weaker the
deleterious effects of a nuclear environment. Also, to achieve high confidence of success
against all threat objects, salvos of interceptors may be launched against each credible
threat object. These salvos will be spaced in time to reduce the likelihood of correlated
errors among the intercept attempts.
http://fas.org/spp/starwars/program/gbi.htm
Each missile would contain approximately 12,595 kilograms (27,766 pounds) of solid propellant. The
exoatmospheric kill vehicle would contain approximately 9 to 14 kilograms (20 to 30 pounds) of liquid propellant.
These liquid propellants would consist of monomethylhydrazine and nitrogen tetroxide.

48
Ground Based Interceptor Launched from Vandenberg AFB

49
The GBI is to use a newly developed silo-launched booster rocket, which is optimized for the role of
exoatmospheric interceptor. To speed up EKV testing, all early interception tests used so-called
"surrogate boosters", which were Lockheed Martin PLVs (Payload Launch Vehicles) made up of
upper stages of surplus Minuteman missiles

50
IFT (Integrated Flight Test) -6 launch and intercept -- July 14, 2001 -- BMDO images
http://www.ucsusa.org/global_security/missile_defense/chronology-of-missile-defense-tests.html

51
The EKV has a sensitive, long-range electro-optical infrared seeker which allows the EKV to acquire and
track targets, and to discriminate between the intended target reentry vehicle and other objects, such as tank
fragments or decoys. This enables the GBI to be launched against a cluster of objects and subsequently
identify and intercept the targeted reentry vehicle. The EKV would also receive one or more in-flight target
updates from other ground and space-based sensors, enhance the probability of intercepting the target.
Based on this received data and its own sensors, the kill vehicle uses small on-board rockets to maneuvers so
as to collide with the target, with both demolished in the high-speed collision.
http://www.designation-systems.net/dusrm/app4/gbi.html

52
The Raytheon EKV is equipped with an infrared seeker,
which is comprised of focal plane arrays and a cooling
assembly attached to an optical telescope. The seeker
software has to detect and track all incoming objects,
discriminate warheads from decoys, and steer the EKV to a
head-on collision with a target at closing speeds of more than
25700 km/h (16000 mph). The EKV's manoeuvering system,
known as DACS (Divert and Attitude Control System), has
four rocket thrusters around the vehicle's body. The vehicle
weighs approximately 63 kg (140 lb), is 140 cm (55 in) long
and about 60 cm (24 in) in diameter.
Raytheon EKV 64 kg
(used on flight IFT-9)
In October 1990, the BMDO awarded three contracts for the
design of an EKV to Martin Marietta (now Lockheed Martin),
Hughes Missiles (now Raytheon) and Rockwell (now Boeing).
The work essentially continued the studies and tests of the HOE
(Homing Overlay Experiment) and ERIS (Exoatmospheric
Reentry Interceptor Subsystem) programs. In a first downselect
in 1995, Martin Marietta was eliminated from the EKV
competition. The NMD flight tests IFT (Integrated Flight Test)-
1 and IFT-2 (see also flight tests below) tested the Boeing and
Raytheon EKV seeker designs on 24 June 1997 and 16 January
1998, respectively. After evaluation of the results, Raytheon was
selected as prime contractor for the development of the EKV for
the operational GBI missile.
Exoatmospheric Kill Vehicle (EKV)
http://en.wikipedia.org/wiki/Ground-Based_Midcourse_DefenseExoatmospheric Kill Vehicle (EKV)

53
GBI tests, which include a kill vehicle, are designated in the IFT (Integrated Flight
Test) series (as opposed to pure booster tests, which are designated BV - see booster
section). All IFT flights up to IFT-10 have used the Lockheed Martin PLV (Payload
Launch Vehicle) as a booster, because no purpose-built GBI booster had been ready.
The PLV consists of the upper two stages of surplus LGM-30F Minuteman II ICBMs
(Aerojet SR19-AJ-1 and Hercules M57A1). The designation NLGM-30F, allocated to
Minuteman IIs converted to test vehicles, is possibly used for the PLVs. The IFT target
missiles not only deploy a dummy warhead but also balloon decoys of varying number
and size.
The first intercept attempt by the Raytheon EKV occurred during flight IFT-3 on 2 October
1999. Despite a failure in the EKV's IMU (Inertial Measurement Unit), the mock warhead was
successfully intercepted. IFT-4 on 18 January 2000 failed to intercept the warhead, because of a
failure in the EKV's sensor cooling system, and IFT-5 on 8 July 2000 was also unsuccessful
because the EKV did not separate from the booster. Tests IFT-6 on 14 July 2001 and IFT-7 on 3
December 2001 repeated IFT-5, but were the first to use the XBR (X-Band Radar) developed for
the operational system (earlier tests used an older radar and largely relied on a beacon in the
mock warhead for target tracking data). XBR performance in IFT-6 was unsatisfactory, but
IFT-6 and -7 both successfully intercepted the warhead. In all tests up to IFT-7, only a single
large decoy balloon was used, which had a much brighter IR signature than the dummy
warhead. This made it comparatively easy for the EKV's seeker logic to discriminate warhead
and decoy, and is certainly not a combat-realistic scenario. IFT-8 on 15 March 2002 used three
decoys, one large and two small ones. However, every decoy still had a significantly different IR
signature than the mock warhead, and the EKV was given discrimination data prior to the test.
IFT-9 on 14 October 2002 was presumably similar to IFT-8 (but MDA has classified decoy
information from this test on), but used the U.S. Navy's AN/SPY-1 Aegis tracking radar for the
first time. Both IFT-8 and -9 intercepted the target warhead. Flight IFT-10 failed on 11
December 2002 because the EKV again failed to separate from the booster.
IFT-6
IFT-8
Lockheed Martin PLV

54
The next two flight tests, IFT-13C and IFT-14, also used the OSC booster. IFT-13C was an all-up test
of the GMD system, where an interception was possible but not the primary objective. IFT-14, planned to
follow about two months after IFT-13C, was to be the first actual interception test with the OSC booster.
Originally planned for mid-2004, the IFT-13C/14 tests had been postponed several times. On 14
December 2004, IFT-13C was finally ready to go. However, the interceptor booster shut down
immediately before the planned lift-off, after the target had already been launched. It turned out that a
software error in a pre-launch check routine led to the abort. The test objectives of IFT-13C were to be
repeated by IFT-14 on 14 February 2005, but again the interceptor missile did not launch. This time, a
support arm, which holds the missile in the silo, did not properly retract before the attempted launch.
Flight testing eventually resumed on 13 December with a test labeled "Flight Test-1" (the IFT numbering
sequence is no longer used). This test, which was to validate GMD component interoperability, was
successful, but did not include an actual target intercept. Tests FT-2 on 1 September 2006 and FT-3a (a.k.a.
FTG-3a) on 28 September 2007 both resulted in a successful target interception. Another test in May 2007
had to be aborted after the STARS target missile had failed.
In December 2002, President Bush directed the Department of Defense to field an initial missile defense
capability by the end of 2004. This was to include ten GMD interceptors in 2004 and ten more by 2005. The
first GBI missile silos were built at Ft. Greely, Alaska, and will form (in connection with supporting
guidance system components at Eareckson AFS on Shemya Island) what is called a "Missile Defense
Testbed". The second GBI base is Vandenberg AFB, California. Because of the problems with the Lockheed
Martin BV, OSC provides all initial booster vehicles. In July 2004, the first GBI missile was installed in a
silo at Ft. Greely, and by the end of the year, five more interceptors had been deployed at that location.
Throughout 2004, it has been planned to get the system to operational alert status by the end of that year
despite the delays in the flight test program. This plan has been postponed after the failure of IFT-13C in
December. In any case, the GMD program has some way to go towards fully realistic interception tests, and
a fully functional combat ready GMD system is probably still several years in the future.
Operational System

55
Length 16.8 m (55 ft)
Diameter 1.27 m (50 in)
Weight 12,700 kg (26,000 lb)
Speed ?
Ceiling 2,000 km (1,250 miles)
Propulsion 1st
stage: Alliant Tech Orion 50SXLG solid-fueled rocket, 441 kN (99,000 lb)
2nd
stage : Alliant Tech Orion 50SXL solid-fueled rocket, 153 kN (34,500 lb)
3rd
stage: : Alliant Tech Orion 38 solid-fueled rocket, 32 kN (7,200 lb)
Warhead EKV “Hit-to-Kill” vehicle
Specifications
Data for Orbital Booster Vehicle:
Kinetic Energy Interceptor (KEI) for ICBM Intercontinental Ballistic Missile Killing

56
http://www.globalsecurity.org/space/systems/nmd.htm

57
Ground Based RADAR http://www.fas.org/spp/starwars/program/gbr.htm

58
These radars appear to have an average power of 170
kW and an antenna area of 123 square meters. This
would appear to result in a power-aperture product of
about 20 million. However, this overstates the search
capability of the XBR, which has a "thinned" array with
some 81,000 transmit-receive modules in the antenna,
only one fifth the number of radiating elements that
would be present in a fully populated phased array
antenna. This thinned array decreases the gain of the
radar by a factor of about 5, with more of the radar's
energy going into sidelobes, producing an effective
power-aperture product of less than 4 million. Fully
populating the XBR antenna would increase its effective
power-aperture by a factor of about 25. However, the
additional transmit-receive modules would greatly
increase the cost of the radar, since these solid-state
active components are the dominant cost of the system.

59

60
Return to TOC

61
DACSDACS THAADTHAAD

62
Defense News
July 20 - 26, 1992

63
http://www.defenselink.mil/specials/missiledefense/tmd-thaad.html
THAAD SYSTEM
Future Weapons: THAAD Missile

64
THAAD SYSTEM http://www.fas.org/spp/starwars/program/thaad.htm

65
http://www.defenselink.mil/specials/missiledefense/tmd-thaad.html
THAAD SYSTEM http://www.fas.org/spp/starwars/program/thaad.htm

66
THAAD Seeker Imaging IFT-10
June 10, 1999
http://www.mda.mil/mdalink/html/thaad1.html
THAAD SYSTEM
Length 6.17 m (20 ft 3 in)
Diameter Booster:34 cm (13.4 in); KV:
37 cm (14.5 in)
Weight 900 kg (2000 lb)
Speed 2,800 m/s (9,200 fps)
Ceiling 150 km (93 miles)
Range > 200 km (125 miles)
Propulsion Pratt & Whitney solid-
fuel rocket
Warhead None (“hit-to-kill”)
http://www.designation-systems.net/dusrm/app4/thaad.html

67
THAAD SYSTEM

68
THAAD MDA - February 2, 2007

69

70
Parameter Value
Operating Frequency 9.5GHz
Wavelength 3.2cm
Physical Aperture Area 9.2m2
Effective Aperture Area 6m2
Number of Active Elements 25,344
Receiving Gain (with weighting) 76,000
Azimuth Beam Width 0.6º
Elevation Beam Width 0.8º
Scan Sector 90º
Search Solid Angle (one line) 0.011str
Module Peak Power 10W
Module Average Power 2.1W
Total Average Power 54kW
Power-aperture Product 324kW m2
Noise Temperature 500ºK
Equipment Loss (Beam center) 2.8db
Extra Loss in Search 7.2db
Atmospheric Loss 5.5db
Total Search Loss 15.5db
THAAD Radar Antenna
Element and Electronics
Report of the
American Physical Society Study Group on
Boost-Phase Intercept Systems
for National Missile Defence
Scientific and Technical Issues
July 2003
pg. 177

71
Original plan for THAAD testing called for a series of 14 flight test, to be completed by March 1997, with the
third flight test being the first intercept attempt. August, 1994: Simulated THAAD launch (to an altitude of
roughly 200 feet) using a short-burn booster.
First Test: April 21, 1995: First THAAD flight test. Tested flight of interceptor and KKV sensors (observing
moon and stars), no target was involved. Labeled a success.
Second Test: July 31 or August 1, 1995: Flight test with no target. After an energy management manuever,
the THAAD velocity was higher than expected, and the missile was destroyed in order to prevent debris from
leaving the test range boundaries. This happened before the seeker shroud was dropped.
Third Test: October 13, 1995: First test with a target; however because of range safety concerns, no actual
intercept was attempted (the kill vehicle was programmed to miss by 20 meters or more). Primary purpose of
test was to collect seeker data, and the interceptor apparently performed well. However, the THAAD GBR radar
(in its first use in a flight test), which was not the prime radar for the test, malfunctioned and failed to track
either THAAD or the target.
***Fourth Test: December 13, 1995: First intercept attempt. The THAAD kill vehicle failed to hit its Storm
target. The miss was attributed to a software error which caused an unneeded kill vehicle divert maneuver,
causing the kill vehicle to run out of divert fuel before the intercept could be made. The THAAD GBR radar,
again used only in an observing role, apparently worked well.
***Fifth Test: March 22, 1996. Second intercept attempt. The THAAD interceptor missed the Hera target. The
THAAD kill vehicle did not respond to commands following separation from its booster. The failure was
attributed to a broken cable connecting the kill vehicle with its supporting electronics module.
***Sixth Test: July 15, 1996. Third intercept attempt. The THAAD kill vehicle failed again to hit its target,
although it apparently came close to it. The failure was caused by a seeker problem. It appears that the precise
cause of the seeker failure could not be conclusively determined, with loose connectors that hold electronics
boards to the back of the seeker the leading suspect. The GBR radar reportedly worked well.
***Seventh Test. March 6, 1997. Fourth intercept attempt. THAAD once again missed the target. The failure
was attributed to the THAAD divert and attitude control system, which had worked in previous tests.
THAAD Demonstration-Validation phase

72
***Eight Test, 12 May 1998, Electrical short circuit due to foreign object debris in thrust vector control
caused booster failure. Prior to the test, Pentagon officials tried to lower expectations by saying they would
consider the test successful if the missile reached the endgame. Angry with the repeated failures, the Senate
voted to cut the FY 99 funding authorization by $253.9 million, reallocating the resources to black projects.
This eliminated the rest of the money authorized in FY 99 to begin an EMD contract with Lockheed Martin.
SASC had already cut $70 million from the THAAD EMD authorization for that year. The House voted to
make Lockheed Martin liable for future tests.
***Ninth Test, 29 March 1999, Attitude control system nozzle was torn from its bracket. There were four
failures: a maneuvering thruster malfunctioned, the thruster's combustion chamber overheated, the telemetry
failed and the missile missed the target. The test was also to demonstrate the infrared indium antimonide
(InSb) seeker, closed-loop system, and (for the first time) the user operational evaluation system radar
performance against the unitary target. Lockheed Martin was penalized $15 million for the miss.
*** Tenth Test, 10 June 1999, Intercept of Hera class unitary target within the aimpoint region (an area on
the mock warhead). At this point, the goal was to field units by 2007. The interception occurred at an altitude
of just under 60 miles with both target and interceptor traveling at just under 1 mile/sec.
http://www.cdi.org/missile-defense/tests-thaad.cfm
*** Eleventh Test, 2 August 1999, Exoatmospheric intercept of Hera class separating target within the
aimpoint region (again, an area on the mock warhead). After, the Pentagon decided to skip attempting a third
interception before going into EMD (the contract was awarded June 30, 2000 , for $4 billion). If Lockheed
Martin had not achieved an interception, it would have been fined $20 million.
*** Twelve Test, 2004, THAAD is scheduled to next undergo a flight test late in FY 04, with intercepts
to be attempted in FY 05. There are 16 tests planned. MDA will start with exo-atmospheric intercepts and
then try endo-atmospheric intercepts.

73

74
Since November 2005 the THAAD Weapon System program has conducted six successful flight tests,
including three tests involving the successful intercept of threat representative targets:
*
* November 2005 – Successful missile-only flight test April 2006 – Successful integration of the entire
THAAD Weapon System including launcher, interceptor, radar and fire control system
* July 2006 – Successful seeker characterization flight test including first target intercept
* September 2006 – Flight test designated a ‘no-test’ when the HERA target malfunctioned and was
destroyed by WSMR Range Safety before the interceptor was launched; excellent ground data was acquired
* January 2007 – Successful intercept of a unitary target in THAAD’s first flight test at the PMRF
* April 2007 – Successful intercept of a unitary target
* June 2007 – Successful missile-only flight test in low endo-atmosphere
THAAD Engineering and Manufacturing Development phase (Resume)

75
21 April 1995: THAAD completed its first test flight to prove its propulsion system. There was no target in the test.
31 July 1995: THAAD failed a kill vehicle control test. The test flight was aborted. There was no target in the test.
13 October 1995: THAAD was launched to test its target-seeking system. There was no attempt to hit the target in the test.
13 December 1995: THAAD failed to hit a test target due to software errors in the missile's fuel system.
22 March 1996: THAAD failed to hit a test target due to mechanical problems with the kill vehicle's booster separation.
15 July 1996: THAAD failed to hit a test target due to a malfunction in the targeting system.
6 March 1997: THAAD failed to hit a test target due to a contamination in the electrical system.
12 May 1998: THAAD failed to hit a test target due to an electrical short circuit in the booster system. At this point,
the U.S. Congress reduced funding for the project due to repeated failures.
29 March 1999: THAAD failed to hit a test target due to multiple failures including guidance system.
10 June 1999: THAAD hit a test target in a simplified test scenario.
2 August 1999: THAAD hit a test target outside the atmosphere.
http://en.wikipedia.org/wiki/THAAD

76
THAAD Engineering and Manufacturing Development phase
In June 2000, Lockheed won the Engineering and Manufacturing Development (EMD) contract to turn the
design into a mobile tactical army fire unit. Flight tests of this system resumed with missile characterization
and full-up system tests in 2006 at WSMR, then moved to the Pacific Missile Range Facility.
On 22 November 2005, THAAD launched a missile in its first Flight EMD Test, known as FLT-01. The test
was deemed a success by Lockheed and the Pentagon.
On 11 May 2006, THAAD conducted FLT-02, the first developmental flight test to test the entire THAAD
system including interceptor, launcher, radar, and fire control system.
On 12 July 2006, THAAD conducted FLT-03, intercepting a live target missile.
On 13 September 2006, THAAD attempted to conduct the FLT-04 test. The HERA target launched but had to
be terminated in mid-flight before the launch of the FLT-04 missile. This has officially been characterized as a
"no test."
FLT-05, a missile-only test, was postponed until mid-spring 2007.
On 27 January 2007, THAAD conducted FLT-06 test, intercepting a “high endo-atmospheric” (just inside
earth’s atmosphere) unitary (non-separating) target representing a “SCUD”-type ballistic missile launched
from a mobile platform off Kauai in the Pacific Ocean.
On 6 April 2007, THAAD conducted FLT-07 test, intercepting a “mid endo-atmospheric” unitary target
missile off Kauai in the Pacific Ocean. It successfully tested THAAD's interoperability with other elements of
the MDS system. [1] [2]
On 27 October 2007, THAAD conducted a successful exo-atmospheric test at the Pacific Missile Range
Facility (PMRF) off Kauai, Hawaii. The flight test demonstrated the system's ability to detect, track and
intercept an incoming unitary target above the Earth's atmosphere. The Missile was hot-condition tested to
prove its ability to operate in extreme environments.[3][4]
THAAD was originally scheduled for deployment in 2012, but deployment has recently been accelerated to
2009.
http://en.wikipedia.org/wiki/THAAD

77
SOLO
March 2009, the first interceptor launched in Flight
Test 10 destroyed a target kill vehicle (left), and seconds
later another Thaad missile collided with a large piece
of debris tumbling from the wreckage of the first
engagement (right). This is a compilation of two
infrared images collected from aircraft monitoring the
test; the image was made public at Aviation Week’s
request.Credit: LOCKHEED MARTIN
Amy Butler, “MDA Eyes Longer-Range Thaad Options”, Aviation Week & Space Technology,
August 17, 2009, pp. 38 - 44
March 2008, first Thaad battery activated.
June 2008, Flight Test 9 intercept separating target at mid endo-atmospheric altitude.
During a Mar. 17 flight trial, the second of two Thaad interceptors, launched 12 sec. after the first, captures a
series of images using its infrared seeker. At left, in the first two photos, the seeker is observing the first
interceptor (top) closing in on the short-range target (bottom). The seeker on Interceptor 2 then captures the
actual collision of Interceptor 1 and the target (third photo). The next two images show the wreckage of the
engagement. Finally, the seeker on Interceptor 2 is viewing a large piece of debris just before impacting it. These
are low-resolution images provided at Aviation Week’s request; high-resolution versions were not
declassified.Credit: LOCKHEED MARTIN

78
Amy Butler, “MDA Eyes Longer-Range Thaad Options”, Aviation Week & Space Technology,
August 17, 2009, pp. 38 - 44
The addition of a larger, 21-in.-dia. booster appears to be the option of most interest. The Thaad
interceptor is now 14.5 in. in diameter. "The concept behind the 21 inches is that it significantly
increases the interceptor range, and by increasing range that significantly--three to four times--
increases the defended area we have on the ground with the system," says U.S. Army Col. William
Lamb, the Missile Defense Agency's Thaad project manager. He says the MDA is reviewing a
concept from prime contractor Lockheed Martin for possible inclusion in the Fiscal 2011 budget,
which is in the early stages of development.
SOLO
Return to TOC

79
Medium Extended Air Defense System (MEADS)
The MEADS system will probably be fully interconnected by data-links with other
air defence systems such as MIM-104 Patriot, THAAD and FSAF Aster. MEADS
will be both mobile and air-transportable by C-130 Hercules and A400M aircraft,
and probably also by heavy lift helicopters such as the CH-47 and CH-53, and will
in effect be an MIM-23 HAWK and MIM-104 Patriot replacement. Present plans
are to use the PAC-3 missile, possibly modified to the Missile Segment
Enhancement (MSE) standard to improve its performance. The MSE version would
have increased range and altitude, improved manoeuvrability, a downlink from the
seeker during flight, and the ability to adjust the motor thrust profile before launch.
There are expected to be two versions of the missile; a hit-to-kill missile for
intercepting ballistic missiles and a fragmentation warhead missile for use against
aircraft and air-breathing missiles.
A typical battery is planned to have six launchers, each with 12 missiles, three re-
load vehicles, each with 12 missiles, two tactical operations centers and two support
vehicles, one UHF surveillance radar, and two dual-role surveillance/engagement
radars. The manpower for a battery would be around 50 personnel, and a complete
battery would take 20 C-130 loads.
MEADS Medium Extended A
MEADS
Return to TOC

80
The Kinetic Energy Interceptor program will provide
needed additional capability to the nation’s Ballistic
Missile Defense System. The program was initially aimed
at deploying a boost-phase intercept capability by 2008.
By engaging ballistic missiles in the boost and ascent
stages of flight, the KEI will provide the nation with the
capability of defeating future sophisticated threats before
their payloads are released. The KEI program is designed
to produce interceptors capable of shooting down enemy
ballistic missiles during their boost and ascent phases of
flight. This effort will augment the midcourse and
terminal based interceptor programs currently underway
to provide a layered missile defense architecture that will
guard against potential enemy attack.
Kinetic Energy Interceptor (KEI) is a missile defense program
whose goal is to design, develop, and deploy kinetic energy-based,
mobile, ground and sea-launched missiles that can intercept and destroy enemy ballistic
missiles during their boost phase. KEI element consists of Interceptor Component,
Mobile Launcher Component, and Command, Control, Battle Management, and
Communications (C2BMC) component
Missile Defense, Kinetic Energy Interceptors

81

82
USA Weapon Systems Evolution
Return to TOC

83
Ballistic Missile Defense Organization (BMDO)
http://en.wikipedia.org/wiki/Ballistic_Missile_Defense_Organization

84
SOLO Anti – Ballistic Missiles - BMDO

85
http://www.defenselink.mil/specials/missiledefense/tmd-ntw.html

86
http://www.defenselink.mil/specials/missiledefense/tmd-pac3.html
http://www.defenselink.mil/specials/missiledefense/tmd-nads.html

87

88

89
Lockheed is in the process of developing an electronic system called `Kill Vehicle' for
the next generation of defensive missiles [29, 30]. The system is composed of four
functional subsystems, each implemented in a separate ASIS MCM as follows:
Figure: Lockheed's Kill Vehicle Architecture with ASIS MCMs.

90
The performance parameters of this system are
1,000 frames per second
256x256 Infrared (IR) pixel arrays
Small volume of a few cubic inches
Weight of less than 3 pounds
The applications of this system include:
defensive missiles
space satellites
real time data acquisition and processing
space based sensor processors
workstations and supercomputers.
The `Kill Vehicle' system shows the importance and the need for real time signal processing, which requires
very high throughput of data with very small size electronics for portability issues. This system was listed in
this chapter because it resembles the envisaged structure for the 3D demonstration device.
Every subsystem is implemented in an MCM as follows:
A Preprocessor: This is an MCM which takes analog output from Infra-Red (IR) pixels, converts the
analog signal into a digital format that is, in turn, transferred to a time dependent systolic array processor.
The preprocessor MCM contains all the analog-to-digital converters, which are mounted onto an active
silicon substrate using flip-chip technology.
Time Dependent Processor: This is a single input multiple data (SIMD) computer architecture, consisting
of a systolic array pixel mapping processor which processes light intensity patterns into patterns which can
be further analysed for identification. The systolic array time dependent processor consists of an array of
flip-chips mounted over an active substrate. The expected operation speed for this module is 164 billion
single bit instructions per second at a 40 MHz clock speed.
Object Dependent Processor: This is responsible for motor stabilisation and time averaging, target
acquisition and centroiding, target estimation and tracking, CSO (unknown acronym) resolution, and
colour discrimination. This is a 64-bit processor designed to operate at 200 MIPS or more.
Guidance and Control Processor: This controls and directs actions to the kill vehicle propulsion system.
The architecture of this processor is similar to the architecture of the Object Dependent Processor.
Return to TOC

91
Space Based Infrared System

92
SBIRS Mission Overview - Lockheed Martin

93
SBIRS GEO-2 Launch Coverage

94

95

96
The Space-Based Infrared System (SBIRS): SBIRS is an additional element that future MD systems will
utilize. SBIRS (High) is being developed by the Air Force as part of the early warning system upgrade,
which will replace the Defense Support Program (DSP) satellites. In its MD mission, the SBIRS (High)
constellation of sensor satellites will acquire and track ballistic missiles throughout their trajectory. This
information will provide the earliest possible trajectory estimate to the BM/C3 element. By providing this
“over-the-horizon” precision tracking data to the MD system, the effective MD battle space is expanded to
permit interceptors to be launched before threats come within range of the XBR, which is critical for
effective Missile Defense.
http://www.defenselink.mil/specials/missiledefense/sbirs.html

97
The Midcource Space Experiment
(MSX) carries an array of sensors
to monitor the spacecraft’s own
environment, as well as the environment
in which enemy missiles andentry
vehicle will be observed.
IEEE Spectrum, September 1997, pg.53

98
Telescopes for Midcource Space Experiment (MSX) various sensors are mounted to a common optical
that holds them in close alignment so that observation through one instrument matches those from
another, even in different portions of the spectrum
IEEE Spectrum, September 1997, pg.53 Return to TOC

99
Arrow Missile System http://www.army-technology.com/projects/arrow2/index.html#arrow22
An Arrow weapon system battery is equipped with typically four or eight launch trailers, each with six launch
tubes and ready-to-fire missiles, a truck mounted Hazelnut Tree launch control centre, a truck mounted
communications centre, a trailer mounted Citron Tree fire control centre and the units of a mobile Green
Pine radar system.
Israel's Arrow Missile Defense System

100
Arrow Missile System
The missile has a dual mode seeker with a passive infrared seeker for the tracking of tactical
ballistic missiles and an active radar seeker used to home on air breathing targets at low
altitudes.
http://www.army-technology.com/projects/arrow2/index.html#arrow22
The Elta Green Pine early warning and
fire control radar for the Arrow system.
The radar can detect targets at ranges
up to about 500km and is able to track
targets at speeds over 3,000m/s.
The missile launch platoon consists of the Hazelnut Tree truck-
mounted Launch Control Centre (LCC), developed by IAI MLM,
with four or eight missile launch trailers. The entire launch
platoon is mobile and able to relocate to a new site. After firing the
launchers can be reloaded in an hour.
Arrow-2 ASIP Intercepts a Ballistic Missile Target
Return to TOC

101
http://www.new-factoria.ru/missile/wobb/samp_t/samp_t.shtml
Aster Missile
Control flaps are associated with four powder maneuver rockets at the center of gravity of the missile
(also referred to as PIF-PAF for Pilotage induit en force—Pilotage aérodynamique en force).
Models of the Aster 30 and Aster 15 side
by side; note the difference between the
boosters.
http://encyclopedia.thefreedictionary.com/Aster+surface-to-air+missile
MBDA-Aster 15 y 30, Misil Antimisil.mp4

102
Aster 30 SAMP/T – Surface-to-Air Missile Platform / Terrain
A SAMP/T battery includes: command and control vehicle, Arabel radar and up to six
Transporter Erector Launcher (TEL) vehicles, each with eight missiles and a store of
reload missiles.
http://www.army-technology.com/projects/aster-30/

103
Aster 30 SAMP/T – Surface-to-Air Missile Platform / Terrain
The SAMP/T uses an upgraded version of the Arabel radar,
with improved performance developed under the Aster 30
block 1 upgrade program, in order to extend the system's
capability against higher speed targets and higher altitude
targets. The SAMP/T system can intercept at 600km range
(short range ballistic missile targets).
The Thales Arabel radar is a 3D phased array radar for
surveillance, tracking and missile guidance. The rectangular,
4,000-element, phased array antenna rotates at one revolution
a second. Arabel operates in the eight to 13GHz X-band (I/J-
band) with 360° azimuthal and -5° to 90° elevation scanning.
The system can track up to 100 targets simultaneously and
manage the uplink transmission of command update data to
16 missiles simultaneously. The standard Arabel radar
operates at 150kW peak power and has a range of 100km.
The beam can be shaped to optimise the performance. The
radar uses frequency agility and pulse compression ECCM
(Electronic Counter-Countermeasures) techniques.
Arabel Radar http://www.miltech.gr/Projects_ARABEL%20FCS_3_7.htm#Downloads

104
ASTER 30 BLOCK 1 MISSILES
The Aster 30 missile has a tandem first stage solid propellant booster motor which
is jettisoned after launch and turn-over and before the mid-course phase. The first
stage booster motor, developed by Fiat Avio, has length 2.3m, weight 340kg, burn
time 3.5 seconds. It has two steerable nozzles to provide the missile with thrust
vector control during the initial stage of flight.
After jettisoning the first stage booster motor, the second stage missile has a
weight of 110kg, length of 2.6m and diameter of 18cm. The body of the missile
carries four long rectangular wings and four blunt-tipped triangular control fins at
the rear. The second stage missile is fitted with solid propellant sustainer motor.
The sustainer motor efflux tube carries the uplink receiver and the fin actuators.
The missile uses inertial mid-course guidance, with guidance correction update data being transmitted from the
ground-based fire control centre via the Arabel multifunction radar's uplink data channel. The Sagem Agyle
inertial guidance unit is fitted with a Sistemi Inersiali inertial guidance reference system and a Sagem miniature
laser gyroscope.
The missile uses 'Pilotage en Force' (PIF) fine-controlled side thrust exhaust for manoeuvrability in the final
phase of flight just before intercept, to ensure that the missile is within 2m of the target when the warhead is
detonated. The missile's PIF system comprises a solid propellant gas generator which exhausts through four
lateral nozzles in the long rectangular wings at a point close to the missile's centre of gravity.
The missile does not role in the final phase of flight. The guidance control system commands the PIF system to
exhaust through one or two nozzles generating a controlled sideways thrust pulling up to 60g acceleration.
The missile and the target approach each other on a reciprocal flight path. As the missile approaches the target
in the terminal phase, the missile uses an active pulse Doppler radar seeker, a derivative of the AD4 seeker
design (Air to Air MICA’s seeker) which incorporates a high-power travelling wave tube transmitter and wide
antenna deflection, to home in on the target.

105
ASTER 30 BLOCK 1 MISSILES (continue)
The seeker is laid on the target using data transmitted via the ground to missile
uplink. Once seeker lock-on has been conformed the missile operates
autonomously. The modifications to the seeker include higher closing velocity
capability, an adjustment to the duty cycle to increase the transmitted power, an
additional high resolution range function, and modified target lock-on and
tracking algorithms.
The seeker has ECCM including home on jam and clutter suppression.
The programmable J-band pulse Doppler AD4A radar seeker
manufactured by Thales and Selex Sistemi Integrati, operates at 12GHz to
18GHz.
The missile, which weighs typically 100kg at target intercept, is fitted with a 15kg directional blast fragmentation
warhead designed by Fiat Avio and MBDA. The warhead is fitted with a Ku-band proximity fuse, which generates
a constant working pseudo random phase digital coded waveform. The warhead is loaded with two types of
fragments, 4g and larger fragments, which are directed towards the target.
The maximum speed of Aster 30 is 1.4km/sec. Aster 30 has the capability to intercept
targets at altitudes from 50m to 20km. Against aircraft targets flying at altitudes
above 3km, the maximum range of the Aster 30 is 100km. At aircraft targets with
altitudes below 3km, the range of Aster 30 is 50km.
Performance

106
http://encyclopedia.thefreedictionary.com/Aster+surface-to-air+missile
In May 1996, trials of the Aster 15 active electromagnetical final guidance system against live targets began.
All six attempts were successful:
8 April 1997: interception of a C22 target simulating a subsonic anti-ship missile,
flying at 10 metres, at a distance of 7 kilometers.
23 May 1997: Direct impact on an Exocet anti-ship missile of the first generation, at 9 kilometers,
to protect a distant ship (7 kilometers).
This was the first "hit-to-kill" interception ever against an anti-ship missile.
13 November 1997: interception of a C22 target in very low flight in a strong countermeasures environment.
In this test, the Aster was not armed with its military warhead so that the distance between
the Aster and the target could be recorded. The C22 was recovered bearing two strong cuts
due to the fins of the Aster missile.
30 December 1997: Interception of a live C22 target by an Aster 30 at a distance of 30 kilometers,
an altitude of 11,000 meters, and a speed of 900 km/h. The Aster climbed up to 15,000
meters before falling on the target at a speed of 2880 km/h. The closest distance between
the Aster and the C22 was four meters.
29 June 2001 : Interception of a Arabel missile in low altitude, in less than five seconds.
In 2001 : Interception by the Aster 15 of a target simulating an aircraft flying at Mach-1 at an altitude
of 100 meters.
Aster 15 Aster Block 2 Missile Shield

107
Aster 15 Aster 30
Function Short/Medium range
surface-to-air anti-
aircraft and anti-missile
Long range surface-to-
air anti-aircraft and
anti-missile
Manufacturer MBDA MBDA
Entered in Service 2001 2001
Propulsion Solid propellant two-
stage rocket
Solid propellant two-
stage rocket
Launch ass 310 kg 510 kg
Length 4.2 m 4.2 m
Diameter 180 mm 180 mm
Speed Mach 3 (1000 m/s) Mach 4.5 (1,400 m/s)
Range 1.7 – 30 km 3 – 120 km
Ceiling 13 km 20 km
Warhead 15 kg directional blast
fragmentation
(4gr and larger)
15 kg directional blast
fragmentation
(4gr and larger)
Guidance Uplink, terminal Active
Pulse Dopler A4D (J
band) Radar
Uplink, terminal Active
Pulse Dopler A4D (J
band) Radar
Maneuver Pilotage in Force (PIF) Pilotage in Force (PIF)
Proximity Fuze Ku band PF Ku band PF
http://en.wikipedia.org/wiki/MBDA_Aster http://www.army-technology.com/projects/aster-30/
Return to TOC

108
SH-01 'Galosh' anti-ballistic missiles paraded in Moscow in 1966
RUSIA’s Anti-Ballistic Missiles

109
SA-10 'Grumble' TEL vehicle with four
missile canisters in the launching
position
(Jane's/Christopher F Foss)
SA-12 'Giant' TEL vehicle in
the foreground, with a
'Gladiator' TEL behind
(Jane's/Christopher F Foss)
Antey S-300V/SA-12 Gladiator/Giant
S-300V (SA-12)
The Russian S-300 SAM
Return to TOC

110
http://www.dtig.org/docs/S-300_Familie.pdf

111
SOLO
http://en.wikipedia.org/wiki/SA-21
Family S-300P (SA-10( S-400 (SA-21( S-300V (SA-12(
Favorit Triumf Antey-2500
Missile S-300P
S-
300PT
S-
300PS
S-
300PM
S-
300PM
S-
300PM
U
S-300PMU1 S-300PMU2 S-300PMU3 S-300VM
5V55K 5V55R 5V55R
UD
48N6
48N6E
48N6E2 48
N6
DM
9M96
9M96E
9M96E2 40N6 9M82 9M83 9M82M
Initial NATO
Nomenclature
SA-
10A
SA-
10B
SA-
10C
SA-10D SA-10E SA-10F SA-10F SA-12B SA-12A
Grumbl
e A
Grumbl
e B
Grumbl
e C
Grumble D Grumble E Gargoyle
A
Gargoyle B Giant Gladiator
Revised NATO
Nomenclature
SA-
10A
SA-
10B
SA-
10C
SA-20A SA-20B SA-21A SA-21B SA-
12A/B
SA-12A/B
Grumbl
e A
Grumbl
e B
Grumbl
e C
Gargoyle A Gargoyle B Growler A Growler B Giant Gladiator
Target Low-
altitude
jet
Low-
altitude
jet
Low-
altitude
jet
Low-altitude
jet, TBM
Low-altitude
jet, TBM
?? TBM Anti-aircraft
mainly
?? TBM Anti-
aircraft
mainly
TBM,
aircraft
Range (km( 47 75 90 150
TBM 40
3~200 120
-
250
?
2.5~40 2.5~120 400-
450
13~100
tbm:13/
40
6~75
TBM:
6/40
200
TBM 40
Altitude (km( - 0.025~
25
0.025~
25
0.025~27 0.01~27 ?? 0.005~25 0.005~30 185 0.1~30
TBM
2~25
0.025~25
TBM 2~25
0.025~30
TBM 30
Kill-probability - - - - - ?? 90%aircraft / 80% TBM ?? 60%(high(
80%~90% (low(
96%
Reaction time - - - - - ?? - ?? 15 7
http://www.globalsecurity.org/military/world/russia/s-300-list.htm
S-300 Series Tactical and Technical Performance

112
Missile S-300P
S-
300PT
S-
300PS
S-
300PM
S-
300PM
S-
300PM
U
5V55K 5V55R 5V55R
UD
48N6
48N6E
48N6E2 48
N6
DM
9M96
9M96E
9M96E2 40
N
6
9M8
2
9M83 9M82M
Initial NATO
Nomenclature
SA-
10A
SA-
10B
SA-
10C
SA-10D SA-10E SA-10F SA-10F SA-
12B
SA-12A
Grumbl
e A
Grumbl
e B
Grumbl
e C
A
Gargoyle B Gian
t
Gladiator
Revised NATO
Nomenclature
SA-
10A
SA-
10B
SA-
10C
SA-20A SA-20B SA-21A SA-21B SA-
12A/
B
SA-12A/B
Grumbl
e A
Grumbl
e B
Grumbl
e C
Gargoyle A Gargoyle B Growler A Growler B Gian
t
Gladiator
Target Low-
altitude
jet
Low-
altitude
jet
Low-
altitude
jet
Low-altitude
jet, TBM
Low-altitude
jet, TBM
mainly
?? TB
M
Anti-
aircraft
mainly
TBM,
aircraft
S-300 Series Tactical and Technical Performance (continue – 1)

113
Missile S-300P
S-
300PT
S-
300PS
S-
300PM
S-
300PM
S-
300PM
U
5V55K 5V55R 5V55R
UD
48N6
48N6E
48N6E2 48
N6
DM
9M96
9M96E
9M96E2 40
N
6
9M8
2
9M83 9M82M
Target Low-
altitude
jet
Low-
altitude
jet
Low-
altitude
jet
Low-altitude
jet, TBM
Low-altitude
jet, TBM
mainly
?? TB
M
Anti-
aircraft
mainly
TBM,
aircraft
Range (km( 47 75 90 150
TBM 40
3~200 120
-
250
?
2.5~40 2.5~120 40
0-
45
0
13~
100
tbm:
13/4
0
6~75
TBM:
6/40
200
TBM 40
Altitude (km( - 0.025~
25
0.025~
25
0.025~27 0.01~27 ?? 0.005~25 0.005~30 18
5
0.1~
30
TB
M
2~2
5
0.025~25
TBM 2~25
0.025~30
TBM 30
Kill-probability - - - - - ?? 90%aircraft / 80% TBM ?? 60%(high(
80%~90% (low(
96%
Reaction time
(s(
- - - - - ?? - ?? 15 7
Guidance
system
- - - - Command + radio TVM Command
+?
?? Command + active radar homing ?? Inertial + Command + semi-active
radar homing
Launch Four cylinder dual-mounted vertical launch Each cylinder 4 / 4 drum dual-
mounted vertical launch
?? double row canisters
4 cylinders in a row canisters
vertical launch

114
Missile S-300P
S-
300PT
S-
300PS
S-
300PM
S-
300PM
S-
300PM
U
5V55K 5V55R 5V55R
UD
48N6
48N6E
48N6E2 48
N6
DM
9M96
9M96E
9M96E2 40
N
6
9M8
2
9M83 9M82M
Initial NATO
Nomenclature
SA-
10A
SA-
10B
SA-
10C
SA-10D SA-10E SA-10F SA-10F SA-
12B
SA-12A
Grumbl
e A
Grumbl
e B
Grumbl
e C
A
Gargoyle B Gian
t
Gladiator
Target Low-
altitude
jet
Low-
altitude
jet
Low-
altitude
jet
Low-altitude
jet, TBM
Low-altitude
jet, TBM
mainly
?? TB
M
Anti-
aircraft
mainly
TBM,
aircraft
Length (m( - - 7.25 7.5 - ?? - - ?? 9.91
8
7.8 -
Diameter (mm( - - 508 515 - ?? - - ?? 715 715 -
launch mass
(kg(
- 1664 1804 1799 About 1,800 ?? 333 420 ?? 469
0
2318 -
flight speed
(m/s(
- 1860 1900 2000 2200 ?? 1000 900 ?? 240
0
1700 -
Acceleration
(g(
- - 25 25 - - ?? 30~60 20~60 ?? 20 20 -
Warhead (kg( - 133 143 143 180 ?? 24 24 ?? Directional Fragmentation
Propulsion Single-stage high-thrust solid rocket motor Two solid rocket motors

115
http://www.ausairpower.net/TE-Asia-Sams-Pt2.pdf
Russia S-300 Family
http://www.ausairpower.net/APA-Grumble-Gargoyle.html

116

117
http://
www.strategycenter.net/research/pubI
D.93/pub_detail.asp
S-300 and S-400 Missiles: The larger
48N6E “Favorit,” which arms later
models of the S-300 system, and the
more compact 9M96E and 9M96E2
missiles of the S-400 system. Photo:
RD Fisher
http://www.defence-update.com/products/a/antey-2500.htm9M96E and 9M96E2

118
http://en.wikipedia.org/wiki/S-300
Russia S-300 PT (SA-10)
The S-300PT (transliterated from Russian С-300П, NATO reporting name SA-10a GRUMBLE) is the
original version of the S-300 system which became operational in 1978. In 1987 over 80 of these sites
were active, mainly in the area around Moscow. The P suffix stand for PVO-Strany (air defence
system). An S-300PT unit consists of a 36D6 (NATO reporting name TIN SHIELD) surveillance
radar, a 30N6 (FLAP LID) fire control system and 5P85-1 launch vehicles. The 5P85-1 vehicle is a
semi-trailer truck. Usually a 76N6 (CLAM SHELL) low altitude detection radar is also a part of the
unit.[2][3]
This system broke substantial new ground, including the use of a phased array radar and multiple
engagements on the same FCS. Nevertheless, it had some limitations. It took over 1 hour to set up this
semi-mobile system for firing and the hot vertical launch method employed scorched the TEL.[4]
It was originally intended to fit the Track Via Missile (TVM) guidance system onto this model.
However, the TVM system had problems tracking targets below 500m. Rather than accept the
limitation, the Soviets decided that the tracking of low altitude targets was a must and decided to use a
pure command-guidance system until the TVM head was ready[4]. This allowed the minimum
engagement altitude to be set at 25m.

119
A single S-300-PM missile TEL ready to fire. Photo by Naval Expeditionary
Warfare Training.

120
Russia’s S-300PMU-1/2 (SA-20)
The S-300PMU-1 (Russian C-300ПМУ-1,US DoD designation SA-20A, NATO reporting name SA-20
GARGOYLE) was also introduced in 1992 with the new and larger 48N6 missiles for the first time in a land-
based system and introduced all the same performance improvements from the S300FM version including
the increased speed, range, TVM guidance and ABM capability. The warhead is slightly smaller than the
naval version at 143 kg (315 lb). This version also saw the introduction of the new and more capable 30N6E
TOMB STONE radar.
The S-300PMU-1 was introduced in 1999 and for the first time introduces several different kinds of
missiles in a single system. In addition to the 5V55R, 48N6E and 48N6E2 missiles the S-300PMU-1 can
utilise two new missiles, the 9M96E1 and 9M96E2. Both are significantly smaller than the previous missiles
at 330 and 420 kg (728 and 926 lb respectively) and carry smaller 24 kg (53 lb) warhead. The 9M96E1 has
an engagement range of 1-40 km (1-25 mi) and the 9M96E2 of 1-120 km (1-75 mi). They are still carried 4
per TEL. Rather than just relying on aerodynamic fins for manoeuvring, they use a gas-dynamic system
which allows them to have an excellent probability of kill (Pk) despite the much smaller warhead. The Pk is
estimated at 0.7 against a tactical ballistic missile for either missile. The S-300PMU-1 typically uses the
83M6E command and control system, although it is also compatible with the older Baikal-1E and Senezh-
M1E CCS command and control systems. The 83M6E system incorporates the 64N6E (BIG BIRD)
surveillance/detection radar. The fire control/illumination and guidance radar used is the 30N6E(1),
optionally matched with a 76N6 low altitude detection radar and a 96L6E all altitude detection radar. The
83M6E command and control system can control up to 12 TELs, both the self propelled 5P85SE vehicle
and the 5P85TE towed launchers. Generally support vehicles are also included, such as the 40V6M tow
vehicle, intended for lifting of the antenna post.[6]

121
http://en.wikipedia.org/wiki/S-300Russia’s S-300PMU-1/2 (SA-20)
The S-300PMU-2 Favorit (Russian C-300ПМУ-2 Фаворит – Favourite, DoD
designation SA-20B), introduced in 1997, is an upgrade to the S-300PMU-1 with
range extended once again to 195 km (121 mi) with the introduction of the 48N6E2
missile. This system is apparently capable against not just short range ballistic
missiles, but now also medium range tactical ballistic missiles. It uses the 83M6E2
command and control system, consisting of the 54K6E2 command post vehicle and
the 64N6E2 surveillance/detection radar. It employs the 30N6E2 fire
control/illumination and guidance radar. Like the S-300PMU-1, 12 TELs can be
controlled, with any mix of 5P85SE2 self propelled and 5P85TE2 trailer launchers.
Optionally it can make use of the 96L6E all altitude detection radar and 76N6 low
altitude detection radar, just like the S-300PMU-1.[1]
S-300PMU S-300PMU1 S-300PMU2
Missile Model 5V55U 48N6E 48N6E2
Maximum Velocity 2,000 m/s 2,000 m/s 2,000 m/s
Launch Weight 1,470 kg 1,780 kg 1,800 kg
Range (vs Aircraft) 150 km 150 km 195 km
Range (vs Missile) 35~40 km 40 km 40~50 km
Altitude 75 km 75 km 95 km
Guidance Semi-Active
Radar
TVM TVM
http://www.sinadefence.com/
army/surfacetoairmissile/s300.asp

122
Russia S-300 Family
S-300PMU-2 vehicles. From left to right: 64N6E2 detection radar, 54K6E2
command post and 5P85 TEL.

123
S-300PMU Launch Complex (Regiment)
Designation
NATO
codename
Qty Systems Purpose
5P85T 32 S-300PMU Truck-towed TEL based on KrAZ-260, each carrying four missile transport-launch containers
(TLC(
5P85SE
(master(
5P85DE (slave(
16
16
S-300PMU1/PMU2 Self-propelled 8X8 TEL based on MAZ-543, each carrying four transport-launch containers (TLC(
30N6E(2( Flap Lid B
(Tomb Stone(
8 S-300PMU/PMU1/PMU2 Phased-array illumination and guidance radar
76N6 Clam Shell 8 S-300PMU/PMU1/PMU2 Low-altitude early warning radar
96L6E 8 S-300PMU1/PMU2 Detection and target designation radar
83M6E(2( 1 S-300PMU/PMU1/PMU2 Command post including 54K6E(2( combat control system and 64N6E(2( early warning radar
54K6E(2( 1 S-300PMU/PMU1/PMU2 Combat control system
64N6E(2( Big Bird 1 S-300PMU/PMU1/PMU2 Early warning radar and IFF interceptor
30N6E Flap Lid B: The 30N6E
Flap Lid B phased-array
illumination and guidance
radar (Source: Chinese
Internet)
64N6E: The 64N6E early
warning radar (Source:
Chinese Internet)
Battery Command Centre: The
battery command post mounted on a
MAZ-543 truck (Source: Chinese
Internet)
Missile Transloader : The
MAZ-7910 transloader used
to re-supply the S-300PMU
system with spare missiles
(Source: Chinese Internet)
http://www.sinadefence.com/army/surfacetoairmissile/s300.asp

124
Russia’s S-300PMU-3/S-400 Triumf ( (SA-X-21)
The S-400 Triumf (Russian: C-400 «Триумф»; English: triumph) is a new generation of anti-
aircraft/anti-missile weapon system complex developed by the Almaz Central Design Bureau as an
upgrade of the S-300 family. Its NATO reporting name is SA-21 Growler. The S-400 was previously
known as S-300PMU-3. It overshadows the capabilities of the other systems from the S-300 series,
and its range is 2 times greater than that of the MIM-104 Patriot system.[1][2]
Russian sources have claimed the S-400 is capable of detecting and destroying targets out to a range
of 400km (250 miles), such as aircraft, cruise missiles and ballistic missiles, including those with a
range of 3,500 km and a speed of 3 miles per second and stealth aircraft.[3]
The S-300PMU-3/S-400 Triumf (Russian C-300ПМУ-3/С-400 Триумф – triumph, DoD designation
SA-X-21) was introduced in 1999 and features a new, much larger missile with 2 per TEL
Specifications
• The S-400 is intended to intercept and destroy airborne targets at a distance of up to 400 km (250
miles).[2]
• The ABM capabilities are near the maximum allowed under the (now void)
Anti-Ballistic Missile Treaty.
• The radar system is claimed to possess advanced capabilities against low flying and (possibly) low RCS
targets.[14][15]
• Detection ranges of 500-600km have been theorized for future radars.[2]

125
The S-300V/S-300VM/Antey-2500 is the
world's only truly mobile Anti Ballistic
Missile system, and later variants are
claimed to be capable of intercepting 4.5
km/sec reentry speed targets. The large
size of the Grill Pan phased array and
TELAR command link and illuminator
antennas is evident. The system provides
the capability to engage very low RCS
aircraft at ranges in excess of 100
nautical miles (Rosvooruzheniye).
http://www.ausairpower.net/APA-Giant-Gladiator.html
9A83 TELAR Deployment
9A83 TELAR Deployed

126

127
9S32 Grill Pan
Target Tracking &
Missile Guidance
9M82 Giant SAM
9M83 Gladiator SAM
9S15 Bill Board
Surveillance

128
9M82 Giant SAM
9M83 Gladiator SAM
The smaller 9M83 Gladiator SAM/ABM is intended to engage aerial targets at all altitudes,
including cruise missiles, and smaller TBMs. The much larger 9M82 Giant has higher
kinematic performance and is intended to kill IRBMs, SRAM class supersonic missiles, but
also standoff jamming aircraft at long ranges. Both weapons employ two solid propellant
stages, with thrust vector control of the first stage (10,225 lb/4,636 kg mass in the Giant and
cca 5,000 lb/2275 kg in the Gladiator) and aerodynamic control of the 2,800 lb (1,200 kg)
second stage, using four servo driven fins, and four fixed stabilizers. The guidance and control
packages, and much of the weapon airframes are identical, the principal distinction being the
bigger booster stage of the Giant and its larger stabilizers.
A cold start ejector is used to expel the missile from the launch tube, the first stage burns for
about 20 seconds, upon which the missile transitions to its midcourse sustainer. During
midcourse flight the missile employs inertial navigation with the option of command link
updates. In the former mode it transitions to its semi-active homing seeker during the final 10
seconds of flight, in the latter 3 seconds before impact - a technique preferred for heavy
jamming environments. Russian sources claim the semi-active seeker can lock on to a 0.05
square metre RCS target from 16.2 nautical miles. The midcourse guidance system attempts to
fly the most energy efficient trajectory to maximize range. A two channel radio proximity fuse is
used to initiate the 330 lb (150 kg) class smart warhead which has a controllable fragmentation
pattern to maximize effect.

129
9M82 Giant SAM
9M83 Gladiator SAM
The engagement envelope of the baseline Gladiator is between 80 ft AGL to 80 kft, and ranges of
3.2 to 40 nautical miles, the Giant between 3,200 ft AGL to 100 kft, and ranges of 7 to 54 nautical
miles. The system can launch the missiles at 1.5 second intervals, and a battalion with four batteries
can engage 24 targets concurrently, with 2 missiles per target, and has a complement of between 96
and 192 missiles available for launch on TELAR/TELs. A TELAR can arm a missile for launch in
15 seconds, with a 40 second time to prepare a TELAR for an engagement, and 5 minute deploy and
stow times - a genuine shoot and scoot capability.
(Continue from previous slide)
The cited single shot kill probabilities for the Gladiator are 50% to 65% against TBMs and 70%
to 90% against aircraft, for the Giant 40% to 60% against IRBMs and 50% to 70% against the
AGM-69 SRAM - ballistic missiles with re-entry velocities of up to 3 km/s can be engaged.
The Soviets were terrified of TAC's EF-111A force and equipped the S-300V system with a facility
for passive targeting of support jammers. The 9S15, 9S19 and 9S32 have receiver channels for
sidelobe jamming cancellation and these are used to produce very accurate bearings to the airborne
jammer, this bearing information is then used to develop angular tracks. The angular tracks are then
processed by the 9S457 command post to estimate range, and the 9S32 then develops an estimated
track for the target jammer. A Giant missile is then launched and steered by command link until it
acquires the target.

130
The specialized 9S19 Imbir is a high power-aperture, coherent, X-band phased
array designed for the rapid acquisition and initial tracking of inbound ballistic
missiles within a 90 degree sector. To that effect it uses a large passive phase
technology transmissive array, using a conceptually similar space feed technique
to the MPQ-53 and 30N6 series radars, producing a narrow 0.5 degree pencil
beam main-lobe. The primary search waveform is chirped to provide a very high
pulse compression ratio intended to provide very high range resolution of small
targets. The design uses a high power Travelling Wave Tube (TWT) source, very
low side-lobes and frequency hopping techniques to provide good resistance to
jamming.
Three primary operating modes are used. In the first the 9S19 scans a 90 degree
sector in azimuth, between 26 and 75 degrees in elevation, to detect inbound
Pershing class IRBMs within a 40 to 95 nautical mile range box, feeding position
and kinematic data for up to 16 targets to the 9S457 command post. The second
mode is intended to detect and track supersonic missiles such as the AGM-69
SRAM, and sweeps a narrower 60 degree sector in azimuth, between 9 and 50
degrees in elevation, within a range box between 10 and 90 nautical miles,
generating target position and velocity updates at 2 second intervals. The third
mode is intended to acquire aircraft in severe jamming environments, with similar
angular and range parameters to the second mode. The radar is claimed to
produce RMS angular errors of around 12 to 15 minutes of arc, and a range error
of a mere 70 metres (at max range 0.04%!). The peak power rating remains
undisclosed.
In function the 9S19 most closely resembles much newer Western X-band ABM
radars, but is implemented using seventies generation antenna and transmitter
technology, and is fully mobile unlike the semimobile US THAAD X-band radar,
and Israeli Green Pine.

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