Jericho II and III, Israeli Ballistic Missile

Jericho is a general designation given to the Israeli ballistic missiles. The name is taken from the first development contract signed between Israel and Dassault in 1963, with the codename as a reference to the Biblical city of Jericho. Like much connected to the nuclear weapons program of Israel, exact details are difficult to find.

Jericho II

The Jericho II is a solid fuel, two-stage medium-range ballistic missile system. There was a series of test launches into the Mediterranean from 1987 to 1992, the longest at around 1,300 km, mostly from the facility at Palmachim, south of Tel Aviv. Jane's reports that a test launch of 1,400 km is believed to have taken place from South Africa's Overberg Test Range in June 1989.

The Jericho II is 14.0 m long and 1.56 m wide, with a reported launch weight of 26,000 kg (although an alternative launch weight of 21,935 kg has been suggested). It has a 1,000 kg payload, capable of carrying a considerable amount of high explosives or a 1 MT yield nuclear warhead. It uses a two-stage solid propellant engine with a separating warhead. The missile can be launched from a silo, a railroad flat truck, or a mobile vehicle. This gives it the ability to be hidden, moved quickly, or kept in a hardened silo, ensuring survival against any attack.

The Jericho II forms the basis of the three-stage, 23 ton Shavit NEXT satellite launcher, first launched in 1988 from Palmachim. From the performance of Shavit it has been estimated that as a ballistic missile it has a maximum range of about 7,800 km with a 500 kg payload.

Jericho III

It is estimated that the Jericho III entered service by 2008. The Jericho III is believed to have a three-stage solid propellant and a payload of 1,000 to 1,300 kg. It is possible for the missile to be equipped with a single 750 kg nuclear warhead or two or three low yield MIRV warheads. It has an estimated launch weight of 30,000 kg and a length of 15.5 m with a width of 1.56 m. It likely is similar to an upgraded Shavit space launch vehicle. It probably has longer first and second-stage motors. It is estimated that it has a range of 4,800 to 11,500 km (2,982 to 7,180 miles), and probably significantly greater with a smaller payload of 350 kg (the size of one smaller Israeli nuclear warhead). It is believed that the Jericho 3 is inertial guided with a radar guided warhead and silo-based with mobile vehicle and railcar capabilities.

According to an official report which was submitted to the American congress in 2004, it may be that with a payload of 1,000 kg the Jericho 3 gives Israel nuclear strike capabilities within the entire Middle East, Africa, Europe, Asia and almost all parts of North America, as well as within large parts of South America and North Oceania. The range of the Jericho 3 also provides an extremely high impact speed for nearby targets, enabling it to avoid any ballistic missile defenses that may develop in the immediate region. On 17 January 2008 Israel test fired a multi-stage ballistic missile believed to be of the Jericho III type reportedly capable of carrying "conventional or non conventional warheads."

M51 SLBM, French Navy submarine-launched ballistic missile

The M51 SLBM is a submarine-launched ballistic missile, built by EADS Astrium Space Transportation, and deployed with the French Navy. Designed to replace the M45 SLBM (In French terminology the MSBS - Mer-Sol-Balistique-Stratégique “Sea-ground-Strategic ballistic”, it was first deployed in 2010.

Each missile carries six to ten independently targetable TN 75 thermonuclear warheads.

The three-stage engine of the M51 is directly derived from the solid propellant boosters of Ariane 5.

The missiles are a compromise over the M5 SLBM design, which is to have a range of 11,000 km (6,200 miles) and carry 10 TNO MIRV of the new generation (Tête Nucléaire Océanique, “Oceanic nuclear warhead”). The M51 will enter service in 2010.

The M51 performed its first flight test (unarmed) on 9 November 2006 from the French missile flight test centre in Biscarrosse (Landes). The target was reached twenty minutes later, in the north-west of the Atlantic Ocean.

A second and third successful test were carried out on 21 June 2007 and 13 November 2008.

On 27 January 2010, at 9h25, a missile was launched underwater by the Terrible, from Audierne Bay. The missile reached its target 2000 kilometres off South Carolina; the 4500 kilometre flight took about 20 minutes.

The 10 July 2010 test validated the Triomphant class submarine capacity to launch a M51 in operational conditions.

M51 SLBM
Type	SLBM
Service history
In service	27 september 2010
Production history
Manufacturer	EADS Astrium Space Transportation
Unit cost	4 billion Euro for the programme
Specifications
Weight	52,000 kg
Length	12.0 m
Diameter	2.3 m
Warhead	M51.1 = 6 to 10 TN 75 MIRV using the 100 kt of TNT (420 TJ), with penetration aids. M51.2 (2015) = using the new Tête Nucléaire Océanique
Engine	three stage solid propellant
Operational range	>10000 km
Speed	Mach 25
Guidance system	Inertial & star positioning
Launch platform	Triomphant class submarines

M45 SLBM. French Navy's submarine ballistic missile

The M45 SLBM is the current standard French Navy's submarine launched ballistic missile (In French terminology the MSBS - Mer-Sol-Ballistique-Stratégique (Sea-ground-Strategic ballistic missile). Forty-eight M45 are in commission in the Force océanique stratégique, the submarine nuclear deterrent component of the French Navy.

The missiles, derived from the M4, are produced by Aerospatiale (now EADS SPACE Transportation). Initially, an ICBM land-based version was considered but these plans were discarded in 1996 to favour an all-naval deployment.

The M45 differs from its predecessor by its increased range (6,000 km vs. 4,000 km), its increased accuracy and penetration capabilities and its new TN-75 warheads. Each missile carries six MIRVs, each armed with a thermonuclear warhead of 100 kt.

The M45 has a reported accuracy of 350 m CEP using an inertial guidance system coupled with computer payload control. It will be succeeded by the M51 SLBM.

In March 1986, a M-4 missile was launched and covered 6,000 km to its target; this flight is rumoured to have been the first test flight for the M-45.

On the night of the 1-2 June 2004, the Triomphant class submarine Vigilant fired a version of the M45 from the southern part of Brittany; the missile hit its target near French Guiana.

M45 SLBM
Type	ICBM
Service history
In service	1996
Production history
Manufacturer	EADS SPACE Transportation
Specifications
Weight	35 t
Length	11.05 m
Diameter	1.93 m
Warhead	6 x 100 kt TN 75
Engine	3-stage solid
Operational range	6,000 km
Guidance system	Inertial plus computer payload control
Launch platform	Triomphant class submarines

Dongfeng-41 (DF-41), Chinese Intercontinental Ballistic Missile

The Dongfeng-41 (DF-41) ("East Wind" 41), is a Chinese nuclear solid-fueled intercontinental ballistic missile currently under service with the Second Artillery Corps.

It has an estimated operational range of 15,000 km, is capable of MIRV delivery (up to 12), and can cover any position on the planet. The project started in the 1980s, and is now quite likely coupled with the JL-2 program.

Military experts had expected that it could be unveiled at the 2009 National Parade. However, rehearsals of the military parade so far have not featured this missile. It is anticipated that the DF-41 will be delivered to the Second Artillery around the year 2010.

DF-41
Type	ICBM
Service history
In service	present
Used by	People's Republic of China
Production history
Manufacturer	China Academy of Launch Vehicle
Specifications
Diameter	2.0 m (6 ft 7 in)
Warhead	nuclear 12 MIRVs
Engine	Three-stage solid propellant
Operational range	~15,000 kms (~9,320 miles)
Guidance system	Inertial with COMPASS
Launch platform	Silo, road-mobile TEL

UR-100N, SS-19 Stiletto

The UR-100N (NATO reporting name SS-19 Stiletto) is an intercontinental ballistic missile in service with Soviet and Russian Strategic Rocket Forces. Russia has 136 missiles still in service, and plans to keep them in their arsenal until 2030. At present (2007) the missiles are deployed in Deraznja, Kozelsk, Pervomajsk and Tatiscevo.

The UR-100N is a fourth-generation silo-launched liquid-propellant ICBM similar to the UR-100 but with much increased dimensions, weights, performance, and payload. The missile was not designed to use existing UR-100 silos, and therefore had new silos constructed for it.

UR-100N
Type	ICBM
Service history
In service	1982–present
Used by	Soviet Union / CIS
Production history
Manufacturer	Khrunichev Machine-Building Plant
Specifications
Weight	105.6 tonnes
Length	27 metres
Diameter	2.5 m
Warhead	up to 6 (1 as per START II
Blast yield	550 KT (Mod 3), 5 MT (Mod 2)
Engine	two-stage liquid fuel
Operational range	10,000 km
Guidance system	inertial

The UR-100N reached initial operating capability in 1974, and by 1978 an inventory of 190 launchers were reached. In 1979, the UR-100UTTH became operational and by 1983 had replaced many older missiles and reached maximum inventory of 360 launchers. This had fallen to 300 by 1991, and with the dissolution of the Soviet Union, many in Ukraine became property of that nation. 170 remained in Russia, although treaty obligations required the rearming of the missiles with single warheads. Russia retains some UR-100UTTHs in its inventory with the potential to retain as many as fifty by the end of the decade. Recent political developments have led to plans to rearm the missiles again with MIRV warheads.

The units previously held by Ukraine have been returned to Russia or decommissioned.

In December 2008 Strategic rocket forces had 126 UR-100NUTTH operational missiles. This does not, however, make them the most numerous ICBMs in the Russian arsenal; that distinction belongs to SS-25 ICBMs.

The UR-100N forms the basis of the Rockot space launch system, which was used in several successful launches in the 1990s and early 2000s, and one failed launch of the ESA CryoSat satellite in 2005. After the failure, Rockot launches were suspended. Once the cause was unambiguously identified and corrective measures implemented, Rockot returned to active service on 28 July 2006, with the successful launch of an earth observation satellite for South Korea.

RT-2PM Topol, SS-25 Sickle, Russian Ballistic Missile

The RT-2PM Topol (NATO reporting name SS-25 Sickle) is a mobile intercontinental ballistic missile designed in the Soviet Union and in service with Russia's Strategic Rocket Forces.

RT-2PM Topol SS-25 Sickle
Type	Intercontinental ballistic missile
Place of origin	Soviet Union
Service history
In service	1988-present
Used by	Russian Strategic Rocket Forces
Production history
Designer	Moscow Institute of Thermal Technology
Manufacturer	Votkinsk Machine Building Plant
Specifications
Weight	45,100 kg (99,000 lb)
Length	21.5 m (71 ft)
Diameter	1.8 m (5 ft 11 in)
Warhead	Single 550 kt warhead
Engine	Three-stage solid propellant
Operational range	10,500 km (6,500 mi)
Speed	approx. 7 km/s
Guidance system	Inertial, autonomous
Accuracy	200 m CEP
Launch platform	Road-mobile TEL

RT-2PM Topol Design

The RT-2PM ICBM was designed to be road mobile and is mounted on a heavy truck (MAZ-7310 or MAZ-7917). Development began in 1977, flight tests of the missile were conducted between 1983 and 1987. After the first series of tests, the first missiles became operational in 1985. Full deployment of 360 missiles was achieved in 1996, and in 2005 300 remained on duty. As of January 2008 the figure had dropped to 201 active missiles. In December 2008 Russian rocket forces had 189 RT-2PM operational missiles. With 276 ICBMs of other types (including 75 R-36 missiles and 75 Topol-M missiles), that gives Russia an ICBM arsenal of 465 missiles - larger than US ICBM arsenal of 450 LGM-30 Minuteman rockets.

The RT-2 is a road mobile 3-stage, single warhead ICBM. Its 29.5 meter length and 1.7 meter diameter are approximately the same size and shape as the U.S. Minuteman ICBM. It has a throw-weight of 1000 kg and carries a single warhead with a yield of 550 kt and accuracy (CEP) of 900 m according to Russian sources [as opposed to 300m according to Western sources]. Its road mobile capability gave the RT-2PM Topol an extremely high probability of survival. It can fire from field deployment sites or through sliding roof garage bases. The RT-2PM Topol joined operational Soviet SRF regiments in 1985. A total area of approximately 190,000 square kilometers could be required to deploy a force consisting of 500 road-mobile Topol ICBMs. Mobile units require a much higher number of personnel for maintenance and operation than fixed systems. Consequently, the RT-2PM Topol was significantly more costly to maintain and operate than silo launched systems.

All three stages are made of composite materials. During first stage operation the flight control is implemented through four aerodynamic and four jet vanes. Four similar trellised aerodynamic surfaces serve for stabilization. During the second and third stage of flight gas is injected into the diverging part of the nozzle for flight control.

The missile is deployed in a Transporter Erector Launcher (TEL) canister mounted on cross-country 7-axle chassis on a mobile launch vehicle. The chassis incorporates jacks, gas and hydraulic drives and cylinders, with a power of several hundred tons, for jacking and leveling of the launcher, speeding up (combat) and slowing down (maintaining) elevation of the container with the missile in the vertical position. The TEL is accompanied by a Mobile command post, carrying support facilities mounted on cross-country 4-axle chassis with unified vans. The complex is equipped with an onboard inertial navigation system which gives the TEL group the capability to conduct the launch independently from its field deployment sites. This topo-geodesic support and navigation subsystem, created by the “Signal” Research Institute, provides a quick and highly precise tie-in of the launcher in a field position and enables its crew to carry out missile launches from any combat patrol route point. The launch can also be carried out at regimental bases from the aforementioned garrison garage.

RT-2UTTKh Topol M, Russian Ballictic Missile

The RT-2UTTKh Topol-M (NATO reporting name: SS-27 Sickle B, other designations: RS-12M1, RS-12M2, RT-2PM2) is one of the most recent intercontinental ballistic missiles to be deployed by Russia (see RS-24), and the first to be developed after the dissolution of the Soviet Union.

In its Russian designation РТ stands for "ракета твердотопливная," Raketa Tverdotoplivnaya ("solid fuel rocket"), while УТТХ - for "улучшенные тактико-технические характеристики," uluchshenniye taktiko-tekhnicheskie kharakteristiki ("improved tactical and technical characteristics"). "Topol" (тополь) in Russian means "poplar". It is designed and produced exclusively by the Moscow Institute of Thermal Technology, and built at the Votkinsk Machine Building Plant.

RT-2UTTKh Topol-M SS-27 Sickle B
Type	Intercontinental ballistic missile
Place of origin	Russia
Service history
In service	December 1997
Used by	Russian Strategic Rocket Forces
Production history
Designer	Moscow Institute of Thermal Technology
Manufacturer	Votkinsk Machine Building Plant
Produced	December 20, 1994
Specifications
Weight	47,200 kg (104,000 lb)
Length	22.7 m (74.47 ft)
Diameter	1.9 m (6 ft 3 in)
Warhead	Single 550 kt warhead
Engine	Three-stage solid propellant
Operational range	11,000 km (6,800 mi)
Speed	10,800 mph (17,400 km/h)
Guidance system	Inertial with GLONASS
Accuracy	200 m CEP
Launch platform	Silo, road-mobile TEL

Missile defense evasion capabilities

According to Russia the missile is designed to be immune to any current or planned U.S. missile defence system. It is claimed to be capable of making evasive maneuvers to avoid a kill by terminal phase interceptors, and carries targeting countermeasures and decoys. It is shielded against radiation, EMP, nuclear explosions at distances over 500 meters, and is designed to survive a hit from any laser technology.

One of the Topol-M's most notable features is its short engine burn time following take-off, intended to minimize satellite detection of launches and thereby complicate both early warning and interception by missile defense systems during boost phase. The missile also has a relatively flat ballistic trajectory, complicating defense acquisition and interception.

According to The Washington Times, Russia has conducted a successful test of the evasive payload delivery system. The missile was launched on November 1, 2005 from the Kapustin Yar facility. The warhead changed course after separating from the launcher, making it difficult to predict a re-entry trajectory.

RS-24 Yarsm, Russian ICBM

The RS-24 Yars is a Russian MIRV-equipped, thermonuclear intercontinental ballistic missile first tested on May 29, 2007 after a secret military R&D project, to replace the older R-36 and UR-100N that have been already used almost for 50 years. RS-24 Yars is a missile that is heavier than Topol M, created in response to the missile shield that the United States was planning to deploy in Europe,^[5] which can carry up to 10 independently targetable warheads.

In June 2008 the chief designer of the Moscow Institute of Thermal Technology, Yuri Solomonov, announced that the RS-24 is an enhanced, MIRVed development of the Topol-M missile that would finish all testing in 2008 and most likely be deployed in 2009. According to General Nikolai Solovtsov, the commander of the Strategic Rocket Forces (SRF), the first RS-24 missiles will be deployed in Teykovo in 2009.

On March 17, 2009 General Solovtsov announced that the first regiment of RS-24 ICBMs will be put in to service in December 2009 when START-1 is set to expire. He later repeated that statement on May 7. According to the Russian rocket forces the first six RS-24 missiles will be mobile.

Further on October 10, 2009, on ITAR-TASS, General Andrei Shvaichenko, the new SRF commander, confirmed the December 2009 deployment of the RS-24 which will support the existing Topol-M (RS-12М2) Missile Complex.

Testing for the new-generation ICBM was completed in mid-July 2010, and the first missiles were deployed shortly after on July 19.

In December 2010 the missile division in Teykovo received its second delivery of RS-24 missile systems. In total 6 missiles are deployed by the end of 2010.

RS-24 Yars
Type	Intercontinental ballistic missile
Place of origin	Russia
Service history
In service	July 2010
Used by	Russia
Production history
Designer	Moscow Institute of Thermal Technology
Manufacturer	Votkinsk Machine Building Plant
Specifications
Length	approx. 23 m
Diameter	approx. 2 m
Warhead	MIRVed, not less than 4, 550 kt warheads
Engine	solid propellant
Speed	Mach 13+
Guidance system	Inertial
Launch platform	Mobile launcher (MAZ-7917)

UGM-133 Trident II

UGM-133 Trident II, or Trident D5 is a submarine-launched ballistic missile, built by Lockheed Martin Space Systems in Sunnyvale, California, and deployed with the Royal Navy and US Navy. It was first deployed in 1990, and is still in service.

UGM-133 Trident II was designed to be more sophisticated than Trident I, and have a greater payload capacity. It is accurate enough to be used as a first strike weapon. All three stages of the Trident II are made of graphite epoxy, making the missile much lighter. Trident II missiles are carried by British Vanguard class and US Ohio class submarines. USS Tennessee was the first submarine to be armed with Trident IIs. Trident II missiles are currently carried by fourteen Ohio class, and four Vanguard class SSBNs. There were 134 consecutive successful test launches of the D5 missile since 1989 with the most recent being carried out on the 7th and 8 June 2010 from USS Maryland (SSBN-738).

The development contract for UGM-133 Trident II was issued in October 1983. The first Trident II launch occurred in January 1987, and the first submarine launch was attempted by USS Tennessee (SSBN-734, the first D-5 ship of the Ohio class) in March 1989. The launch attempt failed because the plume of water following the missile rose to greater height than expected, resulting in water being in the nozzle when the motor ignited. Once the problem was understood relatively simple changes were very quickly made but the problem delayed the IOC (Initial Operational Capability) of Trident II until March 1990.

Specifications of UGM-133 Trident II

• Purpose: strategic nuclear deterrence
• Unit Cost: US$30.9 million
• Range: 11,300 kilometres (7,000 mi)
• Maximum speed: > 6,000 m/s (>21,000 km/h, >13,422 mph).
• Guidance system: inertial, with Star-Sighting, GPS experiments done. but not deployed.
• CEP: Requirement...90–120 m (300–400 ft) That demonstrated by flight tests is significantly better.
• Warhead (in USA usage only): nuclear MIRV. Up to eight W88 (475 kt) warheads (Mark 5) or eight W76 (100 kt) warheads (Mark 4). The Trident II can carry 12 MIRV warheads but START I reduces this to 8 and SORT reduces this yet further to 4 or 5.

UGM-133 Trident II

Function	SLBM
Manufacturer	Lockheed Martin Space Systems
Size
Height	13.41 metres (44.0 ft)
Diameter	2.11 metres (83 in)
Mass	58,500 kilograms (129,000 lb)
Stages	3
Launch history
Status	Active
Launch sites	LC-46, Cape Canaveral Ohio class submarines Vanguard class submarines
Maiden flight	1987-01-15

RUM-139 VL-ASROC, US Anti Submarine Missile

The RUM-139 VL-ASROC is an anti-submarine missile in the ASROC family, currently built by the Lockheed Martin company for the U.S. Navy.

The design and development of the RUM-139 VL-ASROC began in 1983 when the Goodyear Aerospace company was contracted by the U.S. Navy to develop a ship-launched anti-submarine missile compatible with the new Mark-41 Vertical Launch System. The development of the VLS ASROC underwent many delays, and it was not deployed on any ships until 1993. During this development, Goodyear Aerospace was bought by the Loral aerospace company in 1986, and this defense division was in turn purchased by Lockheed Martin Aerospace in 1995.

The first VLS ASROC missile was an RUR-5 ASROC with an upgraded solid-fuel booster section and a digital guidance system. It carries a lightweight Mark 46 torpedo homing torpedo that is dropped from the rocket at a precalculated point on its trajectory, and then parachuted into the sea. Beginning in 1996, the missile was replaced by the newer RUM-139A and subsequently the RUM-139B. The torpedo has remained the Mk-46, though at one time an improved torpedo called the Mark-51 was proposed, and then cancelled. The RUM-139C is now in production since October 2004 with the Mark 54 torpedo.

The vertical-launched missile first became operational in 1993, with more than 450 having been produced by 2007. RUM-139 VL-ASROC is 4.5 meters (15 ft) in length, with a firing range of about 11.8 nm or 22 kilometers (24,000 yd).

RUM-139 VL-ASROC
Type	Standoff Anti-Submarine Weapon
Place of origin	United States
Service history
In service	1993
Used by	United States Navy, Japanese Maritime Self-Defense Force, and Others
Production history
Manufacturer	Lockheed Martin
Produced	1993
Specifications
Length	4.5 meters (15 ft)
Warhead	Mark 46 torpedo
Engine	Two-stage Solid Rocket Fuel Engines
Operational range	22 kilometers (24,000 yd)
Guidance system	Inertial guidance
Launch platform	Surface Ship

RIM-66 Standard, US Surface to Air Missile

The RIM-66 Standard MR (SM-1MR/SM-2MR) is a medium range surface-to-air missile (SAM) originally developed for the United States Navy (USN). The SM-1 was developed as a replacement for the RIM-2 Terrier and RIM-24 Tartar deployed in the 1950s on a variety of USN ships. The RIM-67 Standard (SM-1ER/SM-2ER), is an extended range version of this missile with a booster stage.

RIM-66 Standard missile 1

The RIM-66A is the medium ranged version of the Standard missile and was initially developed as a replacement for the earlier RIM-24C as part of the Mk74 "Tartar" Guided Missile Fire Control System. It used the same fuselage as the earlier Tartar missile, for easier use with existing launchers and magazines for that system. The RIM-66A/B is a semi-active radar homing missile like the earlier RIM-24C, but with many improvements that make it more capable than its predecessor. The RIM-66A/B Standard MR, (SM-1MR Block I to V) was used during the Vietnam War. The only remaining version in service is the RIM-66E (SM-1MR Block VI). While no longer in service with the USN, the missile is still in service with Tartar Guided Missile Fire Control System equipped vessels, Mk 92 Guided Missile Fire Control System equipped vessels, and other compatible systems in many navies.

RIM-66 Standard missile 2

The RIM-66C/D Standard MR (SM-2MR Block I), was developed in the 1970s and was a key part of the Aegis combat system and New Threat Upgrade (NTU). The SM-2MR introduced inertial and command mid-course guidance. The missile's autopilot is programmed to fly the most efficient path to the target and can receive course corrections from the ground. Target illumination for semi-active homing is needed only for a few seconds in the terminal phase of the interception. This capability enables the Aegis combat system and New Threat Upgrade equipped vessels to time share illumination radars, greatly increasing the number of targets that can be engaged at one time. In the middle 1980s, the SM-2MR was deployed via Mk 41 Vertical Launch System (VLS) aboard the USS Bunker Hill, the first U.S. Navy ship to deploy a vertical launcher. VLS has, since 2003, been the only launcher used for the Standard missile in the U.S. Navy aboard Ticonderoga-class cruisers and Arleigh Burke-class destroyers.

The SM-1 and SM-2 were continuously upgraded through Blocks (see below).

The Standard can also be used against ships, either at line-of-sight range using its semi-active homing mode, or over the horizon using inertial guidance and terminal infrared homing.

RIM-66 Standard MR
Type	Medium range surface-to-air missile
Place of origin	United States
Service history
In service	1967 (RIM-66A SM-1MR Block I) 1979 (RIM-66C SM-2MR)
Used by	United States Navy, Japanese Maritime Self-Defense Force, Turkish Navy, Royal Netherlands Navy, German Navy, Canadian Navy, and Others
Production history
Manufacturer	Raytheon and others
Produced	1967 Onwards
Specifications
Weight	SM-2 – 1,558 lb (707 kg)
Length	15 ft 6 in (4.72 m)
Diameter	13.5 in (340 mm)
Warhead	blast fragmentation warhead
Detonation mechanism	radar and contact fuze
Engine	dual thrust, solid fuel rocket
Wingspan	3 ft 6 in (1.07 m)
Operational range	40 to 90 nmi (74 to 170 km)
Flight ceiling	> 24,400 m (80,100 ft)
Speed	Mach 3.5
Guidance system	SM-2 Block IIIA Command and Inertial midcourse guidance with monopulse semi-active radar homing in the terminal phase of the interception. Block IIIB missiles have additionally dual infrared/semi-active terminal homing. SM-1 missiles have monopulse semi-active radar homing without command and inertial mid-course guidance.
Launch platform	Surface Ship

Surface to air variants

Designation	Block	Platform	Notes
RIM-66A	SM-1MR Block I to IV	Digital Tartar	In Service 1967, Conscan radar seeker
RIM-66B	SM-1MR Block V	Digital Tartar	Plane scanning seeker
RIM-66C	SM-2MR Block I	Aegis combat system, Mk26 launcher	MK 115 blast-fragmentation warhead Monopulse seeker for ECM resistance
RIM-66D	SM-2MR Block I	New Threat Upgrade	First New Threat Upgrade version
RIM-66E	SM-1MR Blocks VI, VIA, VIB	Digital Tartar and Mk 92 Fire Control System.	In service 1983. Version still in service with export customers. Adds monopulse seeker developed for Standard missile 2.
RIM-66G	SM-2MR Block II	Aegis combat system, Mk26 launcher	In Service 1983.
RIM-66H	SM-2MR Block II	Aegis combat system, Mk41 Launcher	Added Thiokol MK 104 rocket motor, increasing range High-velocity fragmentation warhead
RIM-66J	SM-2MR Block II	New Threat Upgrade
RIM-66K-1	SM-2MR Block III	New Threat Upgrade
RIM-66K-2	SM-2MR Block IIIA	New Threat Upgrade	In Production.
RIM-66L-1	SM-2MR Block III	Aegis combat system, Mk26 launcher
RIM-66L-2	SM-2MR Block IIIA	Aegis combat system, Mk26 launcher
RIM-66M-1	SM-2MR Block III	Aegis combat system, Mk41 Launcher	Improved MK 45 MOD 9 target detecting device, for low altitude targets
RIM-66M-2	SM-2MR Block IIIA	Aegis combat system, Mk41 Launcher	MK 125 warhead. In production.
RIM-66M-5	SM-2MR Block IIIB	Aegis combat system, Mk41 Launcher	Missile Homing Improvement Program (MHIP), dual IR / SARH seeker, IR seeker mounted on side fairing. In Production.

RIM-161 Standard Missile 3

The RIM-161 Standard Missile 3 (SM-3) is a ship-based missile system used by the US Navy to intercept aircraft, ships, ballistic and cruise missiles as a part of Aegis Ballistic Missile Defense System. Although primarily designed as an anti-ballistic missile, the SM-3 has also been employed in an anti-satellite capacity against a satellite at the lower end of Low Earth orbit. The SM-3 is primarily used and tested by the United States Navy and also operated by the Japan Maritime Self-Defense Force and in the future by the Royal Netherlands Navy.

RIM-161 SM-3
Type	Aegis Ballistic Missile Defense System
Place of origin	United States
Production history
Manufacturer	Raytheon, Aerojet
Unit cost	$9.5 million
Specifications
Length	6.55 m (21 ft 6 in)
Diameter	0.34 m (13.5 in)
Warhead	Lightweight Exo-Atmospheric Projectile (LEAP) kinetic warhead
Wingspan	1.57 m (62 in)
Propellant	Stage1: MK 72 Booster, solid-fuel, Aerojet Stage2: MK 104 Dual Thrust Rocket Motor (DTRM), solid-fuel, Aerojet Stage3: MK 136 Third Stage Rocket Motor (TSRM), solid-fuel, ATK Stage4: Solid Divert and Attitude Control System (SDACS), ATK
Operational range	>500 km (270 nautical miles)
Flight ceiling	>160 km (100 miles)
Speed	9,600 km/h
Guidance system	GPS/INS/semi-active radar homing/passive LWIR seeker (KW)

Variants of RIM-161 Standard Missile 3

The SM-3 Block IA version provides an incremental upgrade to improve reliability and maintainability at a reduced cost. The SM-3 Block IB, due in 2010, offers upgrades which include an advanced two-color infrared seeker, and a 10-thruster solid throttling divert and attitude control system (TDACS/SDACS) on the kill vehicle to give it improved capability against maneuvering ballistic missiles or warheads. Solid TDACS is a joint Raytheon/Aerojet project, but Boeing supplies some components of the kinetic warhead. With Block IB and associated ship-based upgrades, the Navy gains the ability to defend against medium range missiles and some Intermediate Range Ballistic Missiles. SM-3 Block II will widen the missile body to 21” and decrease the size of the maneuvering fins. It will still fit in Mk41 vertical launch systems, and the missile will be faster and have longer range. The SM-3 Block IIA will add a larger diameter kill vehicle that is more maneuverable, and carries another sensor/ discrimination upgrade. It’s currently scheduled to debut around 2015, whereupon the Navy will have a weapon that can engage some Intercontinental Ballistic Missiles.

Standard Missile Three	Anti-Ballistic Missile	Note
RIM-161A	SM-3 Block I,	Development Version
RIM-161B	SM-3 Block IA	1 Color Seeker, Solid Divert Attitude Control System (SDACS)
None to date	SM-3 Block IB	2 Color IIR Seeker and Throttleable Divert Attitude Control System (TDACS) Passed critical design review on 13 July 2009.
None to date	SM-3 Block IIA	Long Range SM-3, Advanced Kinetic Warhead and 21-inch (530 mm) diameter first stage rocket Propulsion

RIM-67 Standard, US Surface to Air Missile

The RIM-67 Standard ER (SM-1ER/SM-2ER) is an extended range surface-to-air missile (SAM) and anti ship missile originally developed for the United States Navy (USN). The RIM-67 was developed as a replacement for the RIM-8 Talos a 1950s system systems deployed on a variety of USN ships.

RIM-67 Standard ER
Type	extended range surface-to-air missile
Place of origin	United States
Service history
In service	1981
Unit cost	$409,000
Specifications
Weight	2,980 lb (1,350 kg)
Length	26.2 ft (8.0 m)
Warhead	Proximity fuse, high explosive 137 lb (62 kg) continuous rod, later blast fragmentation
Engine	Two-stage, solid-fuel rocket; sustainer motor and booster motor
Wingspan	5 ft 2 in (1.57 m)
Operational range	65–100 nmi (120–190 km)
Flight ceiling	80,200 ft (24,400 m)
Speed	classified
Guidance system	Inertial/SARH
Launch platform	Surface Ship

RIM-67A SM-1 Extended Range

The RIM-67A (SM-1ER Block I) was the Navy's replacement for RIM-8 Talos missile. Improved technology allowed the RIM-67 to be reduced to the size of the earlier RIM-2 Terrier missile. Existing ships with the Mk86 guided missile fire control system, or "Terrier" were adapted to employ the new missile in place of the older RIM-2 Terrier missile. Ships that switched from the RIM-2 Terrier to the RIM-67A were still referred to as Terrier ships even though they were equipped with the newer missile.

RIM-67 and RIM-156 SM-2 Extended Range

The second generation of Standard missile, the Standard Missile 2, was developed for the Aegis combat system, and New Threat Upgrade program that was planned for existing Terrier and Tartar ships. The principle change over the Standard missile 1 is the introduction of inertial guidance for each phase of the missile's flight except the terminal phase where semi-active homing was retained. This design change was made so that missiles could time share illumination radars and enable equipped ships to defend against saturation missile attacks.

Terrier ships reequipped as part of the New Threat Upgrade were refit to operate the RIM-67B (SM-2ER Block II) missile. However, Aegis ships were not equipped with launchers that had space enough for the longer RIM-67B.

The RIM-156A Standard SM-2ER Block IV with the Mk 72 booster was developed to compensate for the lack of a long range SAM for the Ticonderoga-class of Aegis cruisers. This configuration can also be used for Terminal phase Ballistic Missile Defense.

There was a plan to build a nuclear armed standard missile mounting a W81 nuclear warhead as a replacement for the earlier Nuclear Terrier missile (RIM-2D). The USN rescinded the requirement for the nuclear armed missile in the 1980s, and the project was canceled.

The Standard can also be used against ships, either at line-of-sight range using its semi-active homing mode, or over the horizon using inertial guidance and terminal infrared homing.

A new generation of Standard extended range missiles is expected to become operational in 2011. This missile is covered in a separate article. Please see RIM-174 Standard ERAM for details.

RIM-67 Standard Surface to air variants

Designation	Block	Notes
RIM-67A	SM-1ER Block I	Terrier Upgrade
RIM-67B	SM-2ER Block I	New Threat Upgrade
RIM-67C	SM-2ER Block II	New Threat Upgrade
RIM-67D	SM-2ER Block III	New Threat Upgrade
RIM-156A	SM-2ER Block IV	Aegis ER VLS
RIM-156B	SM-2ER Block IVA	Canceled

RIM-162 ESSM, US Surface to Air Missile

The RIM-162 Evolved Sea Sparrow Missile (ESSM) is a development of the RIM-7 Sea Sparrow missile used to protect ships from attacking missiles, aircraft and surface threats.^[6] ESSM is designed to counter supersonic maneuvering anti-ship missiles. Compared to the Sea Sparrow, ESSM has a larger, more powerful rocket motor for increased range and agility, as well as upgraded aerodynamics using strakes and skid-to-turn. In addition, ESSM takes advantage of the latest missile guidance technology, with different versions for Aegis/SPY-1, Sewaco/APAR, and traditional target illumination all-the-way. ESSM also has the ability to be "quad-packed" in the Mk 41 VLS system, allowing up to four ESSMs to be carried in a single cell.

ESSM will be used by many allied countries. The first country to achieve operational status for ESSM after the United States was Australia. Other countries which have also integrated the ESSM are Canada, Germany, Turkey, Greece, Japan, Denmark, the Netherlands, and Norway. Countries in the process of integrating ESSM are New Zealand, Spain, and the United Arab Emirates.

RIM-162 Evolved Sea Sparrow Missile (ESSM)
Type	Medium-range surface-to-air missile
Place of origin	United States
Service history
In service	February 2004 aboard USS Chafee
Used by	Australia, Canada, Denmark, Germany, Greece, the Netherlands, Norway, Spain, Turkey and the US
Production history
Manufacturer	Raytheon
Unit cost	$800,000
Produced	September 1998- 1000th missile delivered 25 August 2009
Specifications
Weight	620 lb (280 kg)
Length	12 ft (3.66 m)
Diameter	10 in (254 mm)
Warhead	86 lb (39 kg) blast-fragmentation
Detonation mechanism	Proximity fuze
Engine	Mk 143 Mod 0 solid fuel rocket
Operational range	27+ nm (50+ km)
Speed	Mach 4+
Guidance system	Midcourse datalink Terminal semi-active radar homing
Launch platform	Mk 41 VLS (RIM-162A/B) Mk 48 VLS (RIM-162C) Mk 29 box launcher (RIM-162D)

In addition to the Mk 41 VLS system, the other primary launcher is Mk 48 VLS. The 2-cell module of Mk-48 makes the system very versatle, enables it to be installed onboard in spaces that is otherwise cannot be utilized. The weight of a 2-cell module of Mk-48 is 1,450 pounds (with empty canisters), 725 pounds for exhaust system, and 800 pounds for ship installation interfaces. Each canister of the Mk-48 VLS houses a single RIM-162 ESSM, though with modification, other missiles can also be launched.

MIM-104 Patriot, US Surface to Air Missile

The MIM-104 Patriot is a surface-to-air missile (SAM) system, the primary of its kind used by the United States Army and several allied nations. It is manufactured by the Raytheon Company of the United States. The Patriot System replaced the Nike Hercules system as the U.S. Army's primary High to Medium Air Defense (HIMAD) system, and replaced the MIM-23 Hawk system as the U.S. Army's medium tactical air defense system. In addition to these roles, Patriot has been given the function of the U.S. Army's anti-ballistic missile (ABM) system, which is now Patriot's primary mission.

MIM-104 Patriot uses an advanced aerial interceptor missile and high performance radar systems. Patriot was developed at Redstone Arsenal in Huntsville, Alabama, which had previously developed the Safeguard ABM system and its component Spartan and Sprint missiles. The symbol for Patriot is a drawing of a Revolutionary War-era Minuteman.

MIM-104 Patriot systems have been sold to Taiwan, Egypt, Germany, Greece, Israel, Japan, Kuwait, the Netherlands, Saudi Arabia, United Arab Emirates, and Spain. Poland hosts a battery of Patriot launchers in Morąg since 24 May 2010. The system will be integrated into the Polish air defence system until 2012. The Republic of Korea is also in the process of purchasing several second-hand Patriot systems after North Korea test-launched ballistic missiles to the Sea of Japan and proceeded with underground nuclear testing in 2006.

Patriot missile
Type	Surface-to-air missile
Place of origin	United States
Production history
Designer	Raytheon
Unit cost	US$ 1 to 6 million
Number built	over 8,600
Variants	Standard, ASOJ/SOJC, PAC-2, PAC-2 GEM, GEM/C, GEM/T (or GEM+) and PAC-3
Specifications (PAC-1)
Weight	700 kg
Length	5,800 mm
Diameter	410 mm
Warhead	M248 Composition B HE blast/fragmentation with two layers of pre-formed fragments and Octol 75/25 HE blast/fragmentation
Warhead weight	200 lb (90 kg)
Detonation mechanism	Proximity fuze
Wingspan	920 mm (3 ft 0 in)
Propellant	Solid-fuel rocket
Operational range	PAC - 1 :70 km PAC - 2 :70-160 km PAC - 3 :15 km
Flight altitude	79,500 feet (24,200 m)
Speed	Mach 5.0
Guidance system	Radio command with Track Via Missile semi-active homing
Launch platform	mobile trainable four-round semi-trailer

MIM-104 Patriot equipment

The Patriot system has four major operational functions: communications, command and control, radar surveillance, and missile guidance. The four functions combine to provide a coordinated, secure, integrated, mobile air defense system.

The Patriot system is modular and highly mobile. A battery-sized element can be emplaced in less than 1 hour. All components, consisting of the fire control section (radar set, engagement control section, antenna mast group, electric power plant) and launchers, are truck- or trailer-mounted. The radar set and launchers (with missiles) are mounted on M860 semi-trailers, which are towed by M983 HEMTTs.

Missile reload is accomplished using an M985E1 truck with a crane on the back. This crane is bigger than the standard crane found on most HEMTTs. This crane, called a Guided Missile Transporter (GMT), removes spent missile canisters from the launcher and then replaces them with fresh missiles. Because the crane nearly doubles the height of the HEMMT when not stowed, crews informally refer to it as the "scorpion tail." A standard M983 with a regular-sized crane is referred to as the Large Repair Parts Transporter (LRPT).

The heart of the Patriot battery is the fire control section, consisting of the AN/MPQ-53 or -65 Radar Set, the AN/MSQ-104 Engagement Control Station (ECS), the OE-349 Antenna Mast Group (AMG), and the EPP-III Electric Power Plant. The system's missiles are transported on and launched from the M901 Launching Station, which can carry up to four PAC-2 missiles or up to sixteen PAC-3 missiles. A Patriot battalion is also equipped with the Information Coordination Central (ICC), a command station designed to coordinate the launches of a battalion and uplink Patriot to the JTIDS or MIDS network.

The AN/MPQ-53 and AN/MPQ-65 Radar Set

The AN/MPQ-53/65 Radar Set is a passive electronically scanned array radar equipped with IFF, electronic counter-countermeasure (ECCM), and track-via-missile (TVM) guidance subsystems.

The AN/MPQ-53 Radar Set equips PAC-2 units, while the AN/MPQ-65 Radar Set equips PAC-3 units. The main difference between these two radars is the addition of a second traveling wave tube (TWT), which gives the -65 radar increased search, detection, and tracking capability. The radar's antenna array consists of over 5,000 elements that "flash" the radar's beam many times per second. Additionally, the radar's antenna array contains an IFF interrogator subsystem, a TVM array, and at least one "sidelobe canceller" (SLC), which is a small array designed to decrease interference that might affect the radar. Patriot's radar is somewhat unique in that it is a "detection-to-kill" system, meaning that a single unit performs all search, identification, track, and engagement functions. This is in contrast to most SAM systems, where several different radars are necessary to perform all functions necessary to detect and engage targets.

The beam created by the Patriot's flat phased array radar is comparatively narrow and highly agile compared to a moving dish. This gives the radar an unmatched ability to detect small, fast targets like ballistic missiles, or low radar cross section targets such as stealth aircraft or cruise missiles. Additionally, the power and agility of Patriot's radar is highly resistant to countermeasures, including electronic countermeasures (ECM) radar jamming and radar warning receiver (RWR) equipment. Patriot is capable of quickly jumping between frequencies to resist jamming.

The AN/MSQ-104 Engagement Control Station

The AN/MSQ-104 Engagement Control Station (ECS) is the nerve center of the Patriot firing battery. The ECS consists of a shelter mounted on the bed of an M927 5-Ton Cargo Truck or on the bed of a Light Medium Tactical Vehicle (LMTV) cargo truck. The main sub-components of the ECS are the Weapons Control Computer (WCC), the Data Link Terminal (DLT), the UHF communications array, the Routing Logic Radio Interface Unit (RLRIU), and the two manstations that serve as the system's man-to-machine interface. The ECS is air conditioned, pressurized (to resist chemical/biological attack), and shielded against electromagnetic pulse (EMP) or other such electromagnetic interference. The ECS also contains several SINCGARS radios to facilitate voice communications.

The WCC is the main computer within the Patriot system. It is a 24-bit parallel militarized computer with fixed and floating point capability. It is organized in a multiprocessor configuration that operates at a maximum clock rate of 6 megahertz. This computer controls the operator interface, calculates missile intercept algorithms, and provides limited fault diagnostics. Compared to modern personal computers, it has somewhat limited processing power, although it has been upgraded several times during Patriot's service life.

The DLT connects the ECS to Patriot's Launching Stations. It uses either a SINCGARS radio or fiber optic cables to transmit encrypted data between the ECS and the launchers. Through the DLT, the system operators can remotely emplace, slew or stow launchers, perform diagnostics on launchers or missiles, and fire missiles.

The UHF communications array consists of three UHF radio "stacks" and their associated patching and encrypting equipment. These radios are connected to the antennas of the OE-349 Antenna Mast Group, which are used to create UHF "shots" between sister Patriot batteries and their associated ICC. This creates a secure, real-time data network (known as PADIL, Patriot Data Information Link) that allows the ICC to centralize control of its subordinate firing batteries.

The RLRIU functions as the primary router for all data coming into the ECS. The RLRIU gives a firing battery an address on the battalion data network, and sends/receives data from across the battalion. It also "translates" data coming from the WCC to the DLT, facilitating communication with the launchers.

Patriot's crew stations are referred to as Manstation 1 and 3 (MS1 and MS3). These are the stations where Patriot operators interface with the system. The manstations consist of a monochrome (green and black) screen surrounded by various Switch Indicators. Each manstation also has a traditional QWERTY keyboard and isometric stick, a tiny joystick that functions much like a PC mouse. It is through these switch indicators and the Patriot user interface software that the system is operated.

The OE-349 Antenna Mast Group

The OE-349 Antenna Mast Group (AMG) is mounted on an M927 5-Ton Cargo Truck. It includes four 4 kW antennas in two pairs on remotely controlled masts. The antennas can be controlled in azimuth, and the masts can be elevated up to 100 feet 11 inches (30.76 m) above ground level. Mounted at the base of each pair of antennas are two high-power amplifiers associated with the antennas and the radios in the collocated shelter. It is through these antennas that the ECS and ICC send their respective UHF "shots" to create the PADIL network.

The EPP-III Electric Power Plant

The EPP-III Diesel- Electric Power Plant (EPP) is the power source for the ECS and Radar. The EPP consists of two 150 kilowatt diesel turbine engines(the same turbines that power Apache helicopters) with 400 hertz generators that are interconnected through the power distribution unit. The generators are mounted on a modified M977 HEMTT. Each EPP has two 75-gallon (280 L) fuel tanks and a fuel distribution assembly with grounding equipment. Each diesel engine can operate more than 8 hours with a full fuel tank. The EPP delivers its power to the Radar and ECS through cables stored in reels alongside the generators.

The M901 Launching Station

The M901 Launching Stations are remotely-operated, self-contained units. The ECS controls operation of the launchers through each launcher's DLT, via fiber optic or VHF (SINCGARS) data link.

Integral leveling equipment permits emplacement on slopes of up to 10 degrees. Each launcher is trainable in azimuth and elevates to a fixed, elevated launch position. Precise aiming of the launcher before launch is not necessary; thus, no extra lags are introduced into system reaction time. Each launcher is also capable of providing detailed diagnostics to the ECS via the data link.

The launching station contains four major equipment subsystems: the launcher generator set, the launcher electronics module (LEM), the launcher mechanics assembly (LMA), and the launcher interconnection group (LIG). The generator set consists of a 15 kW, 400 Hz generator that powers the launcher. The LEM is used for the real-time implementation of launcher operations requested via data link from the ECS. The LMA physically erects and rotates the launcher's platform and its missiles. The LIG connects the missiles themselves to the launcher via the Launcher Missile Round Distributor (LMRD).

MIM-104 Patriot Guided Missile

The first fielded variant was the round MIM-104A, "Standard." It was optimized solely for engagements against aircraft and had very limited capability against ballistic missiles. It had a range of 70 km (44 miles), and a speed in excess of Mach 3. The MIM-104B "anti-standoff jammer" (ASOJ) is a missile designed to seek out and destroy ECM emitters.

The MIM-104C PAC-2 missile was the first Patriot missile that was optimized for ballistic missile engagements. The GEM series of missiles (MIM-104D/E) are further refinements of the PAC-2 missile. The PAC-3 missile is a new interceptor, featuring a Ka band active radar seeker, employing "hit-to-kill" interception (in contrast to previous interceptors' method of exploding in the vicinity of the target, destroying it with shrapnel), and several other enhancements which dramatically increase its lethality against ballistic missiles. It has a substantially lower range of 15 km. The specific information for these different kinds of missiles are discussed in the "Upgrades" section.

The first seven of these are in the larger PAC-2 configuration of a single missile per canister, of which four can be placed on a launcher. PAC-3 missile canisters contain four missiles, so that sixteen rounds can be placed on a launcher. The missile canister serves as both the shipping and storage container and the launch tube. Patriot missiles are referred to as "certified rounds" as they leave the factory, and additional maintenance is not necessary on the missile prior to its being launched.

The PAC-2 missile is 5.8 metres (19 ft 0 in) long, weighs about 900 kilograms (2,000 lb), and is propelled by a solid-fueled rocket motor at speeds in excess of Mach 5.0.

MIM-104 Patriot missile design

The PAC-2 family of missiles all have a fairly standard design, the only differences between the variants being certain internal components. They consist of (from front to rear) the radome, guidance section, warhead section, propulsion section, and control actuator section.

The radome is made of slip-cast fused silica approximately 16.5 millimetres (0.65 in) thick, with nickel alloy tip, and a composite base attachment ring bonded to the slip cast fused silica and protected by a molded silicone rubber ring. The radome provides an aerodynamic shape for the missile and microwave window and thermal protection for the RF seeker and electronic components.

The Patriot guidance section consists primarily of the modular digital airborne guidance system (MDAGS). The MDAGS consists of a modular midcourse package that performs all of the required guidance functions from launch through midcourse and a terminal guidance section. The TVM seeker is mounted on the guidance section, extending into the radome. The seeker consists of an antenna mounted on an inertial platform, antenna control electronics, a receiver, and a transmitter. The Modular Midcourse Package (MMP), which is located in the forward portion of the warhead section, consists of the navigational electronics and a missile-borne computer that computes the guidance and autopilot algorithms and provides steering commands according to a resident computer program.

The warhead section, just aft of the guidance section, contains the proximity fused warhead, safety-and-arming device, fuzing circuits and antennas, link antenna switching circuits, auxiliary electronics, inertial sensor assembly, and signal data converter.

The propulsion section consists of the rocket motor, external heat shield, and two external conduits. The rocket motor includes the case, nozzle assembly, propellant, liner and insulation, pyrogen igniter, and propulsion arming and firing unit. The casing of the motor is an integral structural element of the missile airframe. It contains a conventional, casebonded solid rocket propellant.

The Control Actuator Section (CAS) is at the aft end of the missile. It receives commands from the missile autopilot and positions the fins. The missile fins steer and stabilize the missile in flight. A fin servo system positions the fins. The fin servo system consists of hydraulic actuators and valves and an electrohydraulic power supply. The electrohydraulic power consists of battery, motor pump, oil reservoir, gas pressure bottle, and accumulator.