The Pershing II Weapon System was a solid-fueled two-stage medium-range ballistic missile designed and built by Martin Marietta to replace the Pershing 1a Field Artillery Missile System as the United States Army's primary nuclear-capable theater-level weapon. The U.S. Army replaced the Pershing 1a with the Pershing II Weapon System in 1983, while the German Air Force retained Pershing 1a until all Pershings were eliminated in 1991. The U.S. Army Missile Command (MICOM) managed the development and improvements, while the Field Artillery Branch deployed the systems and developed tactical doctrine.
Development Development began in 1973 for an updated Pershing. The Pershing 1a had a 400 kt warhead, which was greatly over-powered for the Quick Reaction Alert (QRA) tactical role the weapon system filled. Reducing warhead yield, however, required a significant increase in accuracy to match Pershing 1a's ability to kill hard targets like command bunkers. The contract went to Martin Marietta in 1975 with the first development launches in 1977. The first launch took place on July 22, 1982 from Launch Complex 16 at Cape Canaveral Air Force Station. Pershing II was to use the new W85 warhead with a 5 to 80 kt variable yield or an earth-penetrator W86 warhead as nuclear bunker buster. The warhead was packaged in a maneuverable reentry vehicle (MARV) with active radar guidance and would use the existing rocket motors. Requests from Israel to buy the new Pershing II were rejected in 1975.
The Soviet Union began deployment of the RSD-10 Pioneer (NATO designation SS-20 Saber) in 1976. Since the first version of the RSD-10 had a range of and two warheads, the Pershing II requirement was changed to increase the range to , giving the ability to reach targets in eastern Ukraine, Belarus or Lithuania. The NATO Double-Track Decision was made to deploy both the medium-range Pershing and the longer-range, but slower BGM-109G Ground Launched Cruise Missile (GLCM) to strike potential targets farther to the east. The Pershing II with the longer-range motors was initially referred to as Pershing II Extended Range (PIIXR), then reverting to Pershing II.
Both the hard-target capability and W86 nuclear warhead were cancelled in 1980, and all production Pershing II missiles carried the W85. A concept warhead using kinetic energy penetrators for counter-airfield operations never materialized.
System Technical data + Missile data Missile section Length Diameter max Diameter min Mass First stage — Second stage — Guidance & control assembly Warhead section Radar section Missile total
Launcher Because of SALT II agreements, no new launchers could be built, therefore the Pershing 1a M790 launchers were modified into the Pershing II M1003 launchers. The functions of the vehicle-mounted programmer test station needed for the older systems were consolidated into the Launch Control Assembly (LCA) in the Ground Integrated Electronics Unit (GIEU) on the side of the launcher. The warhead and radar sections were carried as an assembly on a pallet that rotated to mate with the main missile.
There were two prime movers for the launcher, both with a crane used for missile assembly and a generator to provide power for the launcher and missile. The U.S. units used the M983 HEMTT with a Hiab 8001 crane and a 30 kW generator. Tactical units in Germany used the M1001 MAN tractor with an Atlas Maschinen GmbH AK4300 M5 crane and a 30 kW generator. Since the new guidance system was self-orienting, the launcher could be emplaced on any surveyed site and the missile launched within minutes.
Booms: Support missile cradle during erection and recapture of the missile. Missile cradle: Supports missile during transport, erection, and recapture of the missile. Retaining ring segments: Used to retain missile in missile cradle during transport. EL pallet cover: Protects radar section and warhead section during travel. EL pallet: Platform used to transport and mate warhead section and radar section. Work platform: Work area for mating reentry vehicle sections. Ground Integrated Electronics Unit (GIEU): Consists of Launch Control Assembly (LCA) and Power Control Assembly (PCA) with the protective door. Hydraulic control panel: Contains controls and indicators for system hydraulic function. Uplock release mechanism: Releases azimuth ring uplock, allowing missile recapture. Uplock assembly: Locks azimuth ring in erect (firing) position. Azimuth ring assembly: Consists of launch platform, blast deflector, and ring for mating the missile. EL power supply: Provides 28 V DC power to EL. Missile power supply: Provides 28 V DC power to the missile. Front jack: Used to raise, lower, and level front of EL. Landing gear: Supports the front of the EL when EL is detached from the tractor and not supported by jacks. Hydraulic oil tank: Non-pressurized reservoir for hydraulic oil. Protective covers: Protect G&C/A and radar section. Rear jacks: Used to raise, lower, and level rear of EL.
Aft panel: Remains in place, except for maintenance. Top panels: Panels with half hinges removed for missile erection, and panels with rollers stored behind side panels for missile erection. Forward side panels: Curbside and roadside panels folded outward for missile erection. Side panels: Curbside and roadside panels removed for missile erection. Aft side panels: Curbside and roadside panels removed for missile erection
Missile
Radar section Warhead section Guidance and control section with adapter Second stage First stage
Motors The new rocket motors were built by Hercules: To minimize airframe weight, the rocket cases were spun from Kevlar with aluminum attachment rings. The Pershing 1a cable mast was replaced by a conduit attached to each motor containing two cables. Cables internally connected from motor to motor and to the G&C. The aft end of the first stage had two tail plugs that connected to the GIEU.
Aft skirt assembly: Cylindrical aluminum assembly that contains aft lift points, vane control system (VCS), nozzle control system (NCS), aft attach ring and cables. Movable nozzle: Directs thrust developed by rocket motor during first stage operation: Nozzle provides pitch and yaw control during the first stage powered flight. Nozzle control system (NCS): Controls movement of the nozzle and provides nozzle position data to Pershing Airborne Computer (PAC). Rocket motor assembly: Filament-wound cylindrical assembly that contains forward lift points, solid propellant, and first stage ignition system: Rocket motor assembly also serves as the outer surface of the forward section of the first stage. First stage ignition system: Allows electrical ignition of first stage rocket motor and prevents inadvertent launch: Ignition system contains igniter, safe and arm (S&A) device, initiators, clocked high energy firing unit (CHEFU), and high voltage cables. Forward attach ring: Allows mating of the first stage to the second stage. Forward lift point: Two lift points allow attachment of first stage hoisting beam so that the first stage can be lifted and moved. Conduit cover assembly: Externally mounted cover that routes cables from aft skirt assembly, lengthwise along outside of rocket motor assembly, to the inside forward skirt. Tailplug connectors: Allow electrical interface between the missile and ground integrated electronics unit (GIEU) on EL. Vane control system (VCS): Controls movement of two movable fins and provides fin position data to PAC. Moveable fin: Two movable fins located opposite each other on the first stage aft skirt: Fins provide roll control during the first stage powered flight. Aft lift point: Two lift points allow attachment of first stage hoisting beam so that the first stage can be lifted and moved. Fixed fin: Two fixed fins located opposite each other on the first stage aft skirt: Fins provide stability during the first stage powered flight. Aft attach ring: Allows mating of the first stage to azimuth ring assembly on EL.
Aft attach ring: Allows mating of the first stage to the second stage. First stage separation system: Allows separation of the first stage from the second stage after first stage burnout and before second stage ignition: Separation system contains linear shaped charge (LSC), separation ring, detonators, CHEFU, and high voltage cables. Aft skirt assembly: Cylindrical aluminum assembly that contains aft lift points, NCS, aft splice ring and cables. Rocket motor assembly: Filament wound cylindrical assembly that contains forward lift points, solid propellant and second stage ignition assembly: Rocket motor assembly also serves as the outer surface of the forward section of the second stage. Conduit cover assembly: Externally mounted cover that routes cables from aft skirt assembly, lengthwise along outside of rocket motor assembly, to the inside forward skirt. Second stage ignition system: Allows electrical ignition of second stage rocket motor: Ignition system contains igniter, initiators, clocked high energy firing unit (CHEFU), and high voltage cables. Forward attach ring: Allows mating of the second stage to G&C/A. Thrust reversal system: Allows second stage reverse thrust to be developed after RV separation so that second stage will not interfere with RV flight: Thrust reversal system contains three thrust reversal ports, LSC rings, shielded mild detonating cord (SMDC), thrust reversal manifold, detonators, CHEFU and high voltage cables. Forward lift point: Two lift points allow attachment of second stage hoisting beam so that the second stage can be lifted and moved. Aft lift point: Two lift points allow attachment of second stage hoisting beam so that the second stage can be lifted and moved. Nozzle control system (NCS): Controls movement of the nozzle and provides nozzle position data to PAC. Moveable nozzle: Directs thrust developed by rocket motor during second stage operation: Nozzle provides pitch and yaw control during second stage powered flight.
Reentry vehicle The reentry vehicle (RV) was structurally and functionally divided into three sections: the radar section (RS), the warhead section (WHS), and the guidance and control/adapter (G&C/A) section.
Guidance and control/adapter The guidance and control/adapter (G&C/A) section consisted of two separate portions, the G&C and the adapter connected by a manufactured splice. At the forward end of the G&C there was a quick access splice for attachment to the warhead section. At the aft end, the adapter was grooved to accept the V-band that spliced the propulsion section to the G&C section. The RV separation system consisted of a linear shaped charge ring assembly bolted to the G&C section so that separation occurred just forward of the G&C manufactured splice. A protective collar on the outer surface of the adapter, mounted over the linear shaped charge, provided personnel protection during G&C/A handling operations.
The G&C portion contained two guidance systems: a Singer-Kearfott inertial navigation system that provided guidance through the terminal phase and as primary terminal guidance system a Goodyear Aerospace active radar guidance system. Using radar maps of the target area, the Pershing II had an accuracy of circular error probable. If the radar guidance failed, the inertial guidance would keep the missile on-target with a lower accuracy. The G&C also contained the Pershing Airborne Computer (PAC), the digital correlator unit (DCU) and actuators to drive the air fins.
Integrated electronics unit (IEU). Controls all functions of the missile during flight. IEU contains the Pershing airborne computer (PAC), digital correlator unit (DCU) and inertial measurement system (IMS). Vane control system (VCS). Controls movement of four fins and provides fin position data to PAC. VCS operates during the second stage powered flight and the terminal portion of the flight.