— Ch. 1 · Development Origins And Design —
Pershing II.
~5 min read · Ch. 1 of 6
In 1973, the United States Army began a new project to replace its aging Pershing 1a missile system. The existing weapon carried a warhead with a yield of 400 kilotons, which was far too powerful for its intended tactical role. Military planners needed a smaller explosive that could still destroy hardened targets like underground command bunkers. Achieving this required a massive leap in precision accuracy. Martin Marietta won the development contract in 1975 after years of evaluation. The first test launch occurred on the 22nd of July 1982 from Launch Complex 16 at Cape Canaveral Air Force Station. Engineers designed the Pershing II to carry either a W85 warhead with variable yields between 5 and 80 kilotons or an earth-penetrating W86 bunker buster. Requests from Israel to purchase the new system were rejected by American officials in 1975. The Soviet Union had begun deploying their RSD-10 Pioneer missiles in 1976, prompting changes to the American range requirements. Planners increased the Pershing II range to ensure it could strike targets deep inside eastern Ukraine, Belarus, or Lithuania.
Technical Architecture And Guidance
The Pershing II utilized solid-fueled two-stage rocket motors built by Hercules Corporation. To keep weight down, engineers spun the rocket cases from Kevlar material with aluminum attachment rings. A Goodyear Aerospace active radar guidance system provided terminal phase accuracy. This system compared live video returns against pre-stored reference maps of the target area. The missile achieved a circular error probable of just 30 meters when using radar correlation. If the radar failed, an inertial navigation system would still guide the weapon to its general target area. The reentry vehicle contained three distinct sections: a radar section, a warhead section, and a guidance and control adapter. Radar maps stored on disk were transferred to quarter-inch cartridges for use during countdown operations. A DEC PDP-11/70 computer programmed these targeting data files before launch. The missile used swivel nozzles for pitch and yaw control during powered flight phases. Roll control came from movable air vanes located on both the first stage and the reentry vehicle.