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| Titan II (missile) | |
|---|---|
| Name | LGM-25C Titan II |
| Caption | Titan II during a test launch |
| Origin | United States |
| Type | Intercontinental ballistic missile |
| Manufacturer | Martin Marietta |
| Designer | Glenn L. Martin Company |
| In service | 1963–1987 |
| Weight | 155,000 lb (70,307 kg) |
| Length | 103 ft (31.4 m) |
| Diameter | 10 ft (3.05 m) |
| Propulsion | Two-stage liquid-propellant rocket |
| Warhead | W62 thermonuclear, single 9 megaton yield |
| Guidance | Inertial guidance (ACG-24 / MARC-42) |
| Launch platform | Silo-launched |
Titan II (missile) The Titan II was a United States intercontinental ballistic missile deployed during the Cold War. Developed by the Glenn L. Martin Company and produced by Martin Marietta, it served as a strategic deterrent with a storable liquid-propellant design and later formed the backbone of several American space-launch programs. The missile connected programs and institutions across the Department of Defense, Strategic Air Command, and National Aeronautics and Space Administration operations.
Development began as part of the larger Titan (rocket family) effort, evolving from earlier SM-68 Titan I work and the needs identified in the 1958 US ballistic missile program reviews. The Glenn L. Martin Company responded to United States Air Force requirements for a missile with greater range and payload than contemporary designs such as the Atlas (rocket family). Design choices emphasized a two-stage configuration using storable hypergolic propellants—hydrazine-derived fuels and dinitrogen tetroxide oxidizer—selected for rapid launch readiness over cryogenic alternatives utilized by Saturn I. The program involved coordination with contractors including Aerojet General, Rocketdyne, and subcontractors tied to the Defense Advanced Research Projects Agency initiatives. Guidance and avionics drew on inertial systems developed alongside projects at MIT Instrumentation Laboratory and testing at ranges like Cape Canaveral Space Force Station and Vandenberg Space Force Base.
The missile measured about 103 feet in length with a 10-foot diameter and two-stage liquid propulsion architecture. The first stage used Aerojet-powered engines producing several hundred thousand pounds of thrust, while the second stage provided final boost and insertion for the reentry vehicle, which carried a single W62 thermonuclear warhead. Its inertial guidance package, influenced by research at Wright-Patterson Air Force Base laboratories and specifications from Sandia National Laboratories, enabled intercontinental accuracy sufficient for strategic targeting doctrines of the Department of Defense. Propellants were storable hypergolic chemicals requiring specialized handling procedures developed with input from United States Atomic Energy Commission safety standards and industrial partners including Union Carbide and Dow Chemical Company.
The LGM-25C entered alert status in the early 1960s under control of Strategic Air Command wings deployed across Arkansas, Arizona, and Texas sites. It provided continuous deterrent patrols during crises such as the Cuban Missile Crisis aftermath and throughout escalation phases traced to events like the Vietnam War period. Titan II units were involved in test launches from Vandenberg AFB that supported accuracy assessments and operational readiness exercises involving commands at Offutt Air Force Base and oversight by the United States Air Force. The missile also transitioned into a civilian role when modified variants supported NASA missions including launches of uncrewed probes and crewed capsules, linking it to programs such as Gemini and commercial satellite deployments.
Operational history included several high-profile accidents drawing attention from Congress and safety regulators within agencies like the Department of Defense and the United States Department of Energy. Notable incidents at silo complexes involved propellant leaks, structural failures, and an infamous 1980 explosion in Arkansas that resulted in fatalities and public scrutiny. Investigations engaged organizations including National Transportation Safety Board-level review teams and led to procedural revisions influenced by reporting to bodies such as House Armed Services Committee panels. Incidents highlighted risks of hypergolic propellants documented in industrial safety literature associated with contractors like Aerojet.
Beginning in the late 1970s and accelerating in the 1980s, the LGM-25C force was retired under strategic arms modernization policies influenced by programs such as the deployment of Minuteman III upgrades and arms control dialogues exemplified by the Intermediate-Range Nuclear Forces Treaty deliberations. Deactivation involved demating warheads under protocols with the Department of Energy and dismantling silos coordinated with base commands at McConnell Air Force Base and other sites. Environmental remediation and disposal practices adhered to standards shaped by Environmental Protection Agency guidance and Defense Department directives; some decommissioned units were preserved or converted for civilian launch use at locations like Vandenberg Space Force Base.
The Titan II airframe and propulsion systems spawned several derivatives in both military and civil sectors. The Titan II GLV variant supported NASA's Gemini program crewed launches, while commercial and research derivatives fed into the broader Titan (rocket family) lineage that included the Titan IIIC and Titan IV heavy-lift vehicles. Companies such as Martin Marietta and later Lockheed Martin leveraged Titan technology in subsequent launch service offerings, connecting the platform to satellites launched for organizations including National Reconnaissance Office, Department of Defense missions, and commercial customers.
Category:Intercontinental ballistic missiles of the United States Category:Cold War weapons of the United States