The interstage structure, oxidizer tank forward skirt, and inter-tank structure are all fabricated assemblies using riveted skin, stringers and frame. The Stage I airframe consists of an interstage structure, oxidizer tank forward skirt, oxidizer tank, inter-tank structure, and fuel tank. A removable cover for tank entry is located on the forward dome of each tank. Access doors are provided on the missile forward, aft and between-tanks structure for inspection and maintenance. External conduits are attached to the outside surface of the tanks to provide passage for the wire bundles and tubing.
MINUTEMAN MISSILE SILO BLAST DOOR SKIN
Each stage is 10 feet (3.0 m) in diameter and has fuel and oxidizer tanks in tandem, with the walls of the tanks forming the skin of the missile in those areas. The missile guidance system enables the shutdown and staging enable relay to initiate Stage I separation. The airframe is a two-stage, aerodynamically stable structure that houses and protects the airborne missile equipment during powered flight. The IMU would compensate and send steering commands to the engine actuators. The Autopilot attempted to keep the missile straight during first stage flight and sent commands to the Inertial Measurement Unit (IMU) on the 2nd stage. Stage I contained three gyros and the Autopilot. In addition, Stage II contains the flight control system and missile guidance system. Stage I and Stage II vehicles each contain propellant and pressurization, rocket engine, hydraulic and electrical systems, and explosive components. Provisions are included for in-flight separation of Stage II from Stage I, and separation of the RV from Stage II. The missile consists of a two-stage, rocket engine powered vehicle and a re-entry vehicle (RV). Titan II carried the largest single warhead of any American ICBM. This reduced time to launch and permitted it to be launched from its silo. Unlike the Titan I, it used hydrazine-based hypergolic propellant which was storable and reliably ignited. Part of the Titan rocket family, the Titan II ICBM was the successor to the Titan I, with double the payload. The modified Titan II SLVs (Space Launch Vehicles) were launched from Vandenberg Air Force Base, California, up until 2003. Those payloads included the USAF Defense Meteorological Satellite Program (DMSP), NOAA weather satellites, and NASA's Gemini crewed space capsules. Titan II was originally designed and used as an ICBM, but was later adapted as a medium-lift space launch vehicle (these adaptations were designated Titan II GLV and Titan 23G) to carry payloads to Earth orbit for the United States Air Force (USAF), National Aeronautics and Space Administration (NASA) and National Oceanic and Atmospheric Administration (NOAA). Martin Company from the earlier Titan I missile. The Titan II was an intercontinental ballistic missile (ICBM) developed by the Glenn L. Titan-II ICBM silo test launch, Vandenberg Air Force Base Mark 6 re-entry vehicle which contained the W-53 nuclear warhead, fitted to the Titan II Titan II launch vehicle launching Gemini 11 (12 September 1966) Titan 23G launch vehicle (5 September 1988) Payload to 100 km (62 mi) sub-orbital trajectory
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