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Aircraft/Missile Information
The Martin B-68 Titan took over the designation after the Martin XB-68 bomber project was canceled. � The B-68 Titan I was redesignated SM-68 and later changed to HGM-25A. � The Titan II was reassigned the LGM-25C designation. � First launch of a SM-68 Titan I was Feb. 6, 1959 � The Titan I is easily distinguished from the Titan II by noting the Titan I has a smaller diameter upper stage (the Titan II is constant diameter first and second stages). The Titan III and IV series rockets have two solid propellant strap-on first stage boosters.
SPECIFICATIONS: Length: 103 ft. (ICBM configuration); first stage length 70 ft. Diameter: 10 ft. (first and second stages - ICBM configuration) Weight: 270,000 lbs. at launch Armament: General Electric Mk. 6 Nuclear warhead Engines: First stage powered by Aerojet LR87-AJ-5 two chamber liquid propellant rocket of 430,000 lbs. thrust fueled by Aerozine-50 (fuel) that ignites on contact with nitrogen tetroxide (oxidizer); second stage of ICBM configuration powered by Aerojet-General LR91-AJ-5 rocket engine of 100,000 lbs. thrust Crew: None
PERFORMANCE (ICBM configuration): Maximum speed: 15,000 mph / 13,904 knots Maximum range: Approx. 10,000 statute miles / 8,700 nautical miles Maximum altitude: 700 statute miles / 610 nautical miles
