The Titan IIID or Titan 3D was an American expendable launch system , part of the Titan rocket family . Titan IIID was flown 22 times with KH-9 and KH-11 satellites between 1971 and 1982, all successful launches. Essentially a Titan IIIC with the Transtage removed, it was designed for heavy LEO payloads.
6-637: The rocket had two UA1205 solid fuel boosters, the first stage was equipped with two LR-87-AJ11 engines and the second stage had a single LR-91-AJ11 engine. Part of the Titan rocket family , the Titan IIID first flew on 15 June 1971, launching the first KH-9 satellite. It was retired from service in 1982, and replaced by the uprated Titan 34D . All launches occurred from Space Launch Complex 4E at Vandenberg Air Force Base . [REDACTED] Media related to Titan IIID at Wikimedia Commons This rocketry article
12-404: A common design, with the only significant differentiating factor being the length of the motor. It was a segmented design, with between five and seven motor segments possible. A solid propellant used was a ammonium perchlorate composite propellant with polybutadiene acrylonitrile (PBAN) binder. The stage had an external diameter of 120 inches. Attitude control in flight was provided by means of
18-509: A liquid injection thrust vector control (LITVC) system, with an external nacelle containing nitrogen tetroxide attached to the side of each booster. Solid fueled separation rockets, used to jettison the spent boosters, were affixed at the top and bottom of the stage. Thrust-termination capability, necessary for crewed rockets such as the Space Shuttle or Manned Orbiting Laboratory , was to be provided by two pyrotechnically triggered ports on
24-477: Is a stub . You can help Misplaced Pages by expanding it . UA120#UA1205 UA120 was a family of American solid rocket boosters , manufactured by the Chemical Systems Division of United Aircraft (later United Technologies Corporation ). They were used as strap-on boosters for the Titan rocket family . Several variants existed, with a varying number of segments. All versions of UA120 shared
30-399: The forward closure, which when opened would allow for the non-propulsive venting of exhaust gasses. The forward end of the stage contained an aerodynamic nose cone , an ignitor, separation rockets, and the forward attachment ring. The aft end contained additional separation rockets, the nozzle, and a heat shield. The overall design of each variant was very similar, the main difference being
36-561: The number of segments used. This is indicated by the number at the end of each designation. UA1205 was flown between 1982 and 1992, and used as a strap-on booster on the Titan IIIC , Titan 23C , Titan IIID , and Titan IIIE rockets, besides being proposed for use on several derivatives of the Saturn rocket family . The UA1206 was flown between 1982 and 1992, and used as a strap-on booster on Titan 34D and Commercial Titan III . UA1207
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