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In an aircraft having a control surface hinged to the aircraft adjacent one edge to move about a U.S. Patent Specifications given axis and having a tab hinged on its opposite edge, mechanism for causing anti-servo and servo motion of the tab relative to the control surface upon These details and drawings of patents granted in the United States are taken, by permission of the movement of the control surface about said given Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies axis, said mechanism including an anti-servo rod of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, means hinged to the aircraft at one side of said axis Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, and operatively connected with the tab to hinge the Southampton Buildings, Chancery Lane, London, W.C.2. same relative to the control surface in the anti-servo directions upon movement of the surface through a limited range, a servo rod hinged to the aircraft at a 2,556,345. Aircraft Control System. Aaron Sivitz, point spaced at the other side of said axis, and a lost Columbus, Ohio, and Philip L. Ruby, Jackson, Mich., motion connection between said servo rod and the assignors to Curtiss-Wright Corporation. Application tab allowing said hinging of the tab and operable to May 7, 1949. limit such hinging so that the servo rod hinges the tab In an aircraft control system, aileron means and a in the servo directions upon movement of the control reversible motor therefor, a variable resistor operated surface beyond the limits of said range, the anti-servo by said motor, a roll gyro and a variable resistor rod means comprising a spring loaded contractible operated thereby, said variable resistors being ar and extensible assembly which contracts and extends ranged in a bridge circuit, a polarized relay responsive during said servo movements of the tab. to the potential across the output terminals of said 2,557,747. Supplying Cooling Air to Turbine Disks bridge circuit and arranged to control said motor for of Gas-Turbine Engines. Charles Alan Judson, Bor- operation in either direction, a variable resistor arranged to apply a potential of either polarity across rowash, John Radclifie Read, Duffield, and Philip said bridge output terminals, a yaw gyro and a re Edgar Hunter, Chcllaston, England, assignors to versible motor arranged to differentially operate the Rolls-Royce Limited, Derby, England. Application the tab and a push-pull rod extending longitudinally last mentioned variable resistor to respectively impose October 13, 1947. In Great Britain October 2, 1946, of the aircraft for operating the lever, the latter being Section 1, Public Law 690, August 8, 1946. Patent pivoted to the control surface on an axis substantially expires October 2, 1966. normal to said transverse axis, a member connected to said push-pull rod a connexion point substantially along said transverse axis, and said member being movably connected to said lever to move said con nexion point substantially along said transverse axis toward or away from the pivot axis of the lever. 2,557,101. Aircraft Cooling System and Method. Waldemar F. Mayer, Los Angeles, Calif., assignor to An axial-flow turbine arrangement comprising a The Garrett Corporation, Los Angeles, Calif. Appli turbine casing, a turbine-rotor-assembly rotatably cation April 3, 1950. ' mounted in the casing, said turbine-rotor-asscmbly automatic yaw control and selection of heading upon comprising a plurality of coaxial, axially-spaccd, the aileron operating system, a pair of polarized blade-carrying disks whereof one disk at least is formed relays arranged in parallel to control said last-men centrally with an axial bore, a shaft-like bolt member tioned motor for operation in either direction, a extending through said axial bore, a nut member second bridge circuit comprising a circular resistor coaxial with the disks, said bolt member having having two pairs of contacts rotatable thereon, one of threaded engagement with the nut member, one of said pairs constituting the input terminals of the bridge said members being rigidly connected with a second circuit and the other of said pairs the output terminals disk so that the nut and bolt members support said thereof, one of said pair of relays being connected bored disk from said second disk, said bolt member across said output terminals of the second bridge having a bore extending through it coaxial with the circuit, one of said pairs of contacts being rotatable discs, an exhaust-assembly carried on the outlet side by said last-mentioned motor, stepping means for of said turbine casing, said exhaust-assembly com rotating the other one of said pairs of contacts, and prising an outer wall and an inner coaxial wall defining means of selectively operating said stepping means between them an annular exhaust passage, and means and the other of said pair of relays to thereby selective to convey cooling air to said axial bore in the bolt ly cause incremental turns and continuous turns of member comprising conduit means extending across the aircraft. the annular exhaust passage from outside said outer wall to within aid inner wall and having a fixed con 2,556,351, Mass Load Applying Means for Airfoils. duit element supported within said inner wall to be Fredrick T. Tullcy, Columbus, Ohio, assignor to coaxial with the turbine disks, said conduit element Curtiss-Wright Corporation. Application July 17, having its outlet end located adjacent the exhaust side of the turbine-rotor-asscmbly, gas-sealing means In an aircraft having a fixed airfoil and a control Mechanism for conditioning the air for use in an interconnecting said fixed conduit element with said airfoil hinged upon an axis forward ,of its centre of aircraft cabin comprising: a compressor, and a pair turbine-rotor-asscmbly in a manner permitting relative gravity to the trailing edge of said fixed airfoil, the of ramming inlet ducts extending along the respective rotation of said fixed conduit element and said turbine- combination of a lever pivoted to the control airfoil sides of said cabin and converging behind said cabin, rotor-asscmbly and providing a passage for conveying at a point therewithin whose longitudinal location is for directing a flow of air to the inlet of said com cooling air from the fixed conduit element into said adjacent that of said centre of gravity, said lever pressor; a cooler disposed between the rear of said axial bore in said bolt member, and means to supply extending forwardly into said fixed airfoil and carrying cabin and said ducts, said cooler having passage cooling air to the conduit means from outside said at its forward end a load-applying mass that is dis means for the flow therethrough of air from the dis outer wall of the exhaust assembly. posed within said fixed airfoil, and a link pivoted to charge side of said compressor and having other the lever intermediate of said mass and the pivot of 2,560,665. Door for Pressurized Aircraft. William passage means for the flow therethrough of a coolant the lever to the control airfoil, said link being pivoted in heat exchange relation to said first mentioned N. Stark, Kirkland, Wash., assignor to Boeing Air passage, means for delivering compressed air from plane Company. Application February 25, 1946. the discharge side of said compressor to said first mentioned passage means and from said first men tioned passage means to said cabin, means for direct ing a flow of air from one of said ducts to said second mentioned passage means and from said second men tioned passage means to the inlet of said compressor, and means for diverting a portion of the compressed air which has passed through said first mentioned passage means, into said second mentioned passage means for auxiliary cooling of said first mentioned to the fixed airfoil forwardly of said axis and being passage means. disposed within the confines of the fixed airfoil, the A door arrangement for an enclosure comprising lever being arranged to apply the load of said load a frame member having a projecting peripheral con 2,557,426. Tab Actuating Mechanism. Thomas C. applying mass to the control airfoil principally in a tact element fixedly supported thereon, a movable George, North Hollywood, Calif., assignor to Lock direction that is substantially normal to the plane of closure member hinged on one side to said frame heed Aircraft Corporation, Burbank, Calif. Applica the control airfoil. member, said closure member including a peripheral tion January 13, 1950. supporting angle fixedly secured thereto, a resilient diaphragm in a state of initial tension secured to 2,556,353. Aircraft Control System. Roland J. opposite legs of said angle forming a pocket bounded White, Seattle, Wash., assignor to Curtiss-Wright by said angle and said diaphragm, said diaphragm Corporation. Application January 10, 1947. being sealingly engageable with said contact element, In an aircraft having a fixed structure, a control and a vent communicating said pocket with the en surface hinged to said structure on an axis transverse closure sealed by the engagement of said diaphragm of the aircraft, a tab movable on the control surface, and said contact means. ,ab operating means including a lever connected to 60 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 1952
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