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means for releasing one pair of couplings at the will of the pilot, and means for sequentially releasing the other pair of couplings, said last mentioned means including a mechanical latch associated with said last These details and drawings of patents granted in the United States are taken, by permission of the mentioned couplings and released by a predeter mined axial rotation of the object to be jettisoned. Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, Southampton Buildings, Chancery Lane, London, W.C.2. 2,550,806. Aircraft Flight Control Apparatus. Laurens Hammond, Chicago, Illinois, assignor to 2,548,858. Gas Turbine Apparatus. Marcus C. Hammond Instrument Company, Chicago, Illinois, a Benedict, Springfield, Pa., assignor to Westinghousc corporation of Delaware. Application November 26, Electric Corporation, East Pittsburgh, Pa., a corpora 1945. Serial No. 630,861. 3 Claims. (CI. 244—79.) tion of Pennsylvania. Application June 24, 1949. In an apparatus for controlling the flight of an aero In a gas turbine power plant including a substanti plane designed for control through two clevons, the ally cylindrical casing structure having an annular combination of a gyro apparatus responsive to rolling air flow passage, and a compressor rotor axially and yawing of the aeroplane, a servomotor controlled mounted therein for drawing air into said passage, an thereby, operating connections between the servo air inlet casing section comprising an outer generally motor and one of the clevons to cause the latter to be frusto-conical wall portion complementary to and operated rapidly in a direction to correct for roll or mounted on said casing structure and an inner fairing yaw of the aeroplane, a gyropilot apparatus respon portion disposed in spaced relation interiorly of said sive to changes in pitch of the aircraft, a second servo outer wall portion, said casing section having an motor controlled thereby, and operating connexions eccentric air inlet passage diverging rearwardly into between said second servomotor and the other clevon 2,550,337. Engine Cowling. John C. Duffendack, a concentric annular passage communicating with the to cause the latter to move relatively slowly in a direc Jr. and Willard W. Tjossem, Burbank, California, first-named passage, an arcuate gear box carried on tion to compensate for incipient changes in pitch. assignors to Lockheed Aircraft Corporation, Burbank, the relatively inswept wall portion of said casing sec California. Application February 7, 1945. Serial No. tion adjacent said eccentric passage and within the 2,551,113. Liquid Feeding Mechanism of Combus 576,530. 7 Claims. (Cl. 123—41.7.) lateral extent of said power plant, a plurality of acces- tion Chambers. Robert H. Goddard, deceased, late of An annular cowling system for aircraft engines, the sory devices for said power plant mounted on said Annapolis, Md, by Esther C. Goddard, executrix, aircraft including an engine extending forwardly from gear box, and driving means therefor including a shaft Worcester, Mass., assignor of one-half to The Daniel a generally circular engine nacell structure, compris operatively connecting said accessory devices. and Florence Guggenheim Foundation, New York, ing cantilever means independent of said engine and N.Y., a corporation of New York. Application separately supported from said nacelle structure, February 7, 1948, Serial. No. 7,018. I Claim. (CI. including a plurality of cowl panels at least one of 60—44.) said panels being hinged directly to said nacelle A combustion chamber having jacketed wall structure, means supporting the remaining cowl portions spaced apart at their closed inner ends and panels on hinge axes normally parallel to the cen adapted to contain liquids under pressure, a pair of tre line of the nacelle structure, and means for parallel annular spray pipes mounted between said latching said last mentioned cowl panels to said first closed ends, and tubular means to connect each wall mentioned panel whereby to produce a rigid cantilever portion at its closed end with the more remote spray cowling capable of resisting distortion. pipe, said closed ends and spray pipes having five sets of spray openings through which jets of liquid arc ejected, the sets of spray openings in the closed ends of the spaced wall portions being directed at oppositely- inclined angles so that the two scries of jets delivered from said openings converge relative to the axis of 2,549,044. Roll Control. Irving L. Ashkenas, said chamber and to each other, each annular supply Beverly Hills, and Thomas A. Feeney, Los Angeles, pipe having one set of spray openings directed Calif., assignors to Northrop Aircraft, Inc., Haw substantially parallel to the jets delivered from the thorne, Calif., a corporation of California. Applica spray openings in its adjacent wall portion, and one tion Octlober 12, 1946. annular supply pipe having an additional set of spray openings which arc oppositely inclined with respect A roll control system for aeroplanes comprising a to its first set of spray openings therein, whereby jets spoiler member protectable above the upper surface ejected from each set of spray openings cross jets from of each wing adjacent the outer end thereof and con a second set of spray openings and continue substanti toured to provide a rolling moment non-linear with ally parallel to jets from a third set of spray openings. respect to projection distance, control means con nected to said members, said control means including means differentially projecting and retracting said 2,550,380. Progressive Release Jettison Tank. John members linearly with respect to movements of said E. Redfod, Glendale, California, assignor to Lock control means, an aileron hinged to said aeroplane heed Aircraft Corporation, Burbank, California. Ap and positioned to provide a rolling movement sub plication April 16, 1947. Serial No. 741,809. 4 Claims. stantially linear with respect to deflexion when de (Cl. 244—135.) flected, and means connecting said aileron to said con A progressive release mechanism for initiating axial trol means to deflect said aileron non-linearly with rotation in jcttisonablc objects of circular section respect to movement of said control means at rates suspended externally from an aeroplane, comprising providing a total rolling moment substantially linear separate pairs of longitudinally aligned couplings, one with respect to movement of said control means. pair of couplings being disposed on cither side of the 2,549,887. Centrifugally Controlled Coning Lock centre of gravity of the object suspended thereby, 2,551,114. Two-Liquid Feed for Bladed Rotors. Michel D. Buivid, Milford, Conn., ing Device for Combustion Cham assignor to United Aircraft Corporation, East Hart bers. Robert H. Goddard, deceased, late of Annapolis, ford, Conn., a corporation of Delaware. Application Md., by Esther C. Goddard, executrix, Worcester, April 21, 1949. Serial No. 88,748. 6 Claims. (Cl. 170— Mass., assignor of one-half of The Daniel and Florence 160.16.) Guggenheim Foundation, New York, N.Y., a cor In a helicopter rotor having a hub and blade, pivot poration of New York. Application March 24, 1948. means for connecting said blade and hub providing Serial No. 16,867. 3 Claims. (CI. 60—44.) upward and downward flapping movement of said In a two-liquid feeding device for a combustion blade, resilient bumper means carried by said hub for chamber comprising an axial porous feeding member, limiting the downward movement of said blade, a means to force one combustion liquid through said cylinder carried by said hub, piston means reciproc- porous member to issue as a fine mist at its outer able in said cylinder and having an operative con surface and annular means to supply a converging nection with said blade for limiting the upward move film of a second combustion liquid to the outer surface ment of said blade, a source of hydraulic fluid having of said porous member at its periphery for interming a fluid line operatively connected to said cylinder, and ling with said fine mist of said first combustion liquid, means responsive to the speed of said rotor including a that improvement which comprises a porous member valve for controlling the flow of fluid in said fluid line which is cup-shaped and outwardly concave and and controlling the position of said piston means. which has an axial raised projection. 320 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Oct 1, 1951
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