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2,685,936. Sound Reduction Equipment for Use with Jet-Propulsion Units. Robert W. Brenneman, Burbank, Edwin Jacobsen, Altadena, and Richard S. Jacobsen, Hollywood, Calif., assignors to Lock heed Aircraft Corporation, Burbank, Calif. Applica These details and drawings of patents granted in the United States are taken, by permission of the tion August 8, 1950. Department of Commerce, from the 'Official Gazette of the United States Patent Office*. Printed copies Equipment for reducing the noise produced by the of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, jet discharged from the tail pipe portion of an aircraft jet engine comprising an inlet tube having a forward Washington, D.C., U.S A. They are usually available for inspection at the British Patent Office, end for receiving the jet, adaptor means yieldingly Southampton Buildings, Chancery Lane, London, W.C.2. connected with the tube for engaging and sealing about said portion, means for admitting atmospheric air into the forward end of the tube, a stack for dis charging the jet gases from the rear portion of the tube, and sound absorbing means in the tube and 2,684,212. Disk Rotor with Refracting Blades for Application June 7, 1950. Claims priority, applica stack. Convertible Aircraft. Edward G. Vanderlip, Radnor, tion Sweden July 7, 1949. Pa., assignor to Piasecki Helicopter Corporation, A missile comprising coaxial relatively movable Morton, Pa. Application October 31, 1951. parts including a substantially cylindrical hollow An aircraft comprising in combination, a fuselage outer casing having a constriction at its forward end having an empennage and forward propulsive means, and a substantially cylindrical inner body having a a disk-shaped aerofoil mounted on said fuselage for conoidal nose of greater maximum diameter than universal inclination thereon, means for rotating said the minimum diameter of said constriction co-opera aerofoil, a plurality of rotary wing blades mounted tive with said constriction to provide an annular port for rotation with said disk-shaped aerofoil, and means adapted to be closed by relative axial movement of for retracting said blades into said aerofoil and for the parts, the rear ends of said parts forming a reactive extending said blades outside of said aerofoil. discharge nozzle, ram jet engine fuel disposed interiorly of the casing, and rocket-engine fuel adjacent thereto, the reaction of combustion of said rocket-engine fuel maintaining said parts in relative positions closing said annular port and the resistance of the atmosphere 2,686,656. Blade Locking Device. Robert N. Abild, in flight inducing relative movement of the parts to New Britain, Conn., assignor to United Aircraft open said port on exceeding said reaction. Corporation, East Hartford, Conn. Application April 4, 1950. In a rotor construction, a disk member having a series of axial slots extending through the disk at its outer periphery, a series of blades extending radially outward from the disk and each having a root member fitting in and engaging one of said slots, and locking means for each blade root to hold it in axial position in the slot, said locking means comprising a flat strip of material extending through said slot and located in the base thereof, said strip having its ends project ing beyond the ends of the slot and having the project 2,684,215. Stick Force Mechanism. Irving L. ing ends extending over and engaging the sides of Ashkenas, Los Angeles, Calif., assignor to Northrop one of said members, said strip having a notch between Aircraft, Inc., Hawthorne, Calif., a corporation of its ends, said other members having a projecting rib California. Application August 29, 1949. thereon engaging with said notch to prevent relative axial movement therebetween. In an aeroplane having a control surface linked to be moved by a pilot's control element, clastic centring means connected to said pilot's control element to tend to centre said control element to substantially neutralize said control surface, force transmitting means having a member adapted to be moved by an external force, and means connecting said member non-linearly to said control element, said connecting means comprising a pivotally mounted support mem ber, linkage means connected between said support 2,684,819. Aircraft Engine Support Structure. member and said pilot's control element to rotate Joseph H. Leggett, Bloomfield, and Robert M. said support member substantially linearly as said Moyer, Great Notch, N.J., assignors to Curtiss- control element is moved in a direction to move said Wright Corporation. Application April 26, 1950. control surface, a cam sector attached to rotate with A device for resiliently connecting an engine to a said support member and having a cam surface on its supporting structure such that the engine shifts about perimeter, a cam follower positioned to ride on said its torque axis relative to said supporting structure in cam surface, and additional means connecting said response to changes in the torque output of the engine; movable member to said cam follower to urge said said device comprising a bracket for connexion to cam follower against said cam surface in accordance with said force, said cam surface having a contour an engine; a bracket for connexion to a supporting providing a predetermined non-linear motion between structure; and means clastically connecting said said movable member and said pilot's control element brackets in such a manner that the spring rate of said connexion in the direction of the relative shift of said on at least one side of said centre. brackets in response to changes in engine torque 2,688,455. Retractable Surface Support. James depends on the relative position of said brackets M. Clark, Jamaica, N.Y., assignor to North American along a line parallel to said direction; said means Aviation, Inc. Application August 14, 1951. including a member having a first portion connected The combination with a relatively fixed wing and to one of said brackets, the other of said brackets a flap operatively carried by the trailing portion of having an engageable portion and said member hav said wing, of a guide track for said flap pivotally ing a second portion engageable with and disengage- mounted upon a chordwise axis upon said wing, means able from said engageable bracket portion for varying for extending said guide track between retracted and said spring rate, said member second portion being extended positions about said chordwise axis and with disposed in engagement with said engageable bracket respect to said wing, and supporting means pivotally portion when the engine torque responsive shift of carried by said flap for engagement with said guide the bracket is below a predetermined value and being track for the support of said flap from said guide movable out from engagement with said engageable track in its extended position. bracket portion when the engine torque responsive shift of the brackets exceeds said value. 2,684,570. Rocket-Engine and Reaction-Motor Missile. Kurt Martin Nordfors, Karlskoga, Sweden, assignor to Aktiebolaget Bofors, Bofors, Sweden. 400 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Nov 1, 1954
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