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U.S. Patent Specifications

U.S. Patent Specifications axes located on, or to the rear of, a transverse line through the centre of gravity of the aeroplane and upstanding from said surfaces, said fins having a substantially symmetrical aero-foil cross section and being pivoted forward of their aerodynamic centre These details and drawings of patents granted in the United States are taken, by permission of the for free floating movement in the stream of air passing Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies over said surfaces, and stop means for each fin limit­ of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, ing the outboard movement of the trailing portion Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thereof beyond a position in which the longitudinal centre line of the fin is substantially parallel with said Southampton Buildings, Chancery Lane, London, W.C.2. plane while permitting free inboard movement of said trailing portion relative to said wing. adapted for substantially linear movement relative thereto in the unfolded position, an element pivoted to said first section at a point spaced from said fold axis, linearly movable parts of said control system that extends from both of said sections having pivotal connexions to said element, and means for moving said element to bring said pivotal connexions into predetermined relation with said fold axis upon folding of said sections, said means comprising inter- abutting portions of one of said sections and one of said parts. 2,538,777. Control Device for the Power Units of Aircraft. Robert Z. Hague, Oradell and Howard A. Alexanderson, Wood-Ridge, N.J., assignors to Ben- 2,538,582. Fuel Pump Control for Gas Turbine dix Aviation Corporation, Teterboro, N.J., a cor­ Responsive to Intake Air Pressure and Temperature. poration of Delaware. Original application May 29, Donald Louis Mordell, Montreal, Quebec, Canada, 1945, Serial No. 596,472. Divided and this application and John Bertram Holliday, Derby, England, assign­ March 3, 1948, Serial No. 12,784. 7 Claims. (Cl. 121— ors to Rolls-Royce Limited, Derby, England, a 41.) British company. Application April 30, 1948. Serial 2,539,404. Solid Propellant Charge for Rocket The combination comprising a first rotatable shaft, No. 24,376. In Great Britain May 13, 1947. 6 Claims. Motors. Leslie M. Crutchfield, Monrovia, William a second rotatable shaft, a walking beam operatively (Cl. 60-41.) E. Campbell, Jr., Pasadena, and Harry W. Mace, connecting said first and second rotatable shafts, stop A fuel system for a gas-turbine engine comprising a Glendale, California, assignors to Aerojet Engineering means for limiting movement of said walking beam in fuel supply pump; means for varying the delivery of Corporation, Azusa, California, a corporation of a first sense and permitting movement of said walking fuel by said pump to the engine; a pressure-sensitive Delaware. Application May 28, 1945. Serial No. beam in a second sense so as to drivingly connect device arranged by its movements to adjust the means 596,208. 5 Claims. (Cl. 60—35.6.) said first and second rotatable shafts, and means for for varying the delivery of fuel by the pump; means A jet motor comprising a combustion chamber for applying a pre-determined load on said pressure- terminating at one end in an exhaust nozzle and at sensitive device in the sense tending to move the the other end in a circular opening, a cap member pressure-sensitive device to cause an increase in the adapted to enclose the circular opening of the com­ delivery of fuel; a first flow restricting orifice of bustion chamber, a propellant charge in the com­ effective area A , through which part of the fuel F bustion chamber, said charge comprising a solid 3 2 delivered to the engine actually passes; valve means stick of self-combustible thermoplastic propellant, a controlling the area of said first flow restricting thermoplastic coating adhering to the side wall of orifice arranged to be moved in accordance with the stick and a pliable wrapper around the coating, engine air intake temperature; a second flow restricting said wrapper being maintained in close contact with orifice of effective area A ; a third flow restricting the wall of the chamber, the exposed end of the stick orifice of effective area A , said second and third facing the nozzle, a metal plate with projecting cars orifices being arranged in series with another and in secured to the end of the stick remote from the parallel across said first flow restricting orifice to pass nozzle so that said cars will engage the combustion the remainder F of the total fuel (low F; valve means chamber remote from the nozzle to prevent the pro­ for controlling the areas of said second and third flow pellant charge from sliding in the direction of the restricting orifices in unison in accordance with air exhaust nozzle, and a cushion disposed in the cap intake pressure of the engine so that areas A , A member between said metal plate and the closed 1 2 conform to the equation: end of the cap member to prevent the propellant charge from sliding in the direction away from the nozzle. where A is a constant; a pressure connexion at pres­ placing said stop means out of said limiting relation 2,539,960. Mounting Structure for Gas-Turbine sure P from one side of the pressure sensitive device so as to permit movement of said walking beam in Power Plants for Aircraft. Francis Charles Ivor to the upstream side of the said first and second flow said second cence. Marchant and William George Morgan, Bristol, restricting orifices; and a pressure connexion at England, assignors to The Bristol Aeroplane Company pressure P to the other side of the pressure sensitive 2,538,878, Retractable Landing Gear. Edward V. Limited, Bristol, England, a British company. Applica­ device from the space between said second and third Misulis, Buffalo, N.Y., assignor to Curtiss-Wright tion July 17, 1947. Serial No. 761,678. In Great flow restricting orifices, thereby to apply a fluid Corporation a corporation of Delaware. Application Britain May 22, 1946. 3 Claims. (Cl. 60—102.) pressure load to the pressure sensitive device in the February 5, 1948, Serial No. 6,487. 15 Claims (Cl. A vehicle power plant comprising a pair of gas- sense to balance the predetermined load, which fluid 244—102.) turbine engines spaced apart and lying side by side, pressure load is approximately proportional to the In a retractable landing gear installation for an a gear-box extending from one engine to the other square of actual fuel flow to the engine, is predeter­ aircraft, a landing gear assembly, a retraction recess and connected to each engine, the engines driving a mined function of air intake pressure and is a pre­ within the aircraft, means for retracting said landing power-output shaft through said gear-box, a bridge- determined function of air intake temperature. gear assembly into said retraction recess, upper fairing piece extending from one engine to the other near means carried by said landing gear assembly for the gear-box and rigidly secured to each engine so as 2,538,602. Aircraft Control Mechanism. Paul H. closing a portion of said retraction recess, lower partly to relieve the gear-box of loads transmitted Taylor, North Tonawanda and Richard E. Karnuth, fairing means pivotally mounted upon the aircraft and from one engine to the other, a plurality of rods Buffalo, N.Y., assignors to Curtiss-Wright Corpora­ arranged for the auto­ spaced around the engines and extending generally tion, a corporation of Delaware Application July matic opening and closing lengthwise of the engines, means for attaching one 20, Serial No. 606,260. 3 Claims. (Cl. 244—90.) of the remainder of said end of each rod to the vehicle and hinge means for In a folding aircraft structure including first and retraction recess upon attaching the end of each rod individually to one of second sections relatively movable about a fold axis, extension and retraction the engines, the hinge axes of said hinge means all a control system extending between said sections and of said landing gear, and being in a common plane lying transversely of the resiliently biased break­ engines so that the power plant is supported canti- ing strut means for main­ levcrwisc by said rods from the vehicle. taining said lower fairing means open and closed in the operative and retracted positions of the land­ ing gear. 2,539,357. Wing-Tip Control Surface for Tailless Aeroplanes. Quentin Wald, Woodmont, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware. Applica­ tion November 20, 1945, Serial No. 629,885. 6 Claims. (Cl. 244—87.) In an aeroplane having wing surfaces on opposite sides of a central longitudinal plane vertical fins pivotally mounted on said surfaces and movable about 186 Aircraft Engineering http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology , Volume 23 (6): 1 – Jun 1, 1951

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032053
Publisher site
See Article on Publisher Site

Abstract

axes located on, or to the rear of, a transverse line through the centre of gravity of the aeroplane and upstanding from said surfaces, said fins having a substantially symmetrical aero-foil cross section and being pivoted forward of their aerodynamic centre These details and drawings of patents granted in the United States are taken, by permission of the for free floating movement in the stream of air passing Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies over said surfaces, and stop means for each fin limit­ of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, ing the outboard movement of the trailing portion Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thereof beyond a position in which the longitudinal centre line of the fin is substantially parallel with said Southampton Buildings, Chancery Lane, London, W.C.2. plane while permitting free inboard movement of said trailing portion relative to said wing. adapted for substantially linear movement relative thereto in the unfolded position, an element pivoted to said first section at a point spaced from said fold axis, linearly movable parts of said control system that extends from both of said sections having pivotal connexions to said element, and means for moving said element to bring said pivotal connexions into predetermined relation with said fold axis upon folding of said sections, said means comprising inter- abutting portions of one of said sections and one of said parts. 2,538,777. Control Device for the Power Units of Aircraft. Robert Z. Hague, Oradell and Howard A. Alexanderson, Wood-Ridge, N.J., assignors to Ben- 2,538,582. Fuel Pump Control for Gas Turbine dix Aviation Corporation, Teterboro, N.J., a cor­ Responsive to Intake Air Pressure and Temperature. poration of Delaware. Original application May 29, Donald Louis Mordell, Montreal, Quebec, Canada, 1945, Serial No. 596,472. Divided and this application and John Bertram Holliday, Derby, England, assign­ March 3, 1948, Serial No. 12,784. 7 Claims. (Cl. 121— ors to Rolls-Royce Limited, Derby, England, a 41.) British company. Application April 30, 1948. Serial 2,539,404. Solid Propellant Charge for Rocket The combination comprising a first rotatable shaft, No. 24,376. In Great Britain May 13, 1947. 6 Claims. Motors. Leslie M. Crutchfield, Monrovia, William a second rotatable shaft, a walking beam operatively (Cl. 60-41.) E. Campbell, Jr., Pasadena, and Harry W. Mace, connecting said first and second rotatable shafts, stop A fuel system for a gas-turbine engine comprising a Glendale, California, assignors to Aerojet Engineering means for limiting movement of said walking beam in fuel supply pump; means for varying the delivery of Corporation, Azusa, California, a corporation of a first sense and permitting movement of said walking fuel by said pump to the engine; a pressure-sensitive Delaware. Application May 28, 1945. Serial No. beam in a second sense so as to drivingly connect device arranged by its movements to adjust the means 596,208. 5 Claims. (Cl. 60—35.6.) said first and second rotatable shafts, and means for for varying the delivery of fuel by the pump; means A jet motor comprising a combustion chamber for applying a pre-determined load on said pressure- terminating at one end in an exhaust nozzle and at sensitive device in the sense tending to move the the other end in a circular opening, a cap member pressure-sensitive device to cause an increase in the adapted to enclose the circular opening of the com­ delivery of fuel; a first flow restricting orifice of bustion chamber, a propellant charge in the com­ effective area A , through which part of the fuel F bustion chamber, said charge comprising a solid 3 2 delivered to the engine actually passes; valve means stick of self-combustible thermoplastic propellant, a controlling the area of said first flow restricting thermoplastic coating adhering to the side wall of orifice arranged to be moved in accordance with the stick and a pliable wrapper around the coating, engine air intake temperature; a second flow restricting said wrapper being maintained in close contact with orifice of effective area A ; a third flow restricting the wall of the chamber, the exposed end of the stick orifice of effective area A , said second and third facing the nozzle, a metal plate with projecting cars orifices being arranged in series with another and in secured to the end of the stick remote from the parallel across said first flow restricting orifice to pass nozzle so that said cars will engage the combustion the remainder F of the total fuel (low F; valve means chamber remote from the nozzle to prevent the pro­ for controlling the areas of said second and third flow pellant charge from sliding in the direction of the restricting orifices in unison in accordance with air exhaust nozzle, and a cushion disposed in the cap intake pressure of the engine so that areas A , A member between said metal plate and the closed 1 2 conform to the equation: end of the cap member to prevent the propellant charge from sliding in the direction away from the nozzle. where A is a constant; a pressure connexion at pres­ placing said stop means out of said limiting relation 2,539,960. Mounting Structure for Gas-Turbine sure P from one side of the pressure sensitive device so as to permit movement of said walking beam in Power Plants for Aircraft. Francis Charles Ivor to the upstream side of the said first and second flow said second cence. Marchant and William George Morgan, Bristol, restricting orifices; and a pressure connexion at England, assignors to The Bristol Aeroplane Company pressure P to the other side of the pressure sensitive 2,538,878, Retractable Landing Gear. Edward V. Limited, Bristol, England, a British company. Applica­ device from the space between said second and third Misulis, Buffalo, N.Y., assignor to Curtiss-Wright tion July 17, 1947. Serial No. 761,678. In Great flow restricting orifices, thereby to apply a fluid Corporation a corporation of Delaware. Application Britain May 22, 1946. 3 Claims. (Cl. 60—102.) pressure load to the pressure sensitive device in the February 5, 1948, Serial No. 6,487. 15 Claims (Cl. A vehicle power plant comprising a pair of gas- sense to balance the predetermined load, which fluid 244—102.) turbine engines spaced apart and lying side by side, pressure load is approximately proportional to the In a retractable landing gear installation for an a gear-box extending from one engine to the other square of actual fuel flow to the engine, is predeter­ aircraft, a landing gear assembly, a retraction recess and connected to each engine, the engines driving a mined function of air intake pressure and is a pre­ within the aircraft, means for retracting said landing power-output shaft through said gear-box, a bridge- determined function of air intake temperature. gear assembly into said retraction recess, upper fairing piece extending from one engine to the other near means carried by said landing gear assembly for the gear-box and rigidly secured to each engine so as 2,538,602. Aircraft Control Mechanism. Paul H. closing a portion of said retraction recess, lower partly to relieve the gear-box of loads transmitted Taylor, North Tonawanda and Richard E. Karnuth, fairing means pivotally mounted upon the aircraft and from one engine to the other, a plurality of rods Buffalo, N.Y., assignors to Curtiss-Wright Corpora­ arranged for the auto­ spaced around the engines and extending generally tion, a corporation of Delaware Application July matic opening and closing lengthwise of the engines, means for attaching one 20, Serial No. 606,260. 3 Claims. (Cl. 244—90.) of the remainder of said end of each rod to the vehicle and hinge means for In a folding aircraft structure including first and retraction recess upon attaching the end of each rod individually to one of second sections relatively movable about a fold axis, extension and retraction the engines, the hinge axes of said hinge means all a control system extending between said sections and of said landing gear, and being in a common plane lying transversely of the resiliently biased break­ engines so that the power plant is supported canti- ing strut means for main­ levcrwisc by said rods from the vehicle. taining said lower fairing means open and closed in the operative and retracted positions of the land­ ing gear. 2,539,357. Wing-Tip Control Surface for Tailless Aeroplanes. Quentin Wald, Woodmont, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware. Applica­ tion November 20, 1945, Serial No. 629,885. 6 Claims. (Cl. 244—87.) In an aeroplane having wing surfaces on opposite sides of a central longitudinal plane vertical fins pivotally mounted on said surfaces and movable about 186 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jun 1, 1951

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