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U.S. Patent Specifications

U.S. Patent Specifications A booster control mechanism for an aircraft control system having a movable surface to be con­ trolled, a pilot operated member operatively con­ nected to the surface, a booster servo-motor opera­ tively connected to the surface, and a source of These details and drawings of patents granted in the United States are taken, by permission of the energy for the servo-motor, said control mechanism Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies comprising a floating control member having con­ of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, nections at spaced points thereon to said surface and Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, to said pilot-operated member respectively, supporting means for urging said control member into an inter­ Southampton Buildings, Chancery Lane, London, W.C.2. mediate position thereof, and two control elements for jointly controlling the supply of energy from said 2,514,393. Variable Area Exhaust Nozzle for Burbank, Calif. Original application March 6, 1942. source to said servo-motor, one of said elements Power Plants. David W. Hutchinson, Mamaroneck, Divided and this application January 15, 1945. having operative engagement with said control mem­ N.Y., assignor to Westinghouse Electric Corporation, An aircraft including an airfoil having a boundary ber adjacent said supporting means and the other of East Pittsburgh, Pa., a corporation of Pennsylvania. layer removal slot, a turbo jet power plant including said elements having operative engagement with said Application September 3, 1947. a turbine and a jet-discharging exhaust nozzle for the control member at a point spaced from said sup­ In a gas turbine power plant including fuel com­ turbine, duct means for conducting boundary layer porting means for said member. bustion means, a gas turbine operative by motive air from said slot to adjacent said nozzle for ejection fluid therefrom, and a compressor driven by said with the nozzle jet, and means driven by said turbine turbine to supply air under pressure to said com­ for moving the air through the duct means. bustion means, the combination of casing structure 2,514,888. Aircraft Wing Tip Fuel Tank Installa­ forming an exhaust nozzle for said turbine, movable tion. Donald L. McFarland, Milford, Conn., assignor tailpiece means operable to vary flow characteristics to United Aircraft Corporation, East Hartford, of said nozzle, said tailpiece means being urged Conn., a corporation of Delaware. Application toward open position by the thrust of gases at said January 31, 1947. nozzle, and fluid pressure responsive mechanism for In an aeroplane, a wing having upper and lower actuating said tailpiece means toward closed position. surfaces and having a tip which is enlarged about a fore-and-aft axis relative to the thickness of the adjacent wing section, said tip being formed by rotating a lateral extension of the upper wing surface, taken at its extremity, about a line in said tip parallel to a chord line at the extremity of said wing until the surface of revolution generated by said rotation inter­ sects the lower wing surface. In an aeroplane, a wing having upper and lower 2,515,639. Safety Device for Pressurized Aircraft. 2,514,178. Synchronizing and Speed Control Device. surfaces and having an outer wing panel terminating John J. Draney, La Mesa, Calif., assignor to Con­ John Alfred Chilman, Gloucester, Alfred George in a wing chord section and a wing tip forming an solidated Vultee Aircraft Corporation, San Diego, Mapp, Cheltenham, and Edward Hollingworth extension of said section, said wing tip terminating Calif., a corporation of Delaware. Application April Morris, Ashstead, England, assignors to Rotol in a surface of revolution formed by rotating a lateral 23, 1947. Limited, Gloucester, England, a British company. extension of the upper surface line of said wing at In an aircraft, a pressurized fuselage adapted to be Application June 19, 1946. In Great Britain Septem­ said section about a fore and aft axis of said wing tip maintained at a predetermined pressure independent ber 25, 1944. parallel to but outboard of a chord line of said wing of the atmospheric pressure, a relief valve in said A device for synchronizing and controlling the speed at said section until it intersects the lower surface of fuselage to automatically exhaust said fuselage to the of the engines of a multi-engined aircraft of which one said wing panel, a drop tank having a well in its side atmosphere when the pressure therein exceeds the engine is the master and the others slaves controlled to receive said wing tip, and co-operating locking predetermined value, a landing gear on said aircraft, thereby comprising a master alternating current means carried by said wing and tank for releasably a bleed valve associated with said landing gear having generator the frequency of which is related to a securing said tank to said wing tip, said lateral ex­ an operative connection with said relief valve, and datum speed, means to drive said generator, a dynamo- tension of the upper surface line of said wing at said means on said landing gear to operate said bleed electric machine driven by said master alternating section being extended laterally to a vertical plane valve to open said relief valve when the load of the current generator and associated with the master through said fore and aft wing tip axis. aircraft is supported by said landing gear thereby to engine, for each engine a variable pitch propeller equalize automatically the internal pressure of said driven by the engine, a constant speed governor fuselage with the atmospheric pressure. driven in common with the propeller for adjusting the pitch of the propeller blades to keep the propeller speed constant at a datum for which the governor is set, an alternating current generator driven by each of the slave engines so that its frequency is related to engine speed, a dynamo-electric machine which re­ ceives current from the alternating current generator driven by the slave engine and the generator driven by the master engine and which responds to a fre­ 2,515,069. Wind Tunnel. Colman Zola, Mount quency difference between said two alternating current Vernon, N.Y., assignor to the United States of generators, proportional to the speed differences be­ America as represented by the Secretary of the Navy. tween said engines, and the constant speed governor. Application March 18, 1946, Serial No. 655,310. 2,516,066. Rotor Assembly. Roderick Cristall 2 Claims. (Cl. 73—147.) McLeod, Cropston, and Thomas Edward Callister, A device for examining the behaviour of a body in Barrow-in-Furness, England, Kenneth Watson, Clark- a high speed fluid current, comprising a tunnel for ston, Scotland, and Geoffrey William Bone, Skelling- defining the path of flow of the fluid current, means thorpe, England, assignors to Power Jets (Research for mounting said body within said tunnel, a source & Development) Limited, London, England. Appli­ of high velocity flow of combustion gases, means on cation November 26, 1945. In Great Britain April said source for directing said flow into said tunnel, 27, 1942. and means for injecting a cooling fluid into the A rotor assembly comprising a compressor rotor tunnel in the direction of said combustion gases to having an axial bore and a second coaxial rotor mix therewith prior to the contact of said mixture axially spaced therefrom, a hollow shaft coaxially with said body. attached to said compressor rotor and extending towards said second rotor, a second shaft coaxially rigidly extending from said second rotor towards the compressor rotor and engaged within said hollow shaft for rotation therewith, and screw connecting 2,514,513. Jet Power Plant with Boundary Layer means internally of said shafting exposed for access Control for Aircraft. Nathan C. Price, Los Angeles, thereto through said axial bore for adjustment to Calif., assignor to Lockheed Aircraft Corporation, mutually draw together axially and secure said hollow shaft and said second shaft. 2,515,457. Hydraulic Power Booster for Aircraft Surface Control. James M. Shoemaker, Nichols, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware. Appli­ cation September 19, 1944. 316 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 22 (10): 1 – Oct 1, 1950

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb031961
Publisher site
See Article on Publisher Site

Abstract

A booster control mechanism for an aircraft control system having a movable surface to be con­ trolled, a pilot operated member operatively con­ nected to the surface, a booster servo-motor opera­ tively connected to the surface, and a source of These details and drawings of patents granted in the United States are taken, by permission of the energy for the servo-motor, said control mechanism Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies comprising a floating control member having con­ of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, nections at spaced points thereon to said surface and Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, to said pilot-operated member respectively, supporting means for urging said control member into an inter­ Southampton Buildings, Chancery Lane, London, W.C.2. mediate position thereof, and two control elements for jointly controlling the supply of energy from said 2,514,393. Variable Area Exhaust Nozzle for Burbank, Calif. Original application March 6, 1942. source to said servo-motor, one of said elements Power Plants. David W. Hutchinson, Mamaroneck, Divided and this application January 15, 1945. having operative engagement with said control mem­ N.Y., assignor to Westinghouse Electric Corporation, An aircraft including an airfoil having a boundary ber adjacent said supporting means and the other of East Pittsburgh, Pa., a corporation of Pennsylvania. layer removal slot, a turbo jet power plant including said elements having operative engagement with said Application September 3, 1947. a turbine and a jet-discharging exhaust nozzle for the control member at a point spaced from said sup­ In a gas turbine power plant including fuel com­ turbine, duct means for conducting boundary layer porting means for said member. bustion means, a gas turbine operative by motive air from said slot to adjacent said nozzle for ejection fluid therefrom, and a compressor driven by said with the nozzle jet, and means driven by said turbine turbine to supply air under pressure to said com­ for moving the air through the duct means. bustion means, the combination of casing structure 2,514,888. Aircraft Wing Tip Fuel Tank Installa­ forming an exhaust nozzle for said turbine, movable tion. Donald L. McFarland, Milford, Conn., assignor tailpiece means operable to vary flow characteristics to United Aircraft Corporation, East Hartford, of said nozzle, said tailpiece means being urged Conn., a corporation of Delaware. Application toward open position by the thrust of gases at said January 31, 1947. nozzle, and fluid pressure responsive mechanism for In an aeroplane, a wing having upper and lower actuating said tailpiece means toward closed position. surfaces and having a tip which is enlarged about a fore-and-aft axis relative to the thickness of the adjacent wing section, said tip being formed by rotating a lateral extension of the upper wing surface, taken at its extremity, about a line in said tip parallel to a chord line at the extremity of said wing until the surface of revolution generated by said rotation inter­ sects the lower wing surface. In an aeroplane, a wing having upper and lower 2,515,639. Safety Device for Pressurized Aircraft. 2,514,178. Synchronizing and Speed Control Device. surfaces and having an outer wing panel terminating John J. Draney, La Mesa, Calif., assignor to Con­ John Alfred Chilman, Gloucester, Alfred George in a wing chord section and a wing tip forming an solidated Vultee Aircraft Corporation, San Diego, Mapp, Cheltenham, and Edward Hollingworth extension of said section, said wing tip terminating Calif., a corporation of Delaware. Application April Morris, Ashstead, England, assignors to Rotol in a surface of revolution formed by rotating a lateral 23, 1947. Limited, Gloucester, England, a British company. extension of the upper surface line of said wing at In an aircraft, a pressurized fuselage adapted to be Application June 19, 1946. In Great Britain Septem­ said section about a fore and aft axis of said wing tip maintained at a predetermined pressure independent ber 25, 1944. parallel to but outboard of a chord line of said wing of the atmospheric pressure, a relief valve in said A device for synchronizing and controlling the speed at said section until it intersects the lower surface of fuselage to automatically exhaust said fuselage to the of the engines of a multi-engined aircraft of which one said wing panel, a drop tank having a well in its side atmosphere when the pressure therein exceeds the engine is the master and the others slaves controlled to receive said wing tip, and co-operating locking predetermined value, a landing gear on said aircraft, thereby comprising a master alternating current means carried by said wing and tank for releasably a bleed valve associated with said landing gear having generator the frequency of which is related to a securing said tank to said wing tip, said lateral ex­ an operative connection with said relief valve, and datum speed, means to drive said generator, a dynamo- tension of the upper surface line of said wing at said means on said landing gear to operate said bleed electric machine driven by said master alternating section being extended laterally to a vertical plane valve to open said relief valve when the load of the current generator and associated with the master through said fore and aft wing tip axis. aircraft is supported by said landing gear thereby to engine, for each engine a variable pitch propeller equalize automatically the internal pressure of said driven by the engine, a constant speed governor fuselage with the atmospheric pressure. driven in common with the propeller for adjusting the pitch of the propeller blades to keep the propeller speed constant at a datum for which the governor is set, an alternating current generator driven by each of the slave engines so that its frequency is related to engine speed, a dynamo-electric machine which re­ ceives current from the alternating current generator driven by the slave engine and the generator driven by the master engine and which responds to a fre­ 2,515,069. Wind Tunnel. Colman Zola, Mount quency difference between said two alternating current Vernon, N.Y., assignor to the United States of generators, proportional to the speed differences be­ America as represented by the Secretary of the Navy. tween said engines, and the constant speed governor. Application March 18, 1946, Serial No. 655,310. 2,516,066. Rotor Assembly. Roderick Cristall 2 Claims. (Cl. 73—147.) McLeod, Cropston, and Thomas Edward Callister, A device for examining the behaviour of a body in Barrow-in-Furness, England, Kenneth Watson, Clark- a high speed fluid current, comprising a tunnel for ston, Scotland, and Geoffrey William Bone, Skelling- defining the path of flow of the fluid current, means thorpe, England, assignors to Power Jets (Research for mounting said body within said tunnel, a source & Development) Limited, London, England. Appli­ of high velocity flow of combustion gases, means on cation November 26, 1945. In Great Britain April said source for directing said flow into said tunnel, 27, 1942. and means for injecting a cooling fluid into the A rotor assembly comprising a compressor rotor tunnel in the direction of said combustion gases to having an axial bore and a second coaxial rotor mix therewith prior to the contact of said mixture axially spaced therefrom, a hollow shaft coaxially with said body. attached to said compressor rotor and extending towards said second rotor, a second shaft coaxially rigidly extending from said second rotor towards the compressor rotor and engaged within said hollow shaft for rotation therewith, and screw connecting 2,514,513. Jet Power Plant with Boundary Layer means internally of said shafting exposed for access Control for Aircraft. Nathan C. Price, Los Angeles, thereto through said axial bore for adjustment to Calif., assignor to Lockheed Aircraft Corporation, mutually draw together axially and secure said hollow shaft and said second shaft. 2,515,457. Hydraulic Power Booster for Aircraft Surface Control. James M. Shoemaker, Nichols, Conn., assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware. Appli­ cation September 19, 1944. 316 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Oct 1, 1950

There are no references for this article.