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U.S. Patent Specifications

U.S. Patent Specifications 86 AIRCRAFT ENGINEERING March, 1937 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. airfoil, a crank for actuating said connecting rod, an d means for moving said crank through a limited arc , said crank being positioned to form an acute angle with said connecting-rod at the median point of said arc, whereby motion of said crank in one direction will swing said crank and connecting-rod pas t dead centre to produce first an increasing and the n a decreasing tilt of said aerofoil in one direc­ tion, and motion of said crank in the opposite direction will produce a constantly increasing opposite tilt of greater magnitude. 2,056,354 . Rate of Clim b Indicator . Erhard Horn,Leipzig , Germany. Application Sept. 9, 1935. Serial No. 39,822. In Germany Sept. 22, 1934. 2,057,010 . Buffle for Air-Cooled Cylinders. 1 Claim. [C1. 264-1.] Roland Chilton, Ridgewood, N. J., assignor, by A rat e of climb indicator comprising a thermally mesne assignments, to The Reed Propeller Co., insulated reservoir, a circular chamber, a stationary Inc., Garden City, N. Y., a corporation of New partitio n wall arranged in said chamber, a hft York. Application Feb. 15, 1932. Serial No. rotatabl y mounted in the axis of said chamber, a 592,998. 3 Claims. [Class 123-171.] pressure plate rotatable with said shaft in said 3 . In an air-cooled engine, including a pair of chamber, spring means normally retaining said spaced finned cylinders, a baffle spanning said pressure plate in predetermined position, means cylinders on one side thereof, said baffle having 2,054,133 . Internal Combustion Engine. bearing portions for fitting engagement between Harr y J,. McPherson, Memphis, Tenn. Application adjacen t fins at the upper and lower portions of May 29, 1930. Serial No . 45(5,890. Renewed March 24, the respective cylinders, a bar spanning said 1934. 6 Claims. [C1. 123-171.] cylinders lying on the opposite side thereof from 1. Λ radial, air cooled, aircraft engine, said said baffle and having bearing portions for fitting engine including cylinders having parts carried engagement between the fins of the cylinders, and b y and extending beyond the heads thereof, and means for adjustably clamping said bar to said havin g cooling fins, a cowl of substantially stream­ baffle, said means lying in the inter-cylinder space. line external configuration around said engine, including said head carried parts, and preventing 2,057,339 . Airplane Wing Structure. radial airflow in the zone of the cylinders of said Pierre Ernest Mercier, Paris, France. Application Mar. 9, 1935. Serial No. 10,269. In France, engine, said cowl having openings for entrance and Sept. 6, 1934. 11 claims. [Class 244-31.] exit of cooling air, such openings being a sub­ stantia l distance forward and rearward respectively 1. In an aeroplane wing, a supporting structure, a box-like wing member supported at opposite from the centre lines of the cylinders of said engine lateral sides by said supporting structure and so as to minimize eddy formation by said cylinders, extendin g outwardly therefrom, said box-like means disposed between said cylinder heads and structur e having lateral sides thereof extending said cowl substantially preventing air flow past said longitudinally of the wing, other sides of said box­ parts , and means, co-operating with said first means an d said cowl, to confine substantially the entire flow of said cooling air between the cooling fins connecting said chamber a t one side of said pressure plat e with said reservoir, and means connecting the of said cylinders. chambe r a t the opposite side of said pressure plate wit h the atmosphere, said pressure plate being 2,054,961 . Lateral Control System for arranged to provide a gap between the edges thereof Aircraft . Edmund T. Allen, Enchutas, Arthur L. an d the walls of said chamber, the dimensions of Klein, Los Angeles, Clark B. Millikan, Pasadena, said gap being such that it serves as a capillary an d John Iv. Northrop, Glendale, Calif., assignors orifice whereby upon occurrence of a pressure t o The Northrop Corporation, Inglewood, Calif., difference between the atmospheric air and the air a corporation of California. Application June 21, in said reservoir, the flow of air through said gap 1933. Serial No. 676,892. 2 Claims. [C1. 244-29.] causes displacement of the pressure plat e an d shaft. 1. In combination, an aeroplane wing, a lateral control surface comprising an auxiliary aerofoil 2,056,938 . Engine Mount. Corydon M. like structur e adjacent said longitudinally-extending hinged above the upper surface of the forward Johnson , Freeport, N. Y. Application Aug. S, sides converging inwardly and with said longitudin­ half of a laterally extending portion of said wing, 1935. Serial No. 35,310. 2 Claims. [Class 248-5.] ally extended sides defining obtuse angles, trans­ an d control means for said aerofoil comprising 1. Means for mounting an engine on an aero­ versely-spaced stiffening members connecting each a connecting-rod pivotally connected to tilt said plan e for absorbing and preventing the trans­ longitudinally extending side with its adjacent mission of the vibrations of said engine to said converging side of said box-like structure, means aeroplane, said means comprising a self-contained for connecting opposite lateral sides of said box- unit , including a pair of relatively movable rigid like structure to the supporting structure adjacent members with shock absorbing means there­ th e juncture of said longitudinally-extending and between, one of said rigid members being secured said converging sides, and means for connecting to said engine and the other member constituting th e inner ends of said converging sides to said a structural part of said aeroplane, said rigid supportin g structure. members comprising an inner and an outer spaced 2,060,858 . Method of Making Tie Rods metallic hollow tube substantially in the form of a an d Blank therefore. Louis W. G. Flynt, East ring, said shock absorbing means comprising a Orange, N. J., assignor to Breeze Corporations, resilient and compressible mass bonded to each of Inc., Newark, N. J. Application Oct. 19, 1933. said members. Serial No. 694,276. 15 claims. [Class 29-148.] 1. The herein described method of making a tie rod, which consists of forming a body of metal of circular contour having streamline ribs a t opposite * The above abstracts or patents granted in the United States sides and reducing the ends to circular shape and are taken, by permission of the Department of Commerce, from the th e intermediate portion to streamline shape, Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the leaving the rod of approximately uniform cross- Commissioner of Patents, Washington, D.C., U.S.A. sectional area from end to end and polishing and Except where otherwise stated, the specification is unaccompanied platin g the body to reduce corrosion and wear. by drawings if none is reproduced. 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 9 (3): 1 – Mar 1, 1937
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Emerald Publishing
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Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030164
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Abstract

86 AIRCRAFT ENGINEERING March, 1937 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. airfoil, a crank for actuating said connecting rod, an d means for moving said crank through a limited arc , said crank being positioned to form an acute angle with said connecting-rod at the median point of said arc, whereby motion of said crank in one direction will swing said crank and connecting-rod pas t dead centre to produce first an increasing and the n a decreasing tilt of said aerofoil in one direc­ tion, and motion of said crank in the opposite direction will produce a constantly increasing opposite tilt of greater magnitude. 2,056,354 . Rate of Clim b Indicator . Erhard Horn,Leipzig , Germany. Application Sept. 9, 1935. Serial No. 39,822. In Germany Sept. 22, 1934. 2,057,010 . Buffle for Air-Cooled Cylinders. 1 Claim. [C1. 264-1.] Roland Chilton, Ridgewood, N. J., assignor, by A rat e of climb indicator comprising a thermally mesne assignments, to The Reed Propeller Co., insulated reservoir, a circular chamber, a stationary Inc., Garden City, N. Y., a corporation of New partitio n wall arranged in said chamber, a hft York. Application Feb. 15, 1932. Serial No. rotatabl y mounted in the axis of said chamber, a 592,998. 3 Claims. [Class 123-171.] pressure plate rotatable with said shaft in said 3 . In an air-cooled engine, including a pair of chamber, spring means normally retaining said spaced finned cylinders, a baffle spanning said pressure plate in predetermined position, means cylinders on one side thereof, said baffle having 2,054,133 . Internal Combustion Engine. bearing portions for fitting engagement between Harr y J,. McPherson, Memphis, Tenn. Application adjacen t fins at the upper and lower portions of May 29, 1930. Serial No . 45(5,890. Renewed March 24, the respective cylinders, a bar spanning said 1934. 6 Claims. [C1. 123-171.] cylinders lying on the opposite side thereof from 1. Λ radial, air cooled, aircraft engine, said said baffle and having bearing portions for fitting engine including cylinders having parts carried engagement between the fins of the cylinders, and b y and extending beyond the heads thereof, and means for adjustably clamping said bar to said havin g cooling fins, a cowl of substantially stream­ baffle, said means lying in the inter-cylinder space. line external configuration around said engine, including said head carried parts, and preventing 2,057,339 . Airplane Wing Structure. radial airflow in the zone of the cylinders of said Pierre Ernest Mercier, Paris, France. Application Mar. 9, 1935. Serial No. 10,269. In France, engine, said cowl having openings for entrance and Sept. 6, 1934. 11 claims. [Class 244-31.] exit of cooling air, such openings being a sub­ stantia l distance forward and rearward respectively 1. In an aeroplane wing, a supporting structure, a box-like wing member supported at opposite from the centre lines of the cylinders of said engine lateral sides by said supporting structure and so as to minimize eddy formation by said cylinders, extendin g outwardly therefrom, said box-like means disposed between said cylinder heads and structur e having lateral sides thereof extending said cowl substantially preventing air flow past said longitudinally of the wing, other sides of said box­ parts , and means, co-operating with said first means an d said cowl, to confine substantially the entire flow of said cooling air between the cooling fins connecting said chamber a t one side of said pressure plat e with said reservoir, and means connecting the of said cylinders. chambe r a t the opposite side of said pressure plate wit h the atmosphere, said pressure plate being 2,054,961 . Lateral Control System for arranged to provide a gap between the edges thereof Aircraft . Edmund T. Allen, Enchutas, Arthur L. an d the walls of said chamber, the dimensions of Klein, Los Angeles, Clark B. Millikan, Pasadena, said gap being such that it serves as a capillary an d John Iv. Northrop, Glendale, Calif., assignors orifice whereby upon occurrence of a pressure t o The Northrop Corporation, Inglewood, Calif., difference between the atmospheric air and the air a corporation of California. Application June 21, in said reservoir, the flow of air through said gap 1933. Serial No. 676,892. 2 Claims. [C1. 244-29.] causes displacement of the pressure plat e an d shaft. 1. In combination, an aeroplane wing, a lateral control surface comprising an auxiliary aerofoil 2,056,938 . Engine Mount. Corydon M. like structur e adjacent said longitudinally-extending hinged above the upper surface of the forward Johnson , Freeport, N. Y. Application Aug. S, sides converging inwardly and with said longitudin­ half of a laterally extending portion of said wing, 1935. Serial No. 35,310. 2 Claims. [Class 248-5.] ally extended sides defining obtuse angles, trans­ an d control means for said aerofoil comprising 1. Means for mounting an engine on an aero­ versely-spaced stiffening members connecting each a connecting-rod pivotally connected to tilt said plan e for absorbing and preventing the trans­ longitudinally extending side with its adjacent mission of the vibrations of said engine to said converging side of said box-like structure, means aeroplane, said means comprising a self-contained for connecting opposite lateral sides of said box- unit , including a pair of relatively movable rigid like structure to the supporting structure adjacent members with shock absorbing means there­ th e juncture of said longitudinally-extending and between, one of said rigid members being secured said converging sides, and means for connecting to said engine and the other member constituting th e inner ends of said converging sides to said a structural part of said aeroplane, said rigid supportin g structure. members comprising an inner and an outer spaced 2,060,858 . Method of Making Tie Rods metallic hollow tube substantially in the form of a an d Blank therefore. Louis W. G. Flynt, East ring, said shock absorbing means comprising a Orange, N. J., assignor to Breeze Corporations, resilient and compressible mass bonded to each of Inc., Newark, N. J. Application Oct. 19, 1933. said members. Serial No. 694,276. 15 claims. [Class 29-148.] 1. The herein described method of making a tie rod, which consists of forming a body of metal of circular contour having streamline ribs a t opposite * The above abstracts or patents granted in the United States sides and reducing the ends to circular shape and are taken, by permission of the Department of Commerce, from the th e intermediate portion to streamline shape, Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the leaving the rod of approximately uniform cross- Commissioner of Patents, Washington, D.C., U.S.A. sectional area from end to end and polishing and Except where otherwise stated, the specification is unaccompanied platin g the body to reduce corrosion and wear. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Mar 1, 1937

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