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U.S. Patent Specifications

U.S. Patent Specifications 236 AIRCRAFT ENGINEERING August, 1936 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,038,531 . Attitude Indicator for Aircraft. Presto n R. Bassett, Rockville Centre, and Elmer A. Sperry , Jr., Brooklyn, N.Y., assignors to Sperry Gyroscope Company, Inc., Brooklyn, N.Y., a corporation of New York. Original application May 23, 1929. Serial No. 365,460, renewed August 25, 1934, now Patent No. 1,982,851. December 4, 1934. Divided and this application November 15, 1934. Serial No. 753,176. In Japan May 5, 1930. 5 Claims. [Class 33-204.] 2. In a level flight indicator for aeroplanes, a gyroscope, a gimbal ring mounting therefore having 2,041,786 . Boundary Layer Control for it s major axis trunnions athwartships of the Wings . Edward A. Stalker, Ann Arbor, Mich. aeroplane and minor axis trunnions fore and aft, an Application March 10, 1932. Serial No. 597,993. indicator representing the aircraft pivoted on the Renewed Oct. 12, 1935. 7 claims. [Class 244-12.] rea r of said gimbal facing the aviator, and gearing 3 . In a wing, associated with a relative flow of connecting said indicator and gyroscope about said fluid ; a means t o interpose, between a wing and minor axis to tilt the indicator relatively to the it s boundary layer, a stream of fluid of energy conten t substantially as large as tha t of the rela­ 2,039,103 . Cooling Fins. Andre J. Meyer, tiv e flow, comprising a wing body possessing in Detroit, Mich., assignor to Continental Motors it s upper surface a spanwise slot extending at Corporation, Detroit, Mich., a corporation of "Vir­ least along a major portion of the semi-span, a ginia. Application Dec. 26, 1931. Serial No. divided upper surface to the rear of the said slot 583,288. 3 Claims. [Class 123-171.] t o form a second slot and an induction opening 1. In an internal combustion engine of the air- leading into the wing, a conduit to connect the cooled type having a cylinder structure provided inductio n opening and the forward slot, and a wit h a cylinder, a cylinder head structure closing fluid conveying conduit to provide a rearward one end of said cylinder and having an annular flow through th e exit of th e second slot. flange seated on the outer end of the cylinder structure , said flange carrying a plurality of out­ aircraft in the same direction as the craft banks wardl y extending cooling fins an d having a plurality 2,041,849 . Propeller. Ernest G. McCauley, relativel y to the gyroscope or horizon. of counterbored holes extendin g there-through, and Dayton , Ohio. Application July 1, 1932. Serial 5. A means for mounting aircraft attitude headed fasteners extending through said holes for No . 620,462. 48 claims. [Class 170-159.] indicatin g instruments in back of the instrument connection to said cylinder structure, the heads of 1. A propeller blade having an outer portion of panel comprising spaced knife edge bearings said fasteners lying substantially within said aerofoil cross-section of the character described, providing a two point support for th e upper par t of counterbores respectively to provide smooth air said outer portion gradually increasing in cross- th e instrument, a single third point of support at flow across said cylinder structure in the vicinity sectional area from the tip inward, a cylindrical th e bottom thereof clamping th e same t o th e panel, of said fins. roo t portion adapted for anchorage to a propeller an d adjustable means for adjusting the bottom of hu b and a shank portion exterior of said hub said insturment at said point toward and away connection of cross-section gradually varying from the panel to compensate for different loading 2,039,135 . Landing Gear. Robert S. Waugh, from a cylindrical to the outer portion aerofoil conditions of the aircraft. Alhambra , and Whiteman Reed, Huntingdon Park, Calif., assignors, by mesne assignments, to The 2,038,898 . Aircraft Brake. Ernest Frederick Cleveland Pneumatic Tool Company, Cleveland, Goodyear, Moxhall Park, Wishaw, Joseph Wright, Ohio, a corporation of Ohio. Application May 11, Stoke Park, Coventry, and Henr y William Trevaskis, 1931. Serial No. 536,566. 3 Claims. [Class Keresley, Coventry, England, assignors to Dunlop 267-64.] Rubbe r Company Limited, London, England, a British Company. Application May 4, 1934. Serial No. 723,876. In Great Britain May 10, 1933. 11 Claims. [Class 188-152.] section, said blade having a longitudinally dis­ posed conical bore extending throughout the 1. Fluid brake pressure apparatus comprising a length of the root portion and into the shank fluid container, a pair of pistons movable to force portion, said conical bore being of such diameter fluid from said container to respective brake an d depth as to provide a gradually increasing apparatus , and mechanism displaceable longitu­ cross-sectional area of the blade from the tip dinally and angularly within said container t o move toward s the root and substantially throughout said pistons through a variable distance to exert a th e entire length of the blade. variabl e pressure. 2,042,099 . One-Piece Hollow Steel Pro­ peller . Walter S. Hoover, Girard, Pa., assignor of one-half to Patrick H. Crow, Meadville, Pa. Application Oct. 27, 1931. Serial No. 571,342. 3 claims. [Class 170-159.] 1. A hollow propeller blade structure comprising a one-piece sheet metal blank varying in wall section from maximum thickness a t the blade root t o minimum thickness at its tip the longitudinal edges of which arc folded to constitute comple­ mentar y abutments which arc welded on the back of th e blade at substantially the centre thereof. 1. I n a hydro-pneumatic strut, a pair of telescop­ ing cylinders, the inner cylinder carrying a piston slidably contacting with the outer cylinder, a meterin g pin carried by one of said cylinders and a check tube carried by the other of said cylinders, said pin being concentric with said tube, and a partia l closure for the inner end of said tube * The above abstracts of patents granted in the United States are taken, by permission of the Department of Commerce, from the surroundin g said pin, whereby the flow of incom­ Official Gazette of the United Stales Patent Office. Printed copies of pressible fluid into and out of said tube is restricted, the full specifications can be obtained, price 10 cents each, from the said tube carrying a valve opening into the inner Commissioner of Patents, Washington, D.C., U.S.A. Except where otherwise stated, the specification is unaccompanied cylinder which closes on the rebound stroke. 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 8 (8): 1 – Aug 1, 1936

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030087
Publisher site
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Abstract

236 AIRCRAFT ENGINEERING August, 1936 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,038,531 . Attitude Indicator for Aircraft. Presto n R. Bassett, Rockville Centre, and Elmer A. Sperry , Jr., Brooklyn, N.Y., assignors to Sperry Gyroscope Company, Inc., Brooklyn, N.Y., a corporation of New York. Original application May 23, 1929. Serial No. 365,460, renewed August 25, 1934, now Patent No. 1,982,851. December 4, 1934. Divided and this application November 15, 1934. Serial No. 753,176. In Japan May 5, 1930. 5 Claims. [Class 33-204.] 2. In a level flight indicator for aeroplanes, a gyroscope, a gimbal ring mounting therefore having 2,041,786 . Boundary Layer Control for it s major axis trunnions athwartships of the Wings . Edward A. Stalker, Ann Arbor, Mich. aeroplane and minor axis trunnions fore and aft, an Application March 10, 1932. Serial No. 597,993. indicator representing the aircraft pivoted on the Renewed Oct. 12, 1935. 7 claims. [Class 244-12.] rea r of said gimbal facing the aviator, and gearing 3 . In a wing, associated with a relative flow of connecting said indicator and gyroscope about said fluid ; a means t o interpose, between a wing and minor axis to tilt the indicator relatively to the it s boundary layer, a stream of fluid of energy conten t substantially as large as tha t of the rela­ 2,039,103 . Cooling Fins. Andre J. Meyer, tiv e flow, comprising a wing body possessing in Detroit, Mich., assignor to Continental Motors it s upper surface a spanwise slot extending at Corporation, Detroit, Mich., a corporation of "Vir­ least along a major portion of the semi-span, a ginia. Application Dec. 26, 1931. Serial No. divided upper surface to the rear of the said slot 583,288. 3 Claims. [Class 123-171.] t o form a second slot and an induction opening 1. In an internal combustion engine of the air- leading into the wing, a conduit to connect the cooled type having a cylinder structure provided inductio n opening and the forward slot, and a wit h a cylinder, a cylinder head structure closing fluid conveying conduit to provide a rearward one end of said cylinder and having an annular flow through th e exit of th e second slot. flange seated on the outer end of the cylinder structure , said flange carrying a plurality of out­ aircraft in the same direction as the craft banks wardl y extending cooling fins an d having a plurality 2,041,849 . Propeller. Ernest G. McCauley, relativel y to the gyroscope or horizon. of counterbored holes extendin g there-through, and Dayton , Ohio. Application July 1, 1932. Serial 5. A means for mounting aircraft attitude headed fasteners extending through said holes for No . 620,462. 48 claims. [Class 170-159.] indicatin g instruments in back of the instrument connection to said cylinder structure, the heads of 1. A propeller blade having an outer portion of panel comprising spaced knife edge bearings said fasteners lying substantially within said aerofoil cross-section of the character described, providing a two point support for th e upper par t of counterbores respectively to provide smooth air said outer portion gradually increasing in cross- th e instrument, a single third point of support at flow across said cylinder structure in the vicinity sectional area from the tip inward, a cylindrical th e bottom thereof clamping th e same t o th e panel, of said fins. roo t portion adapted for anchorage to a propeller an d adjustable means for adjusting the bottom of hu b and a shank portion exterior of said hub said insturment at said point toward and away connection of cross-section gradually varying from the panel to compensate for different loading 2,039,135 . Landing Gear. Robert S. Waugh, from a cylindrical to the outer portion aerofoil conditions of the aircraft. Alhambra , and Whiteman Reed, Huntingdon Park, Calif., assignors, by mesne assignments, to The 2,038,898 . Aircraft Brake. Ernest Frederick Cleveland Pneumatic Tool Company, Cleveland, Goodyear, Moxhall Park, Wishaw, Joseph Wright, Ohio, a corporation of Ohio. Application May 11, Stoke Park, Coventry, and Henr y William Trevaskis, 1931. Serial No. 536,566. 3 Claims. [Class Keresley, Coventry, England, assignors to Dunlop 267-64.] Rubbe r Company Limited, London, England, a British Company. Application May 4, 1934. Serial No. 723,876. In Great Britain May 10, 1933. 11 Claims. [Class 188-152.] section, said blade having a longitudinally dis­ posed conical bore extending throughout the 1. Fluid brake pressure apparatus comprising a length of the root portion and into the shank fluid container, a pair of pistons movable to force portion, said conical bore being of such diameter fluid from said container to respective brake an d depth as to provide a gradually increasing apparatus , and mechanism displaceable longitu­ cross-sectional area of the blade from the tip dinally and angularly within said container t o move toward s the root and substantially throughout said pistons through a variable distance to exert a th e entire length of the blade. variabl e pressure. 2,042,099 . One-Piece Hollow Steel Pro­ peller . Walter S. Hoover, Girard, Pa., assignor of one-half to Patrick H. Crow, Meadville, Pa. Application Oct. 27, 1931. Serial No. 571,342. 3 claims. [Class 170-159.] 1. A hollow propeller blade structure comprising a one-piece sheet metal blank varying in wall section from maximum thickness a t the blade root t o minimum thickness at its tip the longitudinal edges of which arc folded to constitute comple­ mentar y abutments which arc welded on the back of th e blade at substantially the centre thereof. 1. I n a hydro-pneumatic strut, a pair of telescop­ ing cylinders, the inner cylinder carrying a piston slidably contacting with the outer cylinder, a meterin g pin carried by one of said cylinders and a check tube carried by the other of said cylinders, said pin being concentric with said tube, and a partia l closure for the inner end of said tube * The above abstracts of patents granted in the United States are taken, by permission of the Department of Commerce, from the surroundin g said pin, whereby the flow of incom­ Official Gazette of the United Stales Patent Office. Printed copies of pressible fluid into and out of said tube is restricted, the full specifications can be obtained, price 10 cents each, from the said tube carrying a valve opening into the inner Commissioner of Patents, Washington, D.C., U.S.A. Except where otherwise stated, the specification is unaccompanied cylinder which closes on the rebound stroke. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Aug 1, 1936

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