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U.S. Patent Specifications

U.S. Patent Specifications 262 AIRCRAFT ENGINEERING August, 1938 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,111,530 . Lift Intensifier for Aircraft. 1936. Divided and this application December 18, Alexander P. de Seversky, New York, N.Y. 1935. Serial No. 55,052. 2 claims. [Class 29- Application June 29, 1935. Serial No. 29,124. 156.8.] 4 claims. [Class 244-42.] 2. In the manufacture of pro­ 1. An aircraft having streamline wings, adjustable pellers, the process which consists port s along the tops of the wings near their forward of forming a blade with a substan­ edges, and means for opening said ports and for tially cylindrical shank, assembling shifting the port openings toward or from the edges a thrust bearing over the shank, of the wings. an d spreading the end of the shank b y an upsetting operation to form internally braced against bending, torsional, and an enlarged abutment on the end direct stress, and formed with a cavity for the of the shank for engagement with reception of a tank, a tank and means within the th e thrust bearing. tan k for translation of torsional and direct stresses independentl y of the tank, means connecting the tan k to the structure, and having provision for lost 2,114,522 . Steerable Tail Wheel. Arthur motion under the influence of bending stress, G. Butler, Buffalo, N.Y., assignor, by mesne assign­ whereby such stress is not imposed upon the tank, ments , to Curtiss-Wright Corporation, a corpora­ bu t formed and disposed to transmit torsional and tion of New York. Application September 13, direct stress through said tank-carried means, but 1932. Serial No. 632,903. 12 claims. [Class no t to the tank. 244-109.] 2,113,910 . Airfoil. Edward F. Zaparka, Baltimore, Md., assignor to Zap Development Corporation, Baltimore, Md., a corporation of Delaware. Application December 1, 1932. Serial No. 645,294. Renewed December 9, 1936. 30 claims. [Class 244-42.] 2,113,478 . Air Screw with Automatically Variabl e Pitch. Robert Richard Gobereau, Le Par c du Perrcux, France. Application April 9, 1936. Serial No. 73,543. In France April 17, 1935. 3 claims. [Class 170-162.] 1. A variable pitc h propeller comprising in com­ binatio n with an engine shaft, a casing rotatably 1. In tail chassis for aircraft, a bearing, a support mounte d on the journalled in said bearing, a device for ground shaft, a plurality contac t carried by said support, a lever pivoted to of propeller blades 1. A device of the character described compris­ said support and movable longitudinally with carried by the ing an airfoil, split flap members hingedly attached respect thereto, and means for releasably engaging casing, each of the t o said airfoil an d bot h movable with respect thereto, said lever with said support responsive to longi­ propeller blades link members without the airstream over the flap tudina l movement of said lever. being rotatable surfaces carried by the flap members for opening around its longi­ and closing the flaps, and operating means for the tudina l axis, a 2,114,839 . Aircraft Wheel Mechanism. links universally connected at the point of hinged pluralit y of vanes Joseph M. Gwinn, Jr., Buffalo, N.Y., assignor to attachment . movably mounted Consolidated Aircraft Corporation, a corporation of on said casing, Delaware. Application April 24, 1934. Serial No. 2,114,283 . Cathode Ray Pitch and Bank means connecting 722,105. 6 claims. [Class 244-109.] Indicato r for Aircraft. Samuel H. Anderson, said shaft with 1. In a releasable tail wheel steering mechanism For t Monmouth, Occanport, N.J. Application each of said vanes for aircraft, a rotatable tail post having a n externally September 23, 1933. Serial No. 690,753. 12 so that the vanes recessed portion, a control member engaging said claims. [Class 33-204.] [Granted under the act ar e subjected to tail post about its recessed portion, a stop member of March 3, 1883, as amended April 30, 1928; movement simultaneously in response to the trans­ fixed to the aircraft, a latch member guided by said 370 p . G. 757.] mitting engine torque, to the centrifugal force set control member for radial movement with respect 1. An indicator for aircraft, u p by rotation of th e engine shaft and to th e action t o the tail post, the said latch member normally comprising a cathode ray of the surrounding medium, means associated with engaging the said recessed portion thereby locking tub e secured to the craft; each propeller blade for turning the blades and circuit means comprising varyin g the pitch thereof in response to the angular elements responsive t o move­ displacement of said casing with respect to said ment s of the cathode ray of shaft, the movement of said vanes varying said said tube ; means t o orient angula r displacement whereby the incidence of the th e longitudinal axis of said propeller blade is determined by the forces acting tub e t o establish zero deflec­ on said vanes. tion of the ray in relation to th e earth's magnetic field 2,113,692 . Fuel Tank for Aircraft. Edwin durin g normal flight level of Λ. Hughes and Robert J. Minshall, Seattle, Wash., th e craft; and means com­ assignors to Boeing Aircraft Company, Seattle, prising a meter mechanism Wash., a corporation of Washington. Application electrically operative with said elements to indicate May 28, 1936. Serial No. 82,240. 12 claims. deviations of the craft in accordance with deflec­ [Class 244-135.] tions of th e cathode ray relative t o said longitudinal 2. In combination with an aircraft structure axis. 2,114,414 . Method of Making Propeller th e control member to the tail post for rotation • The above abstracts of patents granted in the United States Blades . Frank W. Caldwell, Hartford, Conn., therewith , the said latch member being organized are taken, by permission oí the Department of Commerce, from the assignor, by mesne assignments, to United Aircraft t o move radially upon contact with said stop Official Gaxette of the United Slates Patent Office. Printed copies of the full specifications can bo obtained, price 10 cents each, from the Corporation, a corporation of Delaware. Original membe r at predetermined limits of said rotation, Commissioner of Patents, Washington, D.C., U.S.A. application April 21, 1931. Serial No. 531,685, whereby the control member is disengaged from Except where otherwise silted , the specification is unaccompanied now Patent No. 2,032,254, dated February 25, said tail post. 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 10 (8): 1 – Aug 1, 1938

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030362
Publisher site
See Article on Publisher Site

Abstract

262 AIRCRAFT ENGINEERING August, 1938 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,111,530 . Lift Intensifier for Aircraft. 1936. Divided and this application December 18, Alexander P. de Seversky, New York, N.Y. 1935. Serial No. 55,052. 2 claims. [Class 29- Application June 29, 1935. Serial No. 29,124. 156.8.] 4 claims. [Class 244-42.] 2. In the manufacture of pro­ 1. An aircraft having streamline wings, adjustable pellers, the process which consists port s along the tops of the wings near their forward of forming a blade with a substan­ edges, and means for opening said ports and for tially cylindrical shank, assembling shifting the port openings toward or from the edges a thrust bearing over the shank, of the wings. an d spreading the end of the shank b y an upsetting operation to form internally braced against bending, torsional, and an enlarged abutment on the end direct stress, and formed with a cavity for the of the shank for engagement with reception of a tank, a tank and means within the th e thrust bearing. tan k for translation of torsional and direct stresses independentl y of the tank, means connecting the tan k to the structure, and having provision for lost 2,114,522 . Steerable Tail Wheel. Arthur motion under the influence of bending stress, G. Butler, Buffalo, N.Y., assignor, by mesne assign­ whereby such stress is not imposed upon the tank, ments , to Curtiss-Wright Corporation, a corpora­ bu t formed and disposed to transmit torsional and tion of New York. Application September 13, direct stress through said tank-carried means, but 1932. Serial No. 632,903. 12 claims. [Class no t to the tank. 244-109.] 2,113,910 . Airfoil. Edward F. Zaparka, Baltimore, Md., assignor to Zap Development Corporation, Baltimore, Md., a corporation of Delaware. Application December 1, 1932. Serial No. 645,294. Renewed December 9, 1936. 30 claims. [Class 244-42.] 2,113,478 . Air Screw with Automatically Variabl e Pitch. Robert Richard Gobereau, Le Par c du Perrcux, France. Application April 9, 1936. Serial No. 73,543. In France April 17, 1935. 3 claims. [Class 170-162.] 1. A variable pitc h propeller comprising in com­ binatio n with an engine shaft, a casing rotatably 1. In tail chassis for aircraft, a bearing, a support mounte d on the journalled in said bearing, a device for ground shaft, a plurality contac t carried by said support, a lever pivoted to of propeller blades 1. A device of the character described compris­ said support and movable longitudinally with carried by the ing an airfoil, split flap members hingedly attached respect thereto, and means for releasably engaging casing, each of the t o said airfoil an d bot h movable with respect thereto, said lever with said support responsive to longi­ propeller blades link members without the airstream over the flap tudina l movement of said lever. being rotatable surfaces carried by the flap members for opening around its longi­ and closing the flaps, and operating means for the tudina l axis, a 2,114,839 . Aircraft Wheel Mechanism. links universally connected at the point of hinged pluralit y of vanes Joseph M. Gwinn, Jr., Buffalo, N.Y., assignor to attachment . movably mounted Consolidated Aircraft Corporation, a corporation of on said casing, Delaware. Application April 24, 1934. Serial No. 2,114,283 . Cathode Ray Pitch and Bank means connecting 722,105. 6 claims. [Class 244-109.] Indicato r for Aircraft. Samuel H. Anderson, said shaft with 1. In a releasable tail wheel steering mechanism For t Monmouth, Occanport, N.J. Application each of said vanes for aircraft, a rotatable tail post having a n externally September 23, 1933. Serial No. 690,753. 12 so that the vanes recessed portion, a control member engaging said claims. [Class 33-204.] [Granted under the act ar e subjected to tail post about its recessed portion, a stop member of March 3, 1883, as amended April 30, 1928; movement simultaneously in response to the trans­ fixed to the aircraft, a latch member guided by said 370 p . G. 757.] mitting engine torque, to the centrifugal force set control member for radial movement with respect 1. An indicator for aircraft, u p by rotation of th e engine shaft and to th e action t o the tail post, the said latch member normally comprising a cathode ray of the surrounding medium, means associated with engaging the said recessed portion thereby locking tub e secured to the craft; each propeller blade for turning the blades and circuit means comprising varyin g the pitch thereof in response to the angular elements responsive t o move­ displacement of said casing with respect to said ment s of the cathode ray of shaft, the movement of said vanes varying said said tube ; means t o orient angula r displacement whereby the incidence of the th e longitudinal axis of said propeller blade is determined by the forces acting tub e t o establish zero deflec­ on said vanes. tion of the ray in relation to th e earth's magnetic field 2,113,692 . Fuel Tank for Aircraft. Edwin durin g normal flight level of Λ. Hughes and Robert J. Minshall, Seattle, Wash., th e craft; and means com­ assignors to Boeing Aircraft Company, Seattle, prising a meter mechanism Wash., a corporation of Washington. Application electrically operative with said elements to indicate May 28, 1936. Serial No. 82,240. 12 claims. deviations of the craft in accordance with deflec­ [Class 244-135.] tions of th e cathode ray relative t o said longitudinal 2. In combination with an aircraft structure axis. 2,114,414 . Method of Making Propeller th e control member to the tail post for rotation • The above abstracts of patents granted in the United States Blades . Frank W. Caldwell, Hartford, Conn., therewith , the said latch member being organized are taken, by permission oí the Department of Commerce, from the assignor, by mesne assignments, to United Aircraft t o move radially upon contact with said stop Official Gaxette of the United Slates Patent Office. Printed copies of the full specifications can bo obtained, price 10 cents each, from the Corporation, a corporation of Delaware. Original membe r at predetermined limits of said rotation, Commissioner of Patents, Washington, D.C., U.S.A. application April 21, 1931. Serial No. 531,685, whereby the control member is disengaged from Except where otherwise silted , the specification is unaccompanied now Patent No. 2,032,254, dated February 25, said tail post. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Aug 1, 1938

There are no references for this article.