U.S. Patent Specifications

U.S. Patent Specifications November, 1938 366 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,119,089 . Flap Construction. Edward F. 6. A device for testing brake lining comprising, a 2. An airplane construction comprising wings Zaparka, Baltimore, Md., assignor to Zap Develop­ support , means for progressively moving the lining havin g down flow thereover, ailerons operating at men t Corporation, Baltimore, Md., a corporation relative to said support, means to determine the least partially in the downflow, mounting means of Delaware. Application July 21, 1933. Serial "bleeding " of the lining including a heated casing above the wings having recesses therein for No. 681,641. Renewed January 19, 1937. 8 throug h which the lining is passed, means resisting mountin g the ailerons, flaps, and means for oper­ claims. [Class 244-42.] th e movement of the lining for stretching the same, atin g the flaps located at least partially within th e mounting means for the ailerons. means for maintaining the lining heated while it is being stretched, and means for measuring the 2,120,568 . Aeroplane and the Like. Phiroze length of the lining after the "bleeding " operation Pestonji Naz'r, Byfleet, England. Application while it is still stretched. April 11, 1936. Serial No. 73,820. In Great 2,121,429 . Resilient Engine Mount. Serge Britai n April 18, 1935. 5 claims. [Class 244-42.] Gluhareff, Stratford, Conn., assignor, by mesne 1. In an air­ assignments , to United Aircraft Corporation, a craft the com­ corporation of Delaware. Application May 21, bination , with 1935. Serial No. 22,507. 9 claims. [Class 248-5.] a fixed support­ ing wing of invariabl e cross- sectional shape an d camber and havin g a nor­ mally closed slot formed through the rear part thereof, and 4. A combined longitudinal control and stabiliza­ inclined or curved upwardly and backwardly, of tion mechanism, for an airplane provided with an auxiliary plate carried by the wing and movable a control stick, comprising split flaps, a single t o project downwardly and rearwardly there­ cam to operate the said flaps for purposes of from to give auxiliary lift and simultaneously to longitudinal and stabilization control, said single open said slot, said plate also being movable to cam being actuated by the control stick by means project above said wing and increase the drag of the movement of a shaft, for purposes of thereof. 1. A resilient mounting for supporting an engine elevational control, and means mounted on the control stick whereby the shaft may be rotated havin g mounting pads thereon on a frame having 2,121,084 . Production of Beryllium. Osias independently of the control stick for purposes of a n engine mounting ring comprising, pair s of hangers Kruh , Vienna, Austria. Application August 29, stabilization. adapte d to be secured in spaced parallel relation on 1935. Serial No. 38,399. In Austria September 10, said ring t o form engine mounting brackets, mount­ 1934. 25 claims. [Class 75-84.] 2,119,151 . Friction Bearing for Aircraft ing blocks each comprising a forging provided with Contro l Surfaces. Jean Calvy, Paris, France. a pair of spaced parallel sleeves and a centrally Application November 7, 1936. Serial No. located aperture extending therethrough to receive 109,786. 6 claims. [Class 244-87.] a bolt for securing said mounting block t o one of said mountin g pads, a member extending through each of said sleeves and secured to the hangers of the respective brackets receiving said blocks, and a resilient bushing in each of said sleeves surrounding th e respective member. 2,122,631 . Propeller Shaping Machine. Joh n R. Albers, Sioux City, and Gerhard H. Albers, Cherokee, Iowa, assignors to Wincharger Corpora­ tion , Sioux City, Iowa, a corporation of Minnesota. I. In an aircraft including a fixed part and Application October 28, 1935. Serial No. 47,190. a control surface having an axle to be journalled 5 claims. [Class 144-134.] with respect to said part, a friction bearing for 2. A pitch cutting machine comprising a channel, said axle which comprises, in combination, an a carriage received within the channel, means for annula r bearing portion, rigidly connected to attachin g a blank wood strip to the carriage, and said fixed part, provided with a gap on the side mean s for cutting a propeller pitch on said blank thereof nearer to said fixed part, a friction shoe movable radially in said gap, and means for elastically urging said shoe towards the axis of said annular bearing portion, said means forming 1. In the manufacture of beryllium or beryllium a system of elongated shape in the direction of alloys, the process which comprises reducing movement of said shoe and being wholly enclosed beryllium oxide with the aid of carbonaceous in said fixed part and said control surface. material in the presence of a protective gas which is iner t to beryllium at a temperature sufficient to 2,119,305 . Simplified Flap Operating vaporize into said gas the beryllium formed by Means . Edward F. Zaparka, Baltimore, Md., reduction. assignor to Zap Development Corporation, Balti­ more, Md., a corporation of Delaware. Application 2,121,149 . Brake Lining Testing Machine. Jun e 12, 1933. Serial No. 675,486. Renewed William S. James, South Bend, Ind., assignor to December 19, 1936. 18 claims. [Class 244-42.] Bendix Aviation Corporation, South Bend, Ind., a corporation of Delaware. Original application stri p mounted on said channel including a horizontal Januar y 26, 1929. Serial No. 335,178. Divided cuttin g member mounted on said channel, said an d this application March 8, 1935. Serial No. carriage being sloped downwardly across its width 9,929. 14 claims. [Class 265-10.] on the upper surface thereof, said slope being the sam e as th e pitch to be cut, and said carriage being highe r at its forward end to accommodate the taperin g thickness of a propeller blade, means for droppin g said carriage below the level of said cuttin g blades when above the hub portion of the propeller including a pai r of opposed guide members, a rotatable shaft attached at the inner end of said carriage, extensions eccentrically mounted on said shaft and received within the guide members, a trip * The above abstracts of patents granted in the United States membe r attached to said shaft and to one of said are taken, by permission of the Department of Commerce, from the Official Gazette of the United States Patent Office. Printed copies of extensions, a pin attached inwardly of said channel the full specifications can be obtained, price 10 cents each, from the adapte d to force said trip member pivotally about Commissioner of Patents, Washington, D.C., U.S.A. said shaft to cause the shaft to drop during forward Except where otherwise stated, the specification is unaccompanied movemen t of the carriage. 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 (11): 1 – Nov 1, 1938

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030406
Publisher site
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Abstract

November, 1938 366 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,119,089 . Flap Construction. Edward F. 6. A device for testing brake lining comprising, a 2. An airplane construction comprising wings Zaparka, Baltimore, Md., assignor to Zap Develop­ support , means for progressively moving the lining havin g down flow thereover, ailerons operating at men t Corporation, Baltimore, Md., a corporation relative to said support, means to determine the least partially in the downflow, mounting means of Delaware. Application July 21, 1933. Serial "bleeding " of the lining including a heated casing above the wings having recesses therein for No. 681,641. Renewed January 19, 1937. 8 throug h which the lining is passed, means resisting mountin g the ailerons, flaps, and means for oper­ claims. [Class 244-42.] th e movement of the lining for stretching the same, atin g the flaps located at least partially within th e mounting means for the ailerons. means for maintaining the lining heated while it is being stretched, and means for measuring the 2,120,568 . Aeroplane and the Like. Phiroze length of the lining after the "bleeding " operation Pestonji Naz'r, Byfleet, England. Application while it is still stretched. April 11, 1936. Serial No. 73,820. In Great 2,121,429 . Resilient Engine Mount. Serge Britai n April 18, 1935. 5 claims. [Class 244-42.] Gluhareff, Stratford, Conn., assignor, by mesne 1. In an air­ assignments , to United Aircraft Corporation, a craft the com­ corporation of Delaware. Application May 21, bination , with 1935. Serial No. 22,507. 9 claims. [Class 248-5.] a fixed support­ ing wing of invariabl e cross- sectional shape an d camber and havin g a nor­ mally closed slot formed through the rear part thereof, and 4. A combined longitudinal control and stabiliza­ inclined or curved upwardly and backwardly, of tion mechanism, for an airplane provided with an auxiliary plate carried by the wing and movable a control stick, comprising split flaps, a single t o project downwardly and rearwardly there­ cam to operate the said flaps for purposes of from to give auxiliary lift and simultaneously to longitudinal and stabilization control, said single open said slot, said plate also being movable to cam being actuated by the control stick by means project above said wing and increase the drag of the movement of a shaft, for purposes of thereof. 1. A resilient mounting for supporting an engine elevational control, and means mounted on the control stick whereby the shaft may be rotated havin g mounting pads thereon on a frame having 2,121,084 . Production of Beryllium. Osias independently of the control stick for purposes of a n engine mounting ring comprising, pair s of hangers Kruh , Vienna, Austria. Application August 29, stabilization. adapte d to be secured in spaced parallel relation on 1935. Serial No. 38,399. In Austria September 10, said ring t o form engine mounting brackets, mount­ 1934. 25 claims. [Class 75-84.] 2,119,151 . Friction Bearing for Aircraft ing blocks each comprising a forging provided with Contro l Surfaces. Jean Calvy, Paris, France. a pair of spaced parallel sleeves and a centrally Application November 7, 1936. Serial No. located aperture extending therethrough to receive 109,786. 6 claims. [Class 244-87.] a bolt for securing said mounting block t o one of said mountin g pads, a member extending through each of said sleeves and secured to the hangers of the respective brackets receiving said blocks, and a resilient bushing in each of said sleeves surrounding th e respective member. 2,122,631 . Propeller Shaping Machine. Joh n R. Albers, Sioux City, and Gerhard H. Albers, Cherokee, Iowa, assignors to Wincharger Corpora­ tion , Sioux City, Iowa, a corporation of Minnesota. I. In an aircraft including a fixed part and Application October 28, 1935. Serial No. 47,190. a control surface having an axle to be journalled 5 claims. [Class 144-134.] with respect to said part, a friction bearing for 2. A pitch cutting machine comprising a channel, said axle which comprises, in combination, an a carriage received within the channel, means for annula r bearing portion, rigidly connected to attachin g a blank wood strip to the carriage, and said fixed part, provided with a gap on the side mean s for cutting a propeller pitch on said blank thereof nearer to said fixed part, a friction shoe movable radially in said gap, and means for elastically urging said shoe towards the axis of said annular bearing portion, said means forming 1. In the manufacture of beryllium or beryllium a system of elongated shape in the direction of alloys, the process which comprises reducing movement of said shoe and being wholly enclosed beryllium oxide with the aid of carbonaceous in said fixed part and said control surface. material in the presence of a protective gas which is iner t to beryllium at a temperature sufficient to 2,119,305 . Simplified Flap Operating vaporize into said gas the beryllium formed by Means . Edward F. Zaparka, Baltimore, Md., reduction. assignor to Zap Development Corporation, Balti­ more, Md., a corporation of Delaware. Application 2,121,149 . Brake Lining Testing Machine. Jun e 12, 1933. Serial No. 675,486. Renewed William S. James, South Bend, Ind., assignor to December 19, 1936. 18 claims. [Class 244-42.] Bendix Aviation Corporation, South Bend, Ind., a corporation of Delaware. Original application stri p mounted on said channel including a horizontal Januar y 26, 1929. Serial No. 335,178. Divided cuttin g member mounted on said channel, said an d this application March 8, 1935. Serial No. carriage being sloped downwardly across its width 9,929. 14 claims. [Class 265-10.] on the upper surface thereof, said slope being the sam e as th e pitch to be cut, and said carriage being highe r at its forward end to accommodate the taperin g thickness of a propeller blade, means for droppin g said carriage below the level of said cuttin g blades when above the hub portion of the propeller including a pai r of opposed guide members, a rotatable shaft attached at the inner end of said carriage, extensions eccentrically mounted on said shaft and received within the guide members, a trip * The above abstracts of patents granted in the United States membe r attached to said shaft and to one of said are taken, by permission of the Department of Commerce, from the Official Gazette of the United States Patent Office. Printed copies of extensions, a pin attached inwardly of said channel the full specifications can be obtained, price 10 cents each, from the adapte d to force said trip member pivotally about Commissioner of Patents, Washington, D.C., U.S.A. said shaft to cause the shaft to drop during forward Except where otherwise stated, the specification is unaccompanied movemen t of the carriage. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Nov 1, 1938

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