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U.S. Patent Specifications

U.S. Patent Specifications May, 1939 220 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,132,682 . Tail Wheel and the Like for 2,135,464 . Aircraft Wine Structure. Aircraft . (George Herbert Dowty, Cheltenham, Alexander P. de Seversky, New York, N.Y. England . Application April 15, 1936. Serial No. Application June 29, 1935. Serial No. 29,123. 74,(>03. In Great Britain April 17, 1935. 6 1 Claim. [Class 244-123.] Claims. [Class 244-102.] I n an aeroplane wing-structure, a plurality of 1. An aircraft tail-support mount­ separatel y pre-fabricated units each comprising a ing comprising in combination a to p sheathing and a bottom sheathing connected support-carrying element, a mounting b y vertical webbing extending parallel to the element carrying said support-carrying direction of flight and each being open at its front element, shock absorbing means oper­ face and its rear face, said units meeting on separate ativ e between said elements, means vertical webs extending longitudinally of the wing mountin g the elements for castoring an d having vertical angle-members serving as rotation , means for freeing said ele­ mean s for connexion between meeting units, the ment s for castoring rotation when said unit s thus constituting the wing multicellular from body, said formers also forming interconnexions shock absorbing means is loaded, leading-edge to trailing-edge and from tip to root, between the tubular members at opposite sides of mean s for restoring specific alignment n o single one of said united units carrying even the th e body, an external cover of sheet material sur­ between said elements when said major portion of the wing-loading, and the webs roundin g the tubular members (having line contact shock absorbing means is unloaded, which extend parallel to the direction of flight with each of the tubular members) whereby the a bearing for attaching said mounting carryin g vertical and diagonal angles constituting cover is shaped by the tubular members and means means to an aircraft, means operable chordwise trussing between the longitudinal webs, for attaching said cover to said tubular members. independently of the shock absorbing whereby the majority of the number of said webs and castoring means for swinging said extendin g parallel to the flight-direction, in dis­ 2,136,919 . Copper Alloys of Improved mountin g means, support-carrying connected locations, may be destroyed and all of Characteristics . Franz It. Hensel and Earl I. means , shock absorbing means, and said longitudinally-extending webs except any two Larsen, Indianapolis, Ind., assignors to P. R. castoring means as a whole about said ma y be destroyed, without thereby destroying the Mallory & Co., Inc. , Indianapolis, Ind., a corporation bearing for retraction of the wheel. integrit y of the wing itself. of Delaware. No Drawing. Application July 13, 1938. Serial No. 218,970. 3 Claims. [Class 75-154.] 2,132,950 . Self-Locking Rivet. James L. 1. An age-hardened alloy composed of : Green, Cleveland, Ohio, assignor to The Indemse Pe r cent Corporation, a corporation of Michigan. Applica­ Beryllium .. .. .. .. . . 0·03- 3 tion May 15, 1937. Serial No. 142,786. 5 Claims. Silver .. .. .. .. . . 0·05- 4 [Class 85-4.] Tin .. .. .. .. .. . . 0·05-12 1. A self-locking rivet comprising a tubular body Balance substantially all copper. havin g a tapered inside bore, frictional projections 2,135,887 . Blade for Airscrew s and th e Like. Characterized by high hardness and electrical on the tapered inside surface of said tubular body, Charles Richard Fairey, Hayes, England. Applica­ conductivity , and further characterized by the fact a material clamping head on the end of said body tion June 3, 1936. Serial No. 83,395. In Great tha t its hardness and conductivity are not perma­ adjacent the smaller end of the tapered bore, a Britain June 7, 1935. 9 Claims. [Class 170-172.] nentl y adversely affected by elevated temperatures. smaller tubular body of a diameter suitable for 1. An airscrew blade having a tip portion and a telescoping into the first men­ hu b portion, a slot only in that part of the length 2,137,382 . Wing Flap. Raymond C. Blaylock, tioned body, a material clamping of the blade remote from the tip portion and sub­ Franci s P. Bassett, and Edward R. Child, Kenmore, head on one end of said smaller stantiall y in that half of the blade adjacent the body, frictional projections on the hu b portion, said slot extending obliquely from the oute r surface of the smaller body rea r face of the blade adjacent the leading edge of for frictionally engaging the pro­ said blade, to the front face of the blade a t a point jections on the inner surface of remote from said leading edge whereby air flows th e other body to secure said through said slot from the rear to the front face of bodies in telescoped relation for clamping material said blade. between said clamping heads, and slits in the inner end of said smaller body to provide inwardly directed resilient fingers thereon. 2,134,447 . Aircraft Construction. Herman N.Y., and Robert R. Osborn, New Orleans, La., G. Klemm, Baltimore, and Berthoud C. Boulton, assignors, by mesne assignments, to Curtiss-Wright Towson, Md., assignors to The Glenn L. Martin Corporation, a corporation of New York. Applica­ Company, Baltimore, Md. Original application tion November 6, 1936. Serial No. 109,430. 13 December 29, 1936. Serial No. 118,072. Divided Claims. [Class 244-42.] an d this application December 7, 1937. Serial No. 1. In an aircraft wing, a fitting pivoted thereto, 178,462. 2 Claims. [Class 244-53.] split trailing flaps pivoted to said fitting for opposed 1. In an aircraft having an aerofoil, an engine, a movemen t relative to said fitting, and unitary means carburetto r attached to said engine, and a cowling for selectively moving said flaps and fitting bodily relative to said wing and for moving said flaps relative to each other and to said fitting. surrounding said engine, an exhaust gas and carburetto r air intake system comprising an 2,136,265 . Construction of Wings , Surfaces, exhaus t conduit, a first means to convey air from an d Fuselages for Aircraft. George Edward adjacen t said engine in heat dissipating exchange Petty , Brough, near Hull, England, assignor to 2,137,385 . Aircraft Control System . Arthur with said conduit to an exhaust port in an area of Blackburn Aircraft Limited, Brough, near Hull, G. Butler, Buffalo, N.Y., assignor to Curtiss-Wright negative pressure on a surface of said aerofoil, a England . Application October 11, 1937, Serial Corporation, a corporation of Delaware. Applica­ second means including a portion of said first means No. 168,468. In Great Britain October 12, 1936. tion April 16, 1937. Serial No. 137,175. 5 Claims. for conveying air in heat exchange relation with 8 Claims. [Class 244-123.] [Class 244-87.] said conduit to said carburettor, and means for I. An aircraft body comprising, in combination, 1. A control system for aircraft having a stream­ rendering operative either of said first or second a plurality of tubular members extending longi­ lined, elongated, substantially circular fuselage mean s while simultaneously rendering the other of tudinally of the said body, said tubular members havin g a forwardly disposed main lifting surface, said means inoperative. being of constant external size but of diminishing comprising a ring member of aerofoil profile, con­ gauge from one end to the other, transverse formers centrically disposed around said fuselage toward a * The above abstracts of patents granted in the United States havin g peripheral recesses therein shaped partly to rearward portion thereof, brace means for connecting are taken, by permission of tbc Department of Commerce, from the receive the tubular members and define and main­ said ring to the fuselage, means to selectively tilt Official Gazette of the United Slates Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the tain them in positions in which they project proud said ring relative to said fuselage about vertical and Commissioner of Patents, Washington, D.C., U.S.A. of the formers and with their outer borders shaped lateral axes respectively, and fixed stabilizing means Except where otherwise staled, the specification is unaccompanied to conform to a required contour of the aircraft rearwar d of said ring member. 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 11 (5): 1 – May 1, 1939
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030491
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Abstract

May, 1939 220 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,132,682 . Tail Wheel and the Like for 2,135,464 . Aircraft Wine Structure. Aircraft . (George Herbert Dowty, Cheltenham, Alexander P. de Seversky, New York, N.Y. England . Application April 15, 1936. Serial No. Application June 29, 1935. Serial No. 29,123. 74,(>03. In Great Britain April 17, 1935. 6 1 Claim. [Class 244-123.] Claims. [Class 244-102.] I n an aeroplane wing-structure, a plurality of 1. An aircraft tail-support mount­ separatel y pre-fabricated units each comprising a ing comprising in combination a to p sheathing and a bottom sheathing connected support-carrying element, a mounting b y vertical webbing extending parallel to the element carrying said support-carrying direction of flight and each being open at its front element, shock absorbing means oper­ face and its rear face, said units meeting on separate ativ e between said elements, means vertical webs extending longitudinally of the wing mountin g the elements for castoring an d having vertical angle-members serving as rotation , means for freeing said ele­ mean s for connexion between meeting units, the ment s for castoring rotation when said unit s thus constituting the wing multicellular from body, said formers also forming interconnexions shock absorbing means is loaded, leading-edge to trailing-edge and from tip to root, between the tubular members at opposite sides of mean s for restoring specific alignment n o single one of said united units carrying even the th e body, an external cover of sheet material sur­ between said elements when said major portion of the wing-loading, and the webs roundin g the tubular members (having line contact shock absorbing means is unloaded, which extend parallel to the direction of flight with each of the tubular members) whereby the a bearing for attaching said mounting carryin g vertical and diagonal angles constituting cover is shaped by the tubular members and means means to an aircraft, means operable chordwise trussing between the longitudinal webs, for attaching said cover to said tubular members. independently of the shock absorbing whereby the majority of the number of said webs and castoring means for swinging said extendin g parallel to the flight-direction, in dis­ 2,136,919 . Copper Alloys of Improved mountin g means, support-carrying connected locations, may be destroyed and all of Characteristics . Franz It. Hensel and Earl I. means , shock absorbing means, and said longitudinally-extending webs except any two Larsen, Indianapolis, Ind., assignors to P. R. castoring means as a whole about said ma y be destroyed, without thereby destroying the Mallory & Co., Inc. , Indianapolis, Ind., a corporation bearing for retraction of the wheel. integrit y of the wing itself. of Delaware. No Drawing. Application July 13, 1938. Serial No. 218,970. 3 Claims. [Class 75-154.] 2,132,950 . Self-Locking Rivet. James L. 1. An age-hardened alloy composed of : Green, Cleveland, Ohio, assignor to The Indemse Pe r cent Corporation, a corporation of Michigan. Applica­ Beryllium .. .. .. .. . . 0·03- 3 tion May 15, 1937. Serial No. 142,786. 5 Claims. Silver .. .. .. .. . . 0·05- 4 [Class 85-4.] Tin .. .. .. .. .. . . 0·05-12 1. A self-locking rivet comprising a tubular body Balance substantially all copper. havin g a tapered inside bore, frictional projections 2,135,887 . Blade for Airscrew s and th e Like. Characterized by high hardness and electrical on the tapered inside surface of said tubular body, Charles Richard Fairey, Hayes, England. Applica­ conductivity , and further characterized by the fact a material clamping head on the end of said body tion June 3, 1936. Serial No. 83,395. In Great tha t its hardness and conductivity are not perma­ adjacent the smaller end of the tapered bore, a Britain June 7, 1935. 9 Claims. [Class 170-172.] nentl y adversely affected by elevated temperatures. smaller tubular body of a diameter suitable for 1. An airscrew blade having a tip portion and a telescoping into the first men­ hu b portion, a slot only in that part of the length 2,137,382 . Wing Flap. Raymond C. Blaylock, tioned body, a material clamping of the blade remote from the tip portion and sub­ Franci s P. Bassett, and Edward R. Child, Kenmore, head on one end of said smaller stantiall y in that half of the blade adjacent the body, frictional projections on the hu b portion, said slot extending obliquely from the oute r surface of the smaller body rea r face of the blade adjacent the leading edge of for frictionally engaging the pro­ said blade, to the front face of the blade a t a point jections on the inner surface of remote from said leading edge whereby air flows th e other body to secure said through said slot from the rear to the front face of bodies in telescoped relation for clamping material said blade. between said clamping heads, and slits in the inner end of said smaller body to provide inwardly directed resilient fingers thereon. 2,134,447 . Aircraft Construction. Herman N.Y., and Robert R. Osborn, New Orleans, La., G. Klemm, Baltimore, and Berthoud C. Boulton, assignors, by mesne assignments, to Curtiss-Wright Towson, Md., assignors to The Glenn L. Martin Corporation, a corporation of New York. Applica­ Company, Baltimore, Md. Original application tion November 6, 1936. Serial No. 109,430. 13 December 29, 1936. Serial No. 118,072. Divided Claims. [Class 244-42.] an d this application December 7, 1937. Serial No. 1. In an aircraft wing, a fitting pivoted thereto, 178,462. 2 Claims. [Class 244-53.] split trailing flaps pivoted to said fitting for opposed 1. In an aircraft having an aerofoil, an engine, a movemen t relative to said fitting, and unitary means carburetto r attached to said engine, and a cowling for selectively moving said flaps and fitting bodily relative to said wing and for moving said flaps relative to each other and to said fitting. surrounding said engine, an exhaust gas and carburetto r air intake system comprising an 2,136,265 . Construction of Wings , Surfaces, exhaus t conduit, a first means to convey air from an d Fuselages for Aircraft. George Edward adjacen t said engine in heat dissipating exchange Petty , Brough, near Hull, England, assignor to 2,137,385 . Aircraft Control System . Arthur with said conduit to an exhaust port in an area of Blackburn Aircraft Limited, Brough, near Hull, G. Butler, Buffalo, N.Y., assignor to Curtiss-Wright negative pressure on a surface of said aerofoil, a England . Application October 11, 1937, Serial Corporation, a corporation of Delaware. Applica­ second means including a portion of said first means No. 168,468. In Great Britain October 12, 1936. tion April 16, 1937. Serial No. 137,175. 5 Claims. for conveying air in heat exchange relation with 8 Claims. [Class 244-123.] [Class 244-87.] said conduit to said carburettor, and means for I. An aircraft body comprising, in combination, 1. A control system for aircraft having a stream­ rendering operative either of said first or second a plurality of tubular members extending longi­ lined, elongated, substantially circular fuselage mean s while simultaneously rendering the other of tudinally of the said body, said tubular members havin g a forwardly disposed main lifting surface, said means inoperative. being of constant external size but of diminishing comprising a ring member of aerofoil profile, con­ gauge from one end to the other, transverse formers centrically disposed around said fuselage toward a * The above abstracts of patents granted in the United States havin g peripheral recesses therein shaped partly to rearward portion thereof, brace means for connecting are taken, by permission of tbc Department of Commerce, from the receive the tubular members and define and main­ said ring to the fuselage, means to selectively tilt Official Gazette of the United Slates Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the tain them in positions in which they project proud said ring relative to said fuselage about vertical and Commissioner of Patents, Washington, D.C., U.S.A. of the formers and with their outer borders shaped lateral axes respectively, and fixed stabilizing means Except where otherwise staled, the specification is unaccompanied to conform to a required contour of the aircraft rearwar d of said ring member. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: May 1, 1939

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