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U.S. Patent Specifications

U.S. Patent Specifications January, 1938 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,097,807 . Mechanism for Actuating the 2,098,566 . De-icing Means for Aircraft. Contro l Surfaces of Aircraft. Robert Talbot Roland Chilton, Ridgewood, N.J., assignor, by Youngman , Aldershot, England, assignor to The mesne assignments, to The Reed Propellor Co., Faire y Aviation Company, Limited, Hayes, Inc. , Garden City, N.Y., a corporation of New England . Application December 1, 1936, Serial York. Application October 27, 1934. Serial No. 750,253. 2 claims. [Class 244-134.] No . 113,657. In Great Britain, December 13, 1935. 1. The combination with an aircraft having an 9 claims. [Class 244-42.] engine exhaust pipe and a surface to be de-iced, 1. Mechanism for actuating the control surfaces 2,097,990 . Adjusting Means for Control of an alcohol reservoir, an evaporator attached to of aircraft, including a flap mounted so that it is Surfaces . Igor I. Sikorsky, Trumbull, Conn., said pipe, porous covering over said surface, and lowered bodily from its normal retracted position assignor to United Aircraft Corporation, East means to conduct alcohol from said evaporator to t o a position below the wing level and turned to a Hartford, Conn., a company of Delaware. Applica­ desired extent about a transverse axis at or near saturat e said covering. tion September 5, 1935. Serial No. 39,245. 6 th e centre of pressure, the bodily lowering and claims. [Class 244-87.] turnin g movements of the flap being effected 1. In an aeroplane, a fuselage, a stabilizer adjustably mounted on said fuselage, an extensible stru t comprising a screw jack having an axially movable member and a rotatable member disposed between said fuselage and said stabilizer for adjust­ ing said stabilizer, a set of braces extending from opposite sides of said stabilizer into said fuselage, an d means operatively connected with the rotatable 2,099,368 . Device for the automatic control portion of said screw jack for adjusting the length of camber flaps and the like for aeroplanes. of said braces to accommodate the braces to the Ren e Lucien Levy, Montrouge, France, assignor various adjusted positions of the stabilizer. to Société d'Inventions Aeronautiques et Mec- aniques S.I.A.M., Fribourg (Suisse). Application Februar y 13, 1936. Serial No. 63,805. In France 2,097,991 . Mechanic's Platform for Aero­ April 5, 1935. 1 Claim. [Cl. 244—42.] planes . Igor I. Sikorsky, Trumbull, Conn., independently and either successively or simul­ A device for the control of an aeroplane camber assignor to United Aircraft Corporation, East taneously, wherein a lever by which the flap is flap, or the like, comprising : a hydraulic cylinder, Hartford, Conn., a corporation of Delaware. moved to its lowered position is pivoted at its front a piston movable in said cylinder, a hydro-pneu­ Application March 17, 1936. Serial No. 69,355. end on the aircraft wing and is part of a link and matic accumulator, a pipe line connecting this 6 claims. [Class 244-129.] lever mechanism comprising said lever, a second cylinder with said tank on one side of said piston, 1. In an aircraft having a wing and an engine lever parallel therewith and also pivoted at its a liquid tank connected to said cylinder on the supported adjacent to said wing, means providing a front end on the aircraft wing, and a link connecting other side of the th e free ends of said levers, said second lever and piston, a valve said link together constituting a toggle or knuckle interposed in the jointed strut, the elements of which, when the flap pipe line con­ is moved to its lowered position, are straightened nectin g the ou t to form one side of a triangulated structure, a cylinder to the second side of which is formed by the first lever, tank , a source an d the third side of which is constituted by the of hydraulic wing structure between the pivotal axes of the first pressure allow­ and second levers. ing to move said piston in the 2,097,926 . Deicing Apparatus for Aero­ direction corres­ planes . Leo B. Kimball, New Haven, Conn., ponding to the assignor to Fuel Development Corporation, a platform for the support of a person working on increase of the corporation of Delaware. Application June 9, said engine, said means comprising, a movable pressure in said section of the leading edge of said wing hinged along accumulator , its lower side to the fixed portion of the wing, means and means for for supporting said movable section in a position connecting said approximatel y 90 deg. from its normal position in piston to the which it constitutes a continuation of the leading cambe r flap for edge surface of said wing, and means forming a actuatin g the trea d on the surface of said movable section which latte r in one is uppermost when in said 90 deg. position. direction and in th e other. 2,097,996 . Auxiliary Surface Control. 2,098,571 . Link Type Dynamic Damper. Arthu r G. Butler, Eggertsville, N.Y., assignor, by Chester C. De Pew, Bloomfield, N.J., assignor to mesne assignments, to Curtiss-Wright Corporation, Wrigh t Aeronautical Corporation, a corporation of a corporation of New York. Application New York. Application September 21, 1935. November 1, 1935. Serial No. 47,775. 3 claims. Serial No. 41,531. 3 claims. [Class 74-604.] [Class 244-75.] 1. The combination with crankshaft and counter­ weight members, each having an axially extended 2. In an aircraft control surface having a flap plurality of opposed laterally extended grooves, of pivotally attached to its rear portion, operating a laterally means for said flap comprising a fixed screw shaft 1937. Serial No. 147,198. 5 claims. [Class 244- extende d transversel y mounted within said control surface, 134.] plurality of a disc member threadedly engaging the said shaft, 2. In deicing apparatus for aeroplanes, the im­ links in each means associated with the periphery of the disc provement s that comprise, internal means for dis groove, and membe r adapted to impart rotation and transverse tributin g a deicing liquid over the surface to be a lateral translatio n of the disc member along said shaft, a deiced, a chamber having a substantially constant pluralit y bifurcated member attached to said flap member level of deicing liquid therein, a pipe leading from o f hinge havin g its bifurcations transversely spaced and said chamber to said distributing means, a device pins span­ embracing the said disc member, the said rotation for producing an hydrostatic pressure on said nin g said impartin g means passing through the opening liquid in said chamber and in said pipe, and means groove s , between the said bifurcations and serving to main­ to counterbalance said pressure when said dis­ an d engag­ tai n the said means in operative relation with said tributin g means is not obstructed by ice. in g said disc. links for the * The above abstracts or patents granted in the United States oscillatin g are taken, by permission of the Department of Commerce, from the connectio n Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the of said links Commissioner of Patents, Washington, D.C., U.S.A. t o each Except where otherwise stated, the specification is unaccompanied 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 10 (1): 1 – Jan 1, 1938
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Emerald Publishing
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Copyright © Emerald Group Publishing Limited
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0002-2667
DOI
10.1108/eb030269
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Abstract

January, 1938 AIRCRAF T ENGINEERING Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,097,807 . Mechanism for Actuating the 2,098,566 . De-icing Means for Aircraft. Contro l Surfaces of Aircraft. Robert Talbot Roland Chilton, Ridgewood, N.J., assignor, by Youngman , Aldershot, England, assignor to The mesne assignments, to The Reed Propellor Co., Faire y Aviation Company, Limited, Hayes, Inc. , Garden City, N.Y., a corporation of New England . Application December 1, 1936, Serial York. Application October 27, 1934. Serial No. 750,253. 2 claims. [Class 244-134.] No . 113,657. In Great Britain, December 13, 1935. 1. The combination with an aircraft having an 9 claims. [Class 244-42.] engine exhaust pipe and a surface to be de-iced, 1. Mechanism for actuating the control surfaces 2,097,990 . Adjusting Means for Control of an alcohol reservoir, an evaporator attached to of aircraft, including a flap mounted so that it is Surfaces . Igor I. Sikorsky, Trumbull, Conn., said pipe, porous covering over said surface, and lowered bodily from its normal retracted position assignor to United Aircraft Corporation, East means to conduct alcohol from said evaporator to t o a position below the wing level and turned to a Hartford, Conn., a company of Delaware. Applica­ desired extent about a transverse axis at or near saturat e said covering. tion September 5, 1935. Serial No. 39,245. 6 th e centre of pressure, the bodily lowering and claims. [Class 244-87.] turnin g movements of the flap being effected 1. In an aeroplane, a fuselage, a stabilizer adjustably mounted on said fuselage, an extensible stru t comprising a screw jack having an axially movable member and a rotatable member disposed between said fuselage and said stabilizer for adjust­ ing said stabilizer, a set of braces extending from opposite sides of said stabilizer into said fuselage, an d means operatively connected with the rotatable 2,099,368 . Device for the automatic control portion of said screw jack for adjusting the length of camber flaps and the like for aeroplanes. of said braces to accommodate the braces to the Ren e Lucien Levy, Montrouge, France, assignor various adjusted positions of the stabilizer. to Société d'Inventions Aeronautiques et Mec- aniques S.I.A.M., Fribourg (Suisse). Application Februar y 13, 1936. Serial No. 63,805. In France 2,097,991 . Mechanic's Platform for Aero­ April 5, 1935. 1 Claim. [Cl. 244—42.] planes . Igor I. Sikorsky, Trumbull, Conn., independently and either successively or simul­ A device for the control of an aeroplane camber assignor to United Aircraft Corporation, East taneously, wherein a lever by which the flap is flap, or the like, comprising : a hydraulic cylinder, Hartford, Conn., a corporation of Delaware. moved to its lowered position is pivoted at its front a piston movable in said cylinder, a hydro-pneu­ Application March 17, 1936. Serial No. 69,355. end on the aircraft wing and is part of a link and matic accumulator, a pipe line connecting this 6 claims. [Class 244-129.] lever mechanism comprising said lever, a second cylinder with said tank on one side of said piston, 1. In an aircraft having a wing and an engine lever parallel therewith and also pivoted at its a liquid tank connected to said cylinder on the supported adjacent to said wing, means providing a front end on the aircraft wing, and a link connecting other side of the th e free ends of said levers, said second lever and piston, a valve said link together constituting a toggle or knuckle interposed in the jointed strut, the elements of which, when the flap pipe line con­ is moved to its lowered position, are straightened nectin g the ou t to form one side of a triangulated structure, a cylinder to the second side of which is formed by the first lever, tank , a source an d the third side of which is constituted by the of hydraulic wing structure between the pivotal axes of the first pressure allow­ and second levers. ing to move said piston in the 2,097,926 . Deicing Apparatus for Aero­ direction corres­ planes . Leo B. Kimball, New Haven, Conn., ponding to the assignor to Fuel Development Corporation, a platform for the support of a person working on increase of the corporation of Delaware. Application June 9, said engine, said means comprising, a movable pressure in said section of the leading edge of said wing hinged along accumulator , its lower side to the fixed portion of the wing, means and means for for supporting said movable section in a position connecting said approximatel y 90 deg. from its normal position in piston to the which it constitutes a continuation of the leading cambe r flap for edge surface of said wing, and means forming a actuatin g the trea d on the surface of said movable section which latte r in one is uppermost when in said 90 deg. position. direction and in th e other. 2,097,996 . Auxiliary Surface Control. 2,098,571 . Link Type Dynamic Damper. Arthu r G. Butler, Eggertsville, N.Y., assignor, by Chester C. De Pew, Bloomfield, N.J., assignor to mesne assignments, to Curtiss-Wright Corporation, Wrigh t Aeronautical Corporation, a corporation of a corporation of New York. Application New York. Application September 21, 1935. November 1, 1935. Serial No. 47,775. 3 claims. Serial No. 41,531. 3 claims. [Class 74-604.] [Class 244-75.] 1. The combination with crankshaft and counter­ weight members, each having an axially extended 2. In an aircraft control surface having a flap plurality of opposed laterally extended grooves, of pivotally attached to its rear portion, operating a laterally means for said flap comprising a fixed screw shaft 1937. Serial No. 147,198. 5 claims. [Class 244- extende d transversel y mounted within said control surface, 134.] plurality of a disc member threadedly engaging the said shaft, 2. In deicing apparatus for aeroplanes, the im­ links in each means associated with the periphery of the disc provement s that comprise, internal means for dis groove, and membe r adapted to impart rotation and transverse tributin g a deicing liquid over the surface to be a lateral translatio n of the disc member along said shaft, a deiced, a chamber having a substantially constant pluralit y bifurcated member attached to said flap member level of deicing liquid therein, a pipe leading from o f hinge havin g its bifurcations transversely spaced and said chamber to said distributing means, a device pins span­ embracing the said disc member, the said rotation for producing an hydrostatic pressure on said nin g said impartin g means passing through the opening liquid in said chamber and in said pipe, and means groove s , between the said bifurcations and serving to main­ to counterbalance said pressure when said dis­ an d engag­ tai n the said means in operative relation with said tributin g means is not obstructed by ice. in g said disc. links for the * The above abstracts or patents granted in the United States oscillatin g are taken, by permission of the Department of Commerce, from the connectio n Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the of said links Commissioner of Patents, Washington, D.C., U.S.A. t o each Except where otherwise stated, the specification is unaccompanied member. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jan 1, 1938

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