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U.S. Patent Specifications

U.S. Patent Specifications 140 AIRCRAFT ENGINEERING March, 1939 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,126,785 . Readily Detachable Fairing. oute r ends of said cylinders, and said compressor Isaac M. Laddon, San Diego, Calif., assignor to being located between said turbine and the axis Consolidated Aircraft Corporation, a corporation of of said row of cylinders. Delaware. Application September 10, 1936. Serial No. 100,065. 11 Claims. [Class 244-130.] 3. In aircraft construction, a strut, a fairing, bracket means attached to the said strut, and ex­ pansible screw means adapte d to attac h said fairing t o said bracket means by separation of a portion of said bracket means from an opposed portion of said fairing. which ice is collected when moisture is present in said fluid at freezing temperatures whereby said entranc e becomes blocked by the ice formation and th e passage of the fluid is cut off, and means for actuatin g the second-named means in the opposite direction when the passage of fluid is cut off by the ice formation on said third-named means. 2,128,983 . Aircraft Power Plant Control. Werne r J. Blanchard, Kenmore, N.Y., assignor, by 2,128,169 . Safety Indicator for Airplanes. mesne assignments, to Curtiss-Wright Corporation, Francis R. Shanley, Takoma Park, Md., assignor a corporation of New York. Application March 26, t o th e Government of the United States of America, 1935. Serial No. 13,031. 5 claims. [Class 170-135.6.1 a s represented by the Secretary of the Navy. 1. In aircraft, including a plurality of sub­ Application June 29, 1932. Serial No. 620,033. stantiall y similar power plants each comprising a 12 Claims. [Class 177-311.] supercharged internal combustion engine and a 1. A device for indicating during the flight of power driven controllable pitch propeller including electrical control means therefor; a unitary device including an expansible diaphragm con­ 2,127,264 . Propeller Blade . Glen T. Lampton, nected to the intake manifold of each engine, a Williamsport, Pa., assignor to Aviation Manu­ switch ar m operated by each diaphragm, a common facturing Corporation, Chicago, Ill., a corporation contac t carrier for all said arms having contacts of Delaware. Application November 7, 1935. Serial connected to respective propeller control means for No. 48,643. 13 Claims. [Class 170-159.] effecting pitch change of the propellers in response 1. A propeller blade comprising a body and a t o ar m contact s due t o changes in manifold pressure, cylindrical shank of laminated material such a an d single adjusting means for said carrier whereby wood with longitudinal metallic plates in the shank th e effect of manifold pressure change is effected and bonded thereto and intersecting the joints simultaneousl y for all units. between the laminae. a n airplane the approach and the existence of any flight condition characterised by certain predeter­ mined combinations of the variables of accelera­ tion acting on the airplane in a direction substan­ tiall y perpendicular to the lifting surfaces of the airplane and the dynamic pressure due t o the velo­ cit y of the airplane through the air, comprising 2,127,437 . Degreasing Metal Strip. Samuel a n index, means for moving said index along a Barnes Spencer an d John Charles Dutton , Runcorn, fixed path and with respect to a zero position in England, assignors t o Imperial Chemical Industries, response to the variations in the actual value of Limited, a corporation of Great Britain. Applica­ one of said variables, a second index movable tion January 12, 1937. Serial No. 120,319. In Great along substantially the same path as the first 2,129,824 . Aircraft Structure. Alexander Britain, January 16, 1936. 13 Claims. [Class 87-6.] index, the position of the second index wit h respect P . de Seversky, Asharoken Beach, Northport, N.Y., 1. A method of degreasing metal strip which t o the zero position of the first index representing assignor to Seversky Aircraft Corporation, a cor­ comprises orienting said strip so as to dispose one t o the scale of motion of the first index the value poration of Delaware. Application November 1, of the longitudinal edges thereof substantially of the first variable which in conjunction with the 1937. Serial No. 172,156. 11 claims. [Class vertically above th e othe r longitudinal edge thereof, existing value of the second variable will produce 244-102.] and passing the thus oriented strip through a zone one of said predetermined conbinations, and means 1. In an aircraft, the combination with a of solvent vapour. for moving said second index in response to the structur e having a recess in its under side, of a variations in th e actua l value of th e second variable, suppor t and a landing wheel carried thereby, th e relative position of said indices indicating the said support being attached to the said structure relationship between the actual value of the first an d movable upwardly and rearwardly into the variable and tha t value of th e first variable required recess, a rigid fairing member carried at the t o produce one of said predetermined combinations forward side of said support and a collapsible of acceleration and dynamic pressure. fairing member connected to said rigid fairing 2,128,789 . Aircraft Machinery. René membe r to constitute a streamline-form rear­ Anxionnaz, Paris, France. Application February 8, 2,127,823 . Ice Warnin g Device . Paul Leifheit, wardl y of said rigid fairing member, said col­ 1936. Serial No. 63,000. In France, February 16, Oswego, Ill., assignor to Pioneer Instrument lapsible fairing member being retractable into the 1935. 4 Claims. [Class 244-59.] Company, Inc., Brooklyn, N.Y., a corporation of stru t receiving recess when the strut is retracted. 1. In an aircraft, the combination of a fuselage, New York. Application September 14, 1935. Serial a n air-cooled engine carried by said fuselage No. 54,466. 7 Claims. [Class 177-311.] havin g at least one row of cylinders projecting 1. An ice responsive device for aircraft com­ radially from said fuselage so as to be cooled by prising means providing a passage for a fluid, means th e relative wind produced along said fuselage in said passage for actuation in one direction by said b y the movement of said aircraft, and a turbo- fluid, means at the entrance of said passage upon compressor carried by said fuselage behind said row of cylinders, said turbo-compressor including * The above abstracts of patents granted in the United States a turbine having its axis at right angles to the are taken, by permission of the Department of Commerce, from the engine axis and a compressor coupled directly Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the with said turbine coaxially therewith, said turbine Commissioner of Patents, Washington, D.C., U.S.A. being located substantially in a cylindrical surface Except where otherwise stated, the specification is unaccompanied coaxial with said engine and passing through the 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 (3): 1 – Mar 1, 1939
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030463
Publisher site
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Abstract

140 AIRCRAFT ENGINEERING March, 1939 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,126,785 . Readily Detachable Fairing. oute r ends of said cylinders, and said compressor Isaac M. Laddon, San Diego, Calif., assignor to being located between said turbine and the axis Consolidated Aircraft Corporation, a corporation of of said row of cylinders. Delaware. Application September 10, 1936. Serial No. 100,065. 11 Claims. [Class 244-130.] 3. In aircraft construction, a strut, a fairing, bracket means attached to the said strut, and ex­ pansible screw means adapte d to attac h said fairing t o said bracket means by separation of a portion of said bracket means from an opposed portion of said fairing. which ice is collected when moisture is present in said fluid at freezing temperatures whereby said entranc e becomes blocked by the ice formation and th e passage of the fluid is cut off, and means for actuatin g the second-named means in the opposite direction when the passage of fluid is cut off by the ice formation on said third-named means. 2,128,983 . Aircraft Power Plant Control. Werne r J. Blanchard, Kenmore, N.Y., assignor, by 2,128,169 . Safety Indicator for Airplanes. mesne assignments, to Curtiss-Wright Corporation, Francis R. Shanley, Takoma Park, Md., assignor a corporation of New York. Application March 26, t o th e Government of the United States of America, 1935. Serial No. 13,031. 5 claims. [Class 170-135.6.1 a s represented by the Secretary of the Navy. 1. In aircraft, including a plurality of sub­ Application June 29, 1932. Serial No. 620,033. stantiall y similar power plants each comprising a 12 Claims. [Class 177-311.] supercharged internal combustion engine and a 1. A device for indicating during the flight of power driven controllable pitch propeller including electrical control means therefor; a unitary device including an expansible diaphragm con­ 2,127,264 . Propeller Blade . Glen T. Lampton, nected to the intake manifold of each engine, a Williamsport, Pa., assignor to Aviation Manu­ switch ar m operated by each diaphragm, a common facturing Corporation, Chicago, Ill., a corporation contac t carrier for all said arms having contacts of Delaware. Application November 7, 1935. Serial connected to respective propeller control means for No. 48,643. 13 Claims. [Class 170-159.] effecting pitch change of the propellers in response 1. A propeller blade comprising a body and a t o ar m contact s due t o changes in manifold pressure, cylindrical shank of laminated material such a an d single adjusting means for said carrier whereby wood with longitudinal metallic plates in the shank th e effect of manifold pressure change is effected and bonded thereto and intersecting the joints simultaneousl y for all units. between the laminae. a n airplane the approach and the existence of any flight condition characterised by certain predeter­ mined combinations of the variables of accelera­ tion acting on the airplane in a direction substan­ tiall y perpendicular to the lifting surfaces of the airplane and the dynamic pressure due t o the velo­ cit y of the airplane through the air, comprising 2,127,437 . Degreasing Metal Strip. Samuel a n index, means for moving said index along a Barnes Spencer an d John Charles Dutton , Runcorn, fixed path and with respect to a zero position in England, assignors t o Imperial Chemical Industries, response to the variations in the actual value of Limited, a corporation of Great Britain. Applica­ one of said variables, a second index movable tion January 12, 1937. Serial No. 120,319. In Great along substantially the same path as the first 2,129,824 . Aircraft Structure. Alexander Britain, January 16, 1936. 13 Claims. [Class 87-6.] index, the position of the second index wit h respect P . de Seversky, Asharoken Beach, Northport, N.Y., 1. A method of degreasing metal strip which t o the zero position of the first index representing assignor to Seversky Aircraft Corporation, a cor­ comprises orienting said strip so as to dispose one t o the scale of motion of the first index the value poration of Delaware. Application November 1, of the longitudinal edges thereof substantially of the first variable which in conjunction with the 1937. Serial No. 172,156. 11 claims. [Class vertically above th e othe r longitudinal edge thereof, existing value of the second variable will produce 244-102.] and passing the thus oriented strip through a zone one of said predetermined conbinations, and means 1. In an aircraft, the combination with a of solvent vapour. for moving said second index in response to the structur e having a recess in its under side, of a variations in th e actua l value of th e second variable, suppor t and a landing wheel carried thereby, th e relative position of said indices indicating the said support being attached to the said structure relationship between the actual value of the first an d movable upwardly and rearwardly into the variable and tha t value of th e first variable required recess, a rigid fairing member carried at the t o produce one of said predetermined combinations forward side of said support and a collapsible of acceleration and dynamic pressure. fairing member connected to said rigid fairing 2,128,789 . Aircraft Machinery. René membe r to constitute a streamline-form rear­ Anxionnaz, Paris, France. Application February 8, 2,127,823 . Ice Warnin g Device . Paul Leifheit, wardl y of said rigid fairing member, said col­ 1936. Serial No. 63,000. In France, February 16, Oswego, Ill., assignor to Pioneer Instrument lapsible fairing member being retractable into the 1935. 4 Claims. [Class 244-59.] Company, Inc., Brooklyn, N.Y., a corporation of stru t receiving recess when the strut is retracted. 1. In an aircraft, the combination of a fuselage, New York. Application September 14, 1935. Serial a n air-cooled engine carried by said fuselage No. 54,466. 7 Claims. [Class 177-311.] havin g at least one row of cylinders projecting 1. An ice responsive device for aircraft com­ radially from said fuselage so as to be cooled by prising means providing a passage for a fluid, means th e relative wind produced along said fuselage in said passage for actuation in one direction by said b y the movement of said aircraft, and a turbo- fluid, means at the entrance of said passage upon compressor carried by said fuselage behind said row of cylinders, said turbo-compressor including * The above abstracts of patents granted in the United States a turbine having its axis at right angles to the are taken, by permission of the Department of Commerce, from the engine axis and a compressor coupled directly Official Gazette of the United States Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the with said turbine coaxially therewith, said turbine Commissioner of Patents, Washington, D.C., U.S.A. being located substantially in a cylindrical surface Except where otherwise stated, the specification is unaccompanied coaxial with said engine and passing through the by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Mar 1, 1939

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