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200 AIRCRAFT ENGINEERING July, 1937 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2.075.658 . Ice Preventing Device. John engaged by the other end of said blocks, and crank of said wing flaps, a single control rod adapted to Edwin Ramsbottom, Benny Lockspeiser, and arm s secured to the roots of the blades and said open and close said lower centre flap, a pair of Charles John Stewart, Farnborough, England. pins and swingable about the axes of said pins. operating mechanisms, means for connecting one of Application March 26, 1935. Serial No. 13,050. said mechanisms to said rods whereby only all of In Great Britain April 7, 1934. 8 claims. [Class said lower flaps are opened and closed, and means 2,075,817 . Wing Vortex Reducer. Arthur 244-134.] for connecting said other operating mechanism to W. Loerke, Dayton, Ohio. Application August 17, said rods whereby only said upper and lower wing 8. Apparatus for pro 1934. Serial No. 740,280. 13 Claims. [CI. 244- flaps are opened and closed. tectin g aircraft surfaces 130.] [Granted under the Act of March 3, 1883, from ice accumulation, as amended April 30, 1928 ; 370 O. G. 757.] which comprises means 5. A wing vortex 2,076,225 . Engine Cooling and Cowling. forming a source of reducer comprising, in Roland Chilton, Ridgewood, N.J., assignor, by supply of ice-preventing an aircraft, a wing mesne assignments, to The Reed Propeller Co., fluid, an absorbent havin g a fore-and-aft Inc., Garden City, N.Y., a corporation of New covering material per passage for the flow of York. Application June I, 1934. Serial No . 728,480. meable to said fluid on ai r through the wing 1 Claim. [Cl. 123-171.] th e surface to be protected from ice accumulation from the leading to the In combination, a radial cylinder engine, a pro and means for conveying said fluid from said trailing edges thereof peller mounted thereon and producing more nearly first mentioned means to the inner surface of said an d a lateral passage radial than axial air flow toward the centre thereof, covering. a plurality of concentric annular members arranged for the flow of air into the wing from the tip end i n coplanar relation between said engine and the thereof, said lateral passage communicating with the fore-and-aft passage. 2,075,659 . Apparatus for Preventing Ice Accumulatio n on Aircraft. John Edwin Rams- 2,075,977 . Fuel Tank for Aircraft. Carl de bottom , Benny Lockspeiser, and Charles John Ganahl , Greenlawn, N.Y., assignor to Fleetwings, Stewart , Farnborough, England. Application Inc. , Garden City, Long Island, N.Y., a corporation May 7, 1936. Serial No. 78,328. In Great Britain of Delaware. Application September 14, 1934. May 8, 1935. 6 claims. [Class 244-134.] Serial No. 743,968. 11 claims. [Cl. 220-71.] 2. Means for prevent 1. A fuel tank for aircraft, said tank being formed ing ice formation on sur of thin sheet metal and comprising confining side faces, which comprises a walls and opposite end walls and a plurality of permeable covering on diaphragm s connected with the side walls and said surfaces, tubular dividing said side walls into a plurality of inde means for conveying an pendentl y vibratable sections longitudinally of the ice-preventing fluid to tank , the side wall in each of said sections having said permeable covering a mid portion subject to vibratory energy, and and having spaced open each of said mid portions being domed and shaped so propeller, each said member comprising a ring ings from the interior of tha t it is constantly curved throughout its width, havin g a leading edge inturned so that a tangent said tube to said per longitudinally of the tank. theret o in th e axial plane is more nearly radial than meable covering, and axial, said tangent being substantially parallel to wicks between said openings and said covering for th e local air flow a t the respective leading edges, and conducting fluid from said tube to said permeable a circumscribing ring cowl having an inturned covering. leading edge and a rearward substantially cylindrical portio n embracing the engine, the leading edges of 2,075,682 . Screw Propeller. Francis Samuel said cowl and annular members being coplanar, Welman , Bexley Heath, England, assignor to and said members being axially coextensive with C. L. W. Aviation Company, Limited, Gravesend, th e inturned leading edge portion only of said ring England, a company of Great Britain. Application cowl. April 16, 1936. Serial No. 74,737. In Great Britain March 8, 1935. 10 claims. [Class 170-162.] 2,076,232 . Engine Cowling and Cooling. 1. A variable pitch screw propeller comprising Willard B. Goodman and Wesley L. I.osson, a propeller shaft, a hub movable axially and circumferentially of the propeller shaft, propeller blades having roots revolubly mounted in said hub , spaced flange supports rigidly mounted on the shaft, pivot pins extending between said sup 2,076,150 . Flap Operating Means . Arthur L. port s and disposed parallel to the shaft, pressure Klein, Los Angeles, Calif., assignor to the Northrop blocks supported at one end by said pivot pins Corporation, Inglewood, Calif., a corporation of an d extending laterally of the shaft, towage pins California. Application November 20, 1934. Serial No . 753,871. 4 Claims. [Cl. 244-42.] 1. In combination with an aeroplane having a wing and a fuselage mounted -thereon, opposed uppe r and lower wing flaps on said wing each side of said fuselage, a central lower surface wing flap, operatin g rods extending from said fuselage and adapte d to move laterally to open and close each Passaic, N.J., assignors to Wright Aeronautical Corporation, a corporation of New York. Applica tion June 11, 1935. Serial No. 25,983. 4 Claims. [Cl. 123-171.] 1. In an aeroplane, in combination, a cowling, an engine wholly enclosed thereby, an air entrance scoop in said cowling rearward of said engine, an annula r rearwardly facing air exit opening in said cowling forward of said engine, an engine accessory adapte d to be cooled by air, within said cowling and rearward of said engine, said accessory lying close to said cowling, the latter having an opening adjacent said accessory to permit of the flow of air there * The above abstracts of patents granted in the United States through , and adjustable cover means for said open are taken, by permission of the Department of Commerce, from the Official Gazette of the United States Patent Oflice. Printed copies of ing by which the air flow past said accessory may the full specifications can be obtained, price 10 cents each, from the b e controlled independently of the air flow past Commissioner of Patents, Washington, D.C., U.S.A. said engine, said engine and accessory both re Except where otherwise stated, the specification is unaccompanied by drawings if none is reproduced. ceiving air from said air entrance scoop.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jul 1, 1937
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