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U.S. Patent Specifications

U.S. Patent Specifications 60 A 1 R C R A F T ENGINEERIN G February, 1940 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. schaft, Dessau, Germany. Application December is secured, a spoiler flap in said main aerof. 2,170,787 . Lateral Control Means for 15, 1937, Serial No. 179,874. In Germany December section, a shaft on which said spoiler flap is secure Airplanes . William K. Hose, New York, N.Y. 22,1936 . 11 Claims. [Class 123—174.] and means securing said shafts for simultaneo. Application May 21, 1938. Serial No. 209,220. In combination with a vehicle, and particularly movement whereby rotation of said spoiler 11. 27 Claims. [Class 244-42.] with aircraft of the kind including, by itself, assists in operating said slot foil. Lateral control means for an aeroplane embody­ projecting structures such as a projecting engine ing (a) an aerofoil, (b) a wing tip a t each end thereof, unit, an engine, a casing surrounding said engine, 2,172,522 . Safety Breather for Aircraft each wing tip comprising a nose-piece, a fixed body Engines . Lloyd C. Sline, San Diego, California an annular liquid radiator of the type exposed, portion and an aileron, (c) th e nosepiece at the rear Application March 24, 1938, Serial No. 197,96 owing to its motion relative to the surrounding thereof and the fixed body portion at the front 4 Claims. [Class 123—198.] air, to the passage of a cooling air current, means for arranging said radiator on the front end and, a t least for the most part, within the front contours of said projecting structure, said radiator including an intake plane and a discharge plane, an annular streamlined jacket surrounding said radiator so a s to expose said intake plane to a substantially free inflow of cooling air, said jacket being asso­ ciated with said casing in spaced relation thereto so as to define an annular air conduit issuing from said discharge plane, the walls of said jacket and said casing defining such air conduit being arranged so as to gradually narrow down the conduit, in a nozzle-like manner, toward an exhaust, whereby th e velocity of the cooling air passing through said radiato r is rendered extremely low. In a safety breather for aircraft engines of the thereof being provided with curved vanes or blades class described, a Venturi casing secured on the forming a forward passageway therebetween, the aircraft facing the direction of Jlight of said air 2,171,818 . Wall Structure for Aircraft Com­ fixed body portion at the rear thereof and the craft provided with an oppositely diverging walley partments . Herbert Wagner and Justus Muttray, aileron at the front thereof being provided with channel therein, a nozzle member secured centrally Dessau, Germany, assignors to Junkers Flugzeug- curved vanes or blades forming a rearward passage­ therein at its front portion with its outlet extended und-Motorenwerke Aktiengesellschaft, Dessau, Ger­ wa y therebetween, the said passageways having backwardly, a conductor communicating we many. Application December 15, 1937, Serial their inlet ports at the bottom of the aerofoil to the said nozzle and with the interior of the crane No. 179,875. In Germany December 28, 1936. front of their outlet ports a t the top of the aerofoil, case of the engine, and a regulating member 11 Claims. [Class 244—117.] (d) means for opening and closing said passageways, positioned in the outlet of said nozzle. (e) means for simultaneously moving the ailerons abou t an axis or axes substantially transverse to 2,172,932 . Variable Pitch Propeller the line of flight to positions above and below the Edmun d B. Cairns, Naugatuck, Conn., assignor normal planes of their respective wing tips whereby by mesne assignments, to Cairns Corporation, New th e ailerons may be moved to different angles York, N.Y., a corporation of Delaware. Appli- relatively to the aerofoil and to each other so as to cation April 2(5, 1937, Serial No. 138,900. 1 Clam present to th e airstream different angles of incidence, (Class 170—163.) ( f) the parts being so constructed and arranged In a variable-pitch propeller, the combination of tha t with the aileron of the wing tip on one side of an engine shaft, an externally threaded journal th e aerofoil in lowered position and the aileron of for the shaft on said engine, a hub fixed to the th e wing tip on the othe r side of the aerofoil in raised shaft, internally threaded sockets in said hull position the forward and rearward passageways of propeller blades, externally threaded inner end th e wing tip with its aileron lowered are open and on said blades screwed in said sockets, a ring comprise passageways of gradually decreasing cross- disposed externally of said hub, parallel racks of section from inlet to outlet with their mean cross- said ring projecting into said hub, gears fixed sectional line gradually flattening from inlet to on the propeller blades meshing with the rack outlet, the amoun t of opening being such tha t there an internally threaded gear on said journal, a is no appreciable straight-line path for air from I n aircraft a wall of annular section enclosing outwardl y opening annular channel member of inlet t o outlet, and at the wing ti p having its aileron a compartment traversed by an axis extending th e threaded gear, a flange on the ring projecture raised the forward passageway is open to permit a in parallel to the longitudinal axis of the craft, inwardly into the chamber member, antifriction free flow of pressure air upwardly therethrough and said wall consisting of transparent material means interposed between the channel member th e rear passageway is maintained closed, (g) throughou t and having the form of a self-supporting and the flange to connect the racks to the thread whereby the correlated action of the two wing tips shell, the inner diameter of which at least equals an d the aerofoil on the airstream modifies the flow the height of a seated adult person. thereof in such way that a predominant rolling force is created which persists and maintains 2,172,370 . Slot Foil Aircraft Wing. Delmer lateral control of the aeroplane well beyond the S. Fahrney, United States Navy. Application stalling angle of the aerofoil. Januar y 10, 1938, Serial No. 184,143. 1 Claim. 2,171,817 . Radiator for Aviation Engines. [Class 244—12.] [Granted under the act of March 3, Herber t Wagner, Dessau, and Ludwig Meyer, 1883, as amended April 30, 1928; 370 O. G. 757.] Dessau-Kleinkuhnau, Germany, assignors to An aircraft wing comprising a main aerofoil Junker s Klugzeug-und-Motorenwerke Aktiengesell- section and a smaller slot foil section overlying its forward surface, said slot foil section being linked to said main aerofoil section for movement upwardly and forwardly relative thereto to increase the camber and thickness of the aircraft wing when in the forward position and to restore the normal aircraft contour when in the rearward position, an d means for moving said slot foil section to the fotward position, said means being automatic, said automati c means including a yieldable means urging said slot foil to the forward position, parallel link means connecting said slot foil to said main aero­ foil section, a shaft to which said link means * The above abstract, of patents granted in the United Stales gear for simultaneous movement axially of the are taken, by permission of the Department of Commerce, from the shaft and for relative rotary movement, and Official Gazette of the United States, Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the manuall y actuated gear for rotating the thread Commissioner of Patents, Washington, D.C., U.S.A. gear t o move th e racks axially of the shaft and rot Except where otherwise stated , the specification is unaccompanied the propeller blades about their axes. b y 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 12 (2): 1 – Feb 1, 1940
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030613
Publisher site
See Article on Publisher Site

Abstract

60 A 1 R C R A F T ENGINEERIN G February, 1940 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. schaft, Dessau, Germany. Application December is secured, a spoiler flap in said main aerof. 2,170,787 . Lateral Control Means for 15, 1937, Serial No. 179,874. In Germany December section, a shaft on which said spoiler flap is secure Airplanes . William K. Hose, New York, N.Y. 22,1936 . 11 Claims. [Class 123—174.] and means securing said shafts for simultaneo. Application May 21, 1938. Serial No. 209,220. In combination with a vehicle, and particularly movement whereby rotation of said spoiler 11. 27 Claims. [Class 244-42.] with aircraft of the kind including, by itself, assists in operating said slot foil. Lateral control means for an aeroplane embody­ projecting structures such as a projecting engine ing (a) an aerofoil, (b) a wing tip a t each end thereof, unit, an engine, a casing surrounding said engine, 2,172,522 . Safety Breather for Aircraft each wing tip comprising a nose-piece, a fixed body Engines . Lloyd C. Sline, San Diego, California an annular liquid radiator of the type exposed, portion and an aileron, (c) th e nosepiece at the rear Application March 24, 1938, Serial No. 197,96 owing to its motion relative to the surrounding thereof and the fixed body portion at the front 4 Claims. [Class 123—198.] air, to the passage of a cooling air current, means for arranging said radiator on the front end and, a t least for the most part, within the front contours of said projecting structure, said radiator including an intake plane and a discharge plane, an annular streamlined jacket surrounding said radiator so a s to expose said intake plane to a substantially free inflow of cooling air, said jacket being asso­ ciated with said casing in spaced relation thereto so as to define an annular air conduit issuing from said discharge plane, the walls of said jacket and said casing defining such air conduit being arranged so as to gradually narrow down the conduit, in a nozzle-like manner, toward an exhaust, whereby th e velocity of the cooling air passing through said radiato r is rendered extremely low. In a safety breather for aircraft engines of the thereof being provided with curved vanes or blades class described, a Venturi casing secured on the forming a forward passageway therebetween, the aircraft facing the direction of Jlight of said air 2,171,818 . Wall Structure for Aircraft Com­ fixed body portion at the rear thereof and the craft provided with an oppositely diverging walley partments . Herbert Wagner and Justus Muttray, aileron at the front thereof being provided with channel therein, a nozzle member secured centrally Dessau, Germany, assignors to Junkers Flugzeug- curved vanes or blades forming a rearward passage­ therein at its front portion with its outlet extended und-Motorenwerke Aktiengesellschaft, Dessau, Ger­ wa y therebetween, the said passageways having backwardly, a conductor communicating we many. Application December 15, 1937, Serial their inlet ports at the bottom of the aerofoil to the said nozzle and with the interior of the crane No. 179,875. In Germany December 28, 1936. front of their outlet ports a t the top of the aerofoil, case of the engine, and a regulating member 11 Claims. [Class 244—117.] (d) means for opening and closing said passageways, positioned in the outlet of said nozzle. (e) means for simultaneously moving the ailerons abou t an axis or axes substantially transverse to 2,172,932 . Variable Pitch Propeller the line of flight to positions above and below the Edmun d B. Cairns, Naugatuck, Conn., assignor normal planes of their respective wing tips whereby by mesne assignments, to Cairns Corporation, New th e ailerons may be moved to different angles York, N.Y., a corporation of Delaware. Appli- relatively to the aerofoil and to each other so as to cation April 2(5, 1937, Serial No. 138,900. 1 Clam present to th e airstream different angles of incidence, (Class 170—163.) ( f) the parts being so constructed and arranged In a variable-pitch propeller, the combination of tha t with the aileron of the wing tip on one side of an engine shaft, an externally threaded journal th e aerofoil in lowered position and the aileron of for the shaft on said engine, a hub fixed to the th e wing tip on the othe r side of the aerofoil in raised shaft, internally threaded sockets in said hull position the forward and rearward passageways of propeller blades, externally threaded inner end th e wing tip with its aileron lowered are open and on said blades screwed in said sockets, a ring comprise passageways of gradually decreasing cross- disposed externally of said hub, parallel racks of section from inlet to outlet with their mean cross- said ring projecting into said hub, gears fixed sectional line gradually flattening from inlet to on the propeller blades meshing with the rack outlet, the amoun t of opening being such tha t there an internally threaded gear on said journal, a is no appreciable straight-line path for air from I n aircraft a wall of annular section enclosing outwardl y opening annular channel member of inlet t o outlet, and at the wing ti p having its aileron a compartment traversed by an axis extending th e threaded gear, a flange on the ring projecture raised the forward passageway is open to permit a in parallel to the longitudinal axis of the craft, inwardly into the chamber member, antifriction free flow of pressure air upwardly therethrough and said wall consisting of transparent material means interposed between the channel member th e rear passageway is maintained closed, (g) throughou t and having the form of a self-supporting and the flange to connect the racks to the thread whereby the correlated action of the two wing tips shell, the inner diameter of which at least equals an d the aerofoil on the airstream modifies the flow the height of a seated adult person. thereof in such way that a predominant rolling force is created which persists and maintains 2,172,370 . Slot Foil Aircraft Wing. Delmer lateral control of the aeroplane well beyond the S. Fahrney, United States Navy. Application stalling angle of the aerofoil. Januar y 10, 1938, Serial No. 184,143. 1 Claim. 2,171,817 . Radiator for Aviation Engines. [Class 244—12.] [Granted under the act of March 3, Herber t Wagner, Dessau, and Ludwig Meyer, 1883, as amended April 30, 1928; 370 O. G. 757.] Dessau-Kleinkuhnau, Germany, assignors to An aircraft wing comprising a main aerofoil Junker s Klugzeug-und-Motorenwerke Aktiengesell- section and a smaller slot foil section overlying its forward surface, said slot foil section being linked to said main aerofoil section for movement upwardly and forwardly relative thereto to increase the camber and thickness of the aircraft wing when in the forward position and to restore the normal aircraft contour when in the rearward position, an d means for moving said slot foil section to the fotward position, said means being automatic, said automati c means including a yieldable means urging said slot foil to the forward position, parallel link means connecting said slot foil to said main aero­ foil section, a shaft to which said link means * The above abstract, of patents granted in the United Stales gear for simultaneous movement axially of the are taken, by permission of the Department of Commerce, from the shaft and for relative rotary movement, and Official Gazette of the United States, Patent Office. Printed copies of the full specifications can be obtained, price 10 cents each, from the manuall y actuated gear for rotating the thread Commissioner of Patents, Washington, D.C., U.S.A. gear t o move th e racks axially of the shaft and rot Except where otherwise stated , the specification is unaccompanied the propeller blades about their axes. b y drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Feb 1, 1940

There are no references for this article.