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Month in the Patent Office

Month in the Patent Office 204 AIRCRAFT ENGINEERING July, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 402,602 . Vaporizers. Fairey Aviation Co., tub e 3 is fixed at its upper end to the aeroplane Ltd. , Cranford Lane, Hayes, Middlesex, and an d is further supported by a collar G. The rollers Forsyth , A. G., Venlaw, Burdon Lane, Cheam, engage the three sides of ribs 9, 10 carried by a Surrey. Dec. 22, 1932, No. 36326. [Class 7 (iii).] sleeve 11 fixed on the axle 2. The rollers 18, 19 Combustible mixture is heated in a connection c. an d 20, 21 are respectively mounted on axles 16, 17 and the rollers 12, 13 are loosely mounted in arrange d between a carburetter or a supercharger boxes 14, 15. The upper end of the shock-absorber an d the induction manifold, by a stream-lined pipe 6 is universally jointed to a cap 7 of the tube 3. g through which hot lubricant passes, a shaft h, which extends therethrough , throwing the lubricant Th e rollers 18, 19, 20, 21 may be arranged in a o n to the inner walls of the pipe. The lubricant plan e slightly inclined to a plane normal to the drain s into the pipe through a ball bearing on axi s of the member 2. th e shaft. or tapering. The flap may be submerged in a recess 20. In a modification a curved flap 25, Fig . 6, is pivoted forwardly of the trailing edge a sufficient distance to permit it to be completely housed within the aerofoil and is made in sections 403,897 . Airscrews. Heenan & Froude, Ltd.' t o miss the chord construction of the aerofoil. I n a further modification a fixed depending flap an d Walker, G. H., Worcester Engineering Works. is provided having channels in which slide tele­ Worcester . Sept. 23, 1932, No . 18918/33. Divided scoping sections. In a still further modification on 403,199. [Class 114.] th e aerofoil is provided with a series of pivoted I n a variable pitch airscrew of the kind where dependin g blades 40, Fig. 12, pivoted at 41 and th e stems of the blades are extended through the adapte d to be moved in unison. These blades boss to overlap, the extensions of the stems are ma y be of various cross sections. An arrangement supporte d at their extremities b y journalled guides is shown in which the flaps are moved by lateral attache d to or formed within the interior of each movemen t of the control stick, which is mounted stem , one of which surrounds the other a t one end, an d th e other surrounds the first a t other end and a t o move universally and has an extension moving thrus t bearing is placed centrally between the in a guide and connected to the elevator control inne r ends of the blades, one member of bearing wire . The flaps on the wings may be moved simultaneously or differentially. bein g carried by one stem and the other by the second stem. The blades 1, la have hollow 404,135 . Screw propellers. Fairey Aviation extensions 1b, 1c, supported by guides 2, 2a formed 404,270 . Aircraft. Zap Development Cor­ Co., Ltd., Cranford Lane, Hayes, Middlesex, and withi n the extension. A thrust bearing 3 is poration , 230, Park Avenue, New York, U.S.A. Forsyth , A. G., Venlaw, Burdon Lane, Cheam, mounte d between th e two stems t o tak e centrifugal April 4, 1932, No . 9683. Convention date, April 3 , Surrey . Dec. 22, 1932, No. 36328. [Class 114.] forces. The extension 1c is provide d with a collar 9 1931. [Class 4.] I n devices for attaching propeller blades f to located between the faces of the bearing 10 and I n aircraft means are provided for increasing bosses or hubs a, th e latter is formed with an in­ havin g adjustable supports in the casing. The th e drag on the rear portion of the lower side of tegra l back plate b, betwee n which an d the movable extensions are provided with worm sectors 12, 12a plat e c th e propeller f is gripped by bolts d which engaged by worms 13 and are geared to the pitch pas s through a loose clamping-plate e which bears adjustmen t mechanism. Specification 403,199 is agains t the edge of the propeller. Various modi­ referred to. fications are described. In one the clamping-plate ha s an exterior cylindrical surface which engages wit h a similar surface formed on lugs on the back plat e b. The clamping plate may also be arranged t o have a pivotal movement about th e central bolt such movement being limited by bolts connecting front and back plates. The clamping-plates may also pivot a t one end about one bolt the other end bolt-hole being slightly slotted to permit radial a wing thus increasing the lift coefficient for the movemen t or the clamping-plates may be stepped aircraft. The means comprises a fixed flap 14 a t their free ends to clear each other. attache d by braces 17 t o th e rear edge of an aero­ foil or forwardly of the rear edge and may extend for the whole or par t of the length of the aerofoil. Th e flap is shown also applied to the ailerons 16. Th e flap is provided with strengthening ribs 18 an d an end plate 15. The flap may be of uniform 403,911 . Aircraft landing - gear. Soc. heigh t or tapering. The flap is shown curved Français e do Materiel d'Aviation, 58, Rue Fenelon, concave towards the direction of flight and also Montrouge, Seine, France. Aug. 16, 1933, No. curved convex toward the direction of flight and 22864. Convention date, July 13. [Class 4.] extending rearwardly beyond the trailing edge. Landing-gear for aeroplanes includes an oblique half-axle 2 carrying the wheel 1 and guided in a tub e 3 by rollers in a member 4 and a piston 5 rigid with the movable member 6a of a shock- 404,269 . Aircraft. Zap Development Cor­ absorbe r 6 universally jointed to the axle 2. The poration , 230, Park Avenue, New York, U.S.A. April 4, 1932, No . 9682. Convention date, April 3, 1931. [Class 4.] * These abstracts of complete specifications of Patents recently I n aircraf t variable mean s ar e provide d t o increase published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified th e drag on the rear portion of the lower side of a into croups. Sets of group abridgments can be obtained from wing , thus increasing the lift coefficient for the the Patent Office, 25 Southampton Buildings, London, W.C.2, aircraft. The means may comprise a flap 12, either sheet by sheet as issued, on payment of a subscription of 5s. per group volume, or in bound volumes at 2s. each. Copies of Fig . 2, hinged t o th e trailing edge 11 of a n aerofoil 10 the full specifications can bo obtained from the same address, an d operated by a horn 13 and a wire 14. The price 1s. each. flap 12 may extend wholly or partially from the Except where otherwise stated, the specification is unaccom­ fuselage to the wing tip, ma y be of uniform height panied by drawings if none is reproduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 6 (7): 1 – Jul 1, 1934

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029825
Publisher site
See Article on Publisher Site

Abstract

204 AIRCRAFT ENGINEERING July, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 402,602 . Vaporizers. Fairey Aviation Co., tub e 3 is fixed at its upper end to the aeroplane Ltd. , Cranford Lane, Hayes, Middlesex, and an d is further supported by a collar G. The rollers Forsyth , A. G., Venlaw, Burdon Lane, Cheam, engage the three sides of ribs 9, 10 carried by a Surrey. Dec. 22, 1932, No. 36326. [Class 7 (iii).] sleeve 11 fixed on the axle 2. The rollers 18, 19 Combustible mixture is heated in a connection c. an d 20, 21 are respectively mounted on axles 16, 17 and the rollers 12, 13 are loosely mounted in arrange d between a carburetter or a supercharger boxes 14, 15. The upper end of the shock-absorber an d the induction manifold, by a stream-lined pipe 6 is universally jointed to a cap 7 of the tube 3. g through which hot lubricant passes, a shaft h, which extends therethrough , throwing the lubricant Th e rollers 18, 19, 20, 21 may be arranged in a o n to the inner walls of the pipe. The lubricant plan e slightly inclined to a plane normal to the drain s into the pipe through a ball bearing on axi s of the member 2. th e shaft. or tapering. The flap may be submerged in a recess 20. In a modification a curved flap 25, Fig . 6, is pivoted forwardly of the trailing edge a sufficient distance to permit it to be completely housed within the aerofoil and is made in sections 403,897 . Airscrews. Heenan & Froude, Ltd.' t o miss the chord construction of the aerofoil. I n a further modification a fixed depending flap an d Walker, G. H., Worcester Engineering Works. is provided having channels in which slide tele­ Worcester . Sept. 23, 1932, No . 18918/33. Divided scoping sections. In a still further modification on 403,199. [Class 114.] th e aerofoil is provided with a series of pivoted I n a variable pitch airscrew of the kind where dependin g blades 40, Fig. 12, pivoted at 41 and th e stems of the blades are extended through the adapte d to be moved in unison. These blades boss to overlap, the extensions of the stems are ma y be of various cross sections. An arrangement supporte d at their extremities b y journalled guides is shown in which the flaps are moved by lateral attache d to or formed within the interior of each movemen t of the control stick, which is mounted stem , one of which surrounds the other a t one end, an d th e other surrounds the first a t other end and a t o move universally and has an extension moving thrus t bearing is placed centrally between the in a guide and connected to the elevator control inne r ends of the blades, one member of bearing wire . The flaps on the wings may be moved simultaneously or differentially. bein g carried by one stem and the other by the second stem. The blades 1, la have hollow 404,135 . Screw propellers. Fairey Aviation extensions 1b, 1c, supported by guides 2, 2a formed 404,270 . Aircraft. Zap Development Cor­ Co., Ltd., Cranford Lane, Hayes, Middlesex, and withi n the extension. A thrust bearing 3 is poration , 230, Park Avenue, New York, U.S.A. Forsyth , A. G., Venlaw, Burdon Lane, Cheam, mounte d between th e two stems t o tak e centrifugal April 4, 1932, No . 9683. Convention date, April 3 , Surrey . Dec. 22, 1932, No. 36328. [Class 114.] forces. The extension 1c is provide d with a collar 9 1931. [Class 4.] I n devices for attaching propeller blades f to located between the faces of the bearing 10 and I n aircraft means are provided for increasing bosses or hubs a, th e latter is formed with an in­ havin g adjustable supports in the casing. The th e drag on the rear portion of the lower side of tegra l back plate b, betwee n which an d the movable extensions are provided with worm sectors 12, 12a plat e c th e propeller f is gripped by bolts d which engaged by worms 13 and are geared to the pitch pas s through a loose clamping-plate e which bears adjustmen t mechanism. Specification 403,199 is agains t the edge of the propeller. Various modi­ referred to. fications are described. In one the clamping-plate ha s an exterior cylindrical surface which engages wit h a similar surface formed on lugs on the back plat e b. The clamping plate may also be arranged t o have a pivotal movement about th e central bolt such movement being limited by bolts connecting front and back plates. The clamping-plates may also pivot a t one end about one bolt the other end bolt-hole being slightly slotted to permit radial a wing thus increasing the lift coefficient for the movemen t or the clamping-plates may be stepped aircraft. The means comprises a fixed flap 14 a t their free ends to clear each other. attache d by braces 17 t o th e rear edge of an aero­ foil or forwardly of the rear edge and may extend for the whole or par t of the length of the aerofoil. Th e flap is shown also applied to the ailerons 16. Th e flap is provided with strengthening ribs 18 an d an end plate 15. The flap may be of uniform 403,911 . Aircraft landing - gear. Soc. heigh t or tapering. The flap is shown curved Français e do Materiel d'Aviation, 58, Rue Fenelon, concave towards the direction of flight and also Montrouge, Seine, France. Aug. 16, 1933, No. curved convex toward the direction of flight and 22864. Convention date, July 13. [Class 4.] extending rearwardly beyond the trailing edge. Landing-gear for aeroplanes includes an oblique half-axle 2 carrying the wheel 1 and guided in a tub e 3 by rollers in a member 4 and a piston 5 rigid with the movable member 6a of a shock- 404,269 . Aircraft. Zap Development Cor­ absorbe r 6 universally jointed to the axle 2. The poration , 230, Park Avenue, New York, U.S.A. April 4, 1932, No . 9682. Convention date, April 3, 1931. [Class 4.] * These abstracts of complete specifications of Patents recently I n aircraf t variable mean s ar e provide d t o increase published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified th e drag on the rear portion of the lower side of a into croups. Sets of group abridgments can be obtained from wing , thus increasing the lift coefficient for the the Patent Office, 25 Southampton Buildings, London, W.C.2, aircraft. The means may comprise a flap 12, either sheet by sheet as issued, on payment of a subscription of 5s. per group volume, or in bound volumes at 2s. each. Copies of Fig . 2, hinged t o th e trailing edge 11 of a n aerofoil 10 the full specifications can bo obtained from the same address, an d operated by a horn 13 and a wire 14. The price 1s. each. flap 12 may extend wholly or partially from the Except where otherwise stated, the specification is unaccom­ fuselage to the wing tip, ma y be of uniform height panied by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jul 1, 1934

There are no references for this article.