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Month in the Patent Office

Month in the Patent Office These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the full specifications are obtainable at the same address, price 1s. each. 611,954. Aircraft arrester hooks. Fairey Aviation Co. Ltd. Chaplin, H. E., and Bealc, R. D. May 14, 1946, No. 14537. (Class 4.) In a folding wing aircraft with a tricycle under­ carriage in which the folding of the wings causes the centre of gravity of the aircraft to move behind the rear axle of the undercarriage, the aircraft tail is supported when the wings are folded by a strut 15, which is also an arrester hook for engaging wires on a landing deck for stopping the aircraft, retractable manually into a housing 10a near the tail of the air­ craft. The arrester hook 15 is pivoted about an axis 16 to the aircraft and is extended and supported by a pneumatic jack 20 whose piston 19 is pivoted at 18 to a lever 17 integral with the hook and whose cylinder is pivoted at 21 to a bracket 21a on the air­ craft. The exhaust valve 36 of the jack 20 is auto­ matically closed by a connexion 39, 38 to a lever 37 (see FIG. 4), fast on the shaft 16 when the arrester 612,369. Control surfaces for aircraft. Martin Co., hook 15 is (manually) retracted, a lost motion device G. L. May 22, 1946. No. 15480. Convention date, in the connexion preventing the automatic opening Nov. 4, 1942. (Class 4.) 612,403. Helicopters. Landgraf, F. July 20, 1945. of the valve 36 by extension of the strut. A hinged control surface, more particularly an No. 13867/48. Convention date, Dec. 8, 1942. aileron 2, is mounted so that the axis 8 of its hinges Divided out of 612,317. (Class 4.) (Also in Group 6, 7 lies approximately in the plane of the upper XXIV.) wing surface, and sealing members 9, 11 arc provided In a helicopter comprising a pair of inter-meshing between the hinges to prevent the flow of air through rotors set one on each side of the longitudinal axis, the passage between the control surface and wing. each rotor is rotated by a disk 66 connected by a As shown, the scaling member 9 is provided with a scries of parallel oblique tie rods 344, 345 to a second bead 10 making line contact with the member 11. parallel disk 342 driven by the engine. The ends of The nose portion of the aileron is so shaped that it the rods are oppositely threaded and engage members does not project below the lower surface of the wing 340, 346 carried upon vertical pins in the disks 66, when the aileron is raised, but it carries a slat 12 342. Each of the driving disks 342 is secured to a which is projected into the lower airstream at a negative gear-wheel 360 engaged by an engine-driven worm angle of incidence when the aileron is so operated. 362. FIG. 8. 612,189. Rotary-wing aircraft. Cierva Autogiro Co. Ltd., and Pullin, C. G. May 17, 1946. No. 14943. (Class 4.) A rotary-wing system comprises listing and driving components mounted on a common hub-member, the former comprising at least two aerofoil-shaped blades 17, and the latter two or more substantially non-lifting arms 18a, 186," carrying aero-thermodyna- mic ducts 19a, 196 at their tips. In the aircraft shown in FIGS. 1 and 3 the arms 18a, 186 arc connected to stub arms 21 on the hub 13 by drag pivots 20, and the lifting blades 17 are attached by drag pivots 16 to drag links 15 connected to the hub by flapping pivots 14. Fuel for the propulsive ducts is supplied by a pump 27 to a pipe 29 communicating with transfer pipes 39a, 396 inside the hub and flexible hoses 40a, 406 connected to ducts 41a, 416 inside the arms 18a, 186. Cyclical and collective pitch control of the blades 17 is effected by a vertical member 44 passing through the hub 13, and mounted on a ball joint on a member 42 engaging the upper end of the hub. Cyclical pitch variation is obtained by rocking the member 44 by links 54, 60 and 55, 61, while collective pitch control results from vertical movement of the members 42, 44 initiated by links 62, 65. The movement of the member 42 relative to the hub is permitted by a pin-and-slot connexion 51, 52. FIG. 6 shows a modification in which the rotor hub 31 is mounted on a ball joint 71 at the upper end of-a central shaft 30, and the stub arms 21 carrying the driving arms 18a, 186 are attached to a ring 32 mounted on the hub by trunnions 66 whose axis is perpendicular to the driving arms. In this case the fuel pipe 29 is located on the axis of the hub and is connected to flexible hoses 69a, 69b in communication with ducts 70 in the driving arms 18a, 186. The inclination of the rotor is adjusted by a non-rotating ring 33 which engages with the lower portion of the hub 31. Collective pitch control mechanism for the lifting blades 17 may be provided. October 1951 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 23 (10): 1 – Oct 1, 1951
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032094
Publisher site
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Abstract

These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the full specifications are obtainable at the same address, price 1s. each. 611,954. Aircraft arrester hooks. Fairey Aviation Co. Ltd. Chaplin, H. E., and Bealc, R. D. May 14, 1946, No. 14537. (Class 4.) In a folding wing aircraft with a tricycle under­ carriage in which the folding of the wings causes the centre of gravity of the aircraft to move behind the rear axle of the undercarriage, the aircraft tail is supported when the wings are folded by a strut 15, which is also an arrester hook for engaging wires on a landing deck for stopping the aircraft, retractable manually into a housing 10a near the tail of the air­ craft. The arrester hook 15 is pivoted about an axis 16 to the aircraft and is extended and supported by a pneumatic jack 20 whose piston 19 is pivoted at 18 to a lever 17 integral with the hook and whose cylinder is pivoted at 21 to a bracket 21a on the air­ craft. The exhaust valve 36 of the jack 20 is auto­ matically closed by a connexion 39, 38 to a lever 37 (see FIG. 4), fast on the shaft 16 when the arrester 612,369. Control surfaces for aircraft. Martin Co., hook 15 is (manually) retracted, a lost motion device G. L. May 22, 1946. No. 15480. Convention date, in the connexion preventing the automatic opening Nov. 4, 1942. (Class 4.) 612,403. Helicopters. Landgraf, F. July 20, 1945. of the valve 36 by extension of the strut. A hinged control surface, more particularly an No. 13867/48. Convention date, Dec. 8, 1942. aileron 2, is mounted so that the axis 8 of its hinges Divided out of 612,317. (Class 4.) (Also in Group 6, 7 lies approximately in the plane of the upper XXIV.) wing surface, and sealing members 9, 11 arc provided In a helicopter comprising a pair of inter-meshing between the hinges to prevent the flow of air through rotors set one on each side of the longitudinal axis, the passage between the control surface and wing. each rotor is rotated by a disk 66 connected by a As shown, the scaling member 9 is provided with a scries of parallel oblique tie rods 344, 345 to a second bead 10 making line contact with the member 11. parallel disk 342 driven by the engine. The ends of The nose portion of the aileron is so shaped that it the rods are oppositely threaded and engage members does not project below the lower surface of the wing 340, 346 carried upon vertical pins in the disks 66, when the aileron is raised, but it carries a slat 12 342. Each of the driving disks 342 is secured to a which is projected into the lower airstream at a negative gear-wheel 360 engaged by an engine-driven worm angle of incidence when the aileron is so operated. 362. FIG. 8. 612,189. Rotary-wing aircraft. Cierva Autogiro Co. Ltd., and Pullin, C. G. May 17, 1946. No. 14943. (Class 4.) A rotary-wing system comprises listing and driving components mounted on a common hub-member, the former comprising at least two aerofoil-shaped blades 17, and the latter two or more substantially non-lifting arms 18a, 186," carrying aero-thermodyna- mic ducts 19a, 196 at their tips. In the aircraft shown in FIGS. 1 and 3 the arms 18a, 186 arc connected to stub arms 21 on the hub 13 by drag pivots 20, and the lifting blades 17 are attached by drag pivots 16 to drag links 15 connected to the hub by flapping pivots 14. Fuel for the propulsive ducts is supplied by a pump 27 to a pipe 29 communicating with transfer pipes 39a, 396 inside the hub and flexible hoses 40a, 406 connected to ducts 41a, 416 inside the arms 18a, 186. Cyclical and collective pitch control of the blades 17 is effected by a vertical member 44 passing through the hub 13, and mounted on a ball joint on a member 42 engaging the upper end of the hub. Cyclical pitch variation is obtained by rocking the member 44 by links 54, 60 and 55, 61, while collective pitch control results from vertical movement of the members 42, 44 initiated by links 62, 65. The movement of the member 42 relative to the hub is permitted by a pin-and-slot connexion 51, 52. FIG. 6 shows a modification in which the rotor hub 31 is mounted on a ball joint 71 at the upper end of-a central shaft 30, and the stub arms 21 carrying the driving arms 18a, 186 are attached to a ring 32 mounted on the hub by trunnions 66 whose axis is perpendicular to the driving arms. In this case the fuel pipe 29 is located on the axis of the hub and is connected to flexible hoses 69a, 69b in communication with ducts 70 in the driving arms 18a, 186. The inclination of the rotor is adjusted by a non-rotating ring 33 which engages with the lower portion of the hub 31. Collective pitch control mechanism for the lifting blades 17 may be provided. October 1951

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Oct 1, 1951

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