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Month in the Patent Office

Month in the Patent Office leading edge overlapping slotted flaps mounted on spanwise tubular members actuated by a number of substantially horizontal bellcranks and control rods. In a fifth embodiment (FIGS. 12, 13, not shown) the These abstracts of British Patent Specifications are taken, by permission, from the officially prepared extension flap consists of two component flaps, the hinge points of which are set close together at the abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, trailing edge of the wing. When unfolded rearwardly 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies they can be located at close together or spaced-apart of the full specifications arc obtainable at the same address, price 2s. 8d. each. positions for take-off or landing respectively. When applied to control surfaces such as ailerons (FIGS. 14, 15, not shown), the screening flap is spring-loaded surface is increased by an extension flap hinged 627,121. Folding wings for aeroplanes. Soc. Nation- and the extension flap is actuated by a cable control adjacent to the trailing edge of the surface and rotat- ale dc Constructions Acronautiqucs du Nord. April mechanism coupled to the control mechanism for the able from a retracted position in which it is folded 29, 1947, No. 11,493. Convention date Nov. 14, 1946. wing extension flaps to effect simultaneous actuation. forwardly under the surface to an operative position (Class 4.) When separately mounted on each side of the fuselage, in which it is unfolded rearwardly, the extension flap Jn an aircraft with folding wings, the movable por­ each flap is mounted on a torque tube coupled to a tions 5 arc connected to the fixed portions 4 by hinges being sheltered in its movement by a downwardly and central torque tube to which arc connected the control rearwardly inclined screening flap pivoted forward of whose axes X—X1 arc inclined and located in the rods or cables. the extension flap and normally folded rearwardly longitudinal plane of the main spars 6, 8 of the wings. under the surface. The extension flap 2, FIG. 1, hinged In the form shown, the hinge axes converge down­ 628,684. Controlling Aircraft. Office National at 3 to the wing 1 is in contact with an overlapping wardly, the wing portion in front of each hinge being d'Etudcs ct de Rechcrchcs Acronautiqucs screening flap 4 hinged to the wing at 5. Simultaneous of stepped shape DEFG in plan, while the upper sur­ (O.N.E.R.A.). August 15, 1947. Convention date movement of both flaps to the positions shown in face of the fixed wing portion 4 to the rear of the October 31, 1945. FIGS. 3 and 5 is obtained by linking them by rods hinge is formed with a recess 9 to allow the passage of 10,13, to a common pilot's control lever 6. In a second the lower edge 10 of the rear portion of the movable embodiment (FIG. 7, not shown) the extension flap wing portion 5 during folding and unfolding. The only is connected to the pilot's control lever, the undcr-surfacc of the fixed portion is formed with a Lateral and yawing control of an aircraft is effected by end plates 2 which arc normally vertical and serve as stabilizing fins, and arc mounted on horizontal, rcarwardly-convcrging axes XY to function as ailerons and rudders. For lateral control both surfaces arc rotated about their axes, while for control in yaw one is fixed and the other rotated. The trailing edge portion of each of the surfaces 2 may be provicd with a pivoted flap. 628,861. Helicopters. Firestone Tire & Rubber Co. March 26, 1947. Convention date April 17, 1946. In order to balance the reaction torque of the lifting rotor 12 of a helicopter, two auxiliary rotors 17a, 176 arc mounted on a common transverse axis and are located below the main rotor cxtcriorily of the fuse­ lage 7 so as to be subjected to the unobstructed down- wash of the main rotor. The blades of the auxiliary rotors arc of variable pitch, one form of pitch control, Specification 627,121 FIG. 3, comprising axial shafts 35a, 356 connected to pitch control arms 33 and displaccable by a pivoted screening flap being held in contact with the extension horizontal extension 11 for supporting the wing por­ member 37 connected by a link 40 to a screw-member flap by a spring. In a third embodiment (FIG. 8, not tion 5, while the latter carries a flap 12 covering the 45 engaging a sleeve operated by chain-and-sprocket shown) the extension flap is mounted on a plurality recess 9 when the wing is extended. The wings may 43, 44. In a modification, FIG. 4 (not shown), a chain of arms pivoted to the trailing edge of the wing to en­ be operated by hydraulic or electric jack; 14, and re­ and sprocket actuates shafts mounted parallel to the able the flap to act as a slotted flap when in the ex­ motely controlled locking devices 17, 18 may be em­ axis of the auxiliary rotors and conncted by links to tended position. In a fourth embodiment (FIGS. 9, ployed for securing the wings in their extended axially-displaceablc hub sleeves by which the rotor 10, 11, not shown) the extension flap is increased in position. pitch is varied. In order to prevent interference the area by forming it from two pivoted overlapping distance between the auxiliary rotors is approximately sections in the form of an overlapping screen. To 627,634. Propelling Aircraft. Wcstinghousc Electric equal to their diameter. counteract the pitching effect caused by the additional International Co. March 14, 1947. Convention date increase in area at the trailing edge of the wing two November 9, 1945. A gas turbine jet-propulsion engine having an annu­ lar nozzle 21 for the discharge of the heated gases from the turbine has a tail cone 22 which forms the inner wall of the annular nozzle and encloses a rocket which discharges rearwardly through an opening 41 in the apex of the tail cone. The rocket comprises a combustion chamber 45 and a nozzle 48, and may be of the liquid or dry fuel type. If the rocket is of the liquid fuel type, the fuel and liquid oxygen or other chemicals may be supplied by conduits 51 and 52 which pass through one of the struts 42a supporting the tail cone. The turbine may drive a propeller. 627,941. Controlling Aircraft. Piatti, S. V. August 29. 1947. Convention date December 27, 1939. The area of an aircraft supporting or control 28 Aircraft Engineering 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 25 (1): 1 – Jan 1, 1953

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032254
Publisher site
See Article on Publisher Site

Abstract

leading edge overlapping slotted flaps mounted on spanwise tubular members actuated by a number of substantially horizontal bellcranks and control rods. In a fifth embodiment (FIGS. 12, 13, not shown) the These abstracts of British Patent Specifications are taken, by permission, from the officially prepared extension flap consists of two component flaps, the hinge points of which are set close together at the abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, trailing edge of the wing. When unfolded rearwardly 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies they can be located at close together or spaced-apart of the full specifications arc obtainable at the same address, price 2s. 8d. each. positions for take-off or landing respectively. When applied to control surfaces such as ailerons (FIGS. 14, 15, not shown), the screening flap is spring-loaded surface is increased by an extension flap hinged 627,121. Folding wings for aeroplanes. Soc. Nation- and the extension flap is actuated by a cable control adjacent to the trailing edge of the surface and rotat- ale dc Constructions Acronautiqucs du Nord. April mechanism coupled to the control mechanism for the able from a retracted position in which it is folded 29, 1947, No. 11,493. Convention date Nov. 14, 1946. wing extension flaps to effect simultaneous actuation. forwardly under the surface to an operative position (Class 4.) When separately mounted on each side of the fuselage, in which it is unfolded rearwardly, the extension flap Jn an aircraft with folding wings, the movable por­ each flap is mounted on a torque tube coupled to a tions 5 arc connected to the fixed portions 4 by hinges being sheltered in its movement by a downwardly and central torque tube to which arc connected the control rearwardly inclined screening flap pivoted forward of whose axes X—X1 arc inclined and located in the rods or cables. the extension flap and normally folded rearwardly longitudinal plane of the main spars 6, 8 of the wings. under the surface. The extension flap 2, FIG. 1, hinged In the form shown, the hinge axes converge down­ 628,684. Controlling Aircraft. Office National at 3 to the wing 1 is in contact with an overlapping wardly, the wing portion in front of each hinge being d'Etudcs ct de Rechcrchcs Acronautiqucs screening flap 4 hinged to the wing at 5. Simultaneous of stepped shape DEFG in plan, while the upper sur­ (O.N.E.R.A.). August 15, 1947. Convention date movement of both flaps to the positions shown in face of the fixed wing portion 4 to the rear of the October 31, 1945. FIGS. 3 and 5 is obtained by linking them by rods hinge is formed with a recess 9 to allow the passage of 10,13, to a common pilot's control lever 6. In a second the lower edge 10 of the rear portion of the movable embodiment (FIG. 7, not shown) the extension flap wing portion 5 during folding and unfolding. The only is connected to the pilot's control lever, the undcr-surfacc of the fixed portion is formed with a Lateral and yawing control of an aircraft is effected by end plates 2 which arc normally vertical and serve as stabilizing fins, and arc mounted on horizontal, rcarwardly-convcrging axes XY to function as ailerons and rudders. For lateral control both surfaces arc rotated about their axes, while for control in yaw one is fixed and the other rotated. The trailing edge portion of each of the surfaces 2 may be provicd with a pivoted flap. 628,861. Helicopters. Firestone Tire & Rubber Co. March 26, 1947. Convention date April 17, 1946. In order to balance the reaction torque of the lifting rotor 12 of a helicopter, two auxiliary rotors 17a, 176 arc mounted on a common transverse axis and are located below the main rotor cxtcriorily of the fuse­ lage 7 so as to be subjected to the unobstructed down- wash of the main rotor. The blades of the auxiliary rotors arc of variable pitch, one form of pitch control, Specification 627,121 FIG. 3, comprising axial shafts 35a, 356 connected to pitch control arms 33 and displaccable by a pivoted screening flap being held in contact with the extension horizontal extension 11 for supporting the wing por­ member 37 connected by a link 40 to a screw-member flap by a spring. In a third embodiment (FIG. 8, not tion 5, while the latter carries a flap 12 covering the 45 engaging a sleeve operated by chain-and-sprocket shown) the extension flap is mounted on a plurality recess 9 when the wing is extended. The wings may 43, 44. In a modification, FIG. 4 (not shown), a chain of arms pivoted to the trailing edge of the wing to en­ be operated by hydraulic or electric jack; 14, and re­ and sprocket actuates shafts mounted parallel to the able the flap to act as a slotted flap when in the ex­ motely controlled locking devices 17, 18 may be em­ axis of the auxiliary rotors and conncted by links to tended position. In a fourth embodiment (FIGS. 9, ployed for securing the wings in their extended axially-displaceablc hub sleeves by which the rotor 10, 11, not shown) the extension flap is increased in position. pitch is varied. In order to prevent interference the area by forming it from two pivoted overlapping distance between the auxiliary rotors is approximately sections in the form of an overlapping screen. To 627,634. Propelling Aircraft. Wcstinghousc Electric equal to their diameter. counteract the pitching effect caused by the additional International Co. March 14, 1947. Convention date increase in area at the trailing edge of the wing two November 9, 1945. A gas turbine jet-propulsion engine having an annu­ lar nozzle 21 for the discharge of the heated gases from the turbine has a tail cone 22 which forms the inner wall of the annular nozzle and encloses a rocket which discharges rearwardly through an opening 41 in the apex of the tail cone. The rocket comprises a combustion chamber 45 and a nozzle 48, and may be of the liquid or dry fuel type. If the rocket is of the liquid fuel type, the fuel and liquid oxygen or other chemicals may be supplied by conduits 51 and 52 which pass through one of the struts 42a supporting the tail cone. The turbine may drive a propeller. 627,941. Controlling Aircraft. Piatti, S. V. August 29. 1947. Convention date December 27, 1939. The area of an aircraft supporting or control 28 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jan 1, 1953

There are no references for this article.