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Month in the Patent Office

Month in the Patent Office 186 AIRCRAFT ENGINEERING July, 1935 A Selection of the More Important Aircraft and Engin e Specifications Published Recently alway s forward of the trailing edge is moved by mechanism substantially wholly within the aero­ foil to cause bodily movement of the flap to the front and rear respectively as it is raised and lowered. In one form, Figs. 1, 2 and 3, a flap 25 normall y rested against the underside of a wing is moved rearwardly by connections to toothed rack s 33 which are movable, parallel to the under­ side of the wing by pinions 27, and is tilted by links 37 pivoted to the aerofoil and the flap in such position as to produce substantially vertical down­ ward movement of the trailing edge of the flap. Th e pinions 27 ar e fast with vertical shafts carrying uppe r pinions 31 meshed with racks 30 secured to a transversel y extending bar 29. At their inner ends th e bars 29 on the two sides of the machine carry or arc formed with threaded sockets 28 respectively receiving oppositely threaded ends of a rod 24 rotatabl e by the pilot, for moving the bars 29 inwardl y or outwardly, by chain and sprocket mechanism . Ailerons 15 are provided but in a modification, Fig. 15, these are omitted and means provided for moving the flaps differentially. In this case th e rack bars 146, 147 ar c engaged by oppositely threade d parts 144, 145 of a bar 114 having a telescopic joint 116, 117. The bar 114 is rotatable for camber changing by chain and sprocket gearing. Hub s 126, 127 journalled in bearings 128, 129 arc formed with internal cam slots 119 in which engage 416,879 . Controlling aircraft . Fairey, C. R., pins 118 on the relatively axially movable parts of ba r 114. The hubs 126, 127 are adapted to be Cranford Lane, Hayes, Middlesex. Oct. 26, 1933, oppositely rotated by sideways movement of control No . 29736. [Class 4.] column 135. Rotation of the hubs 127, 128 causes I n means for controlling aircraft, slot-forming cation in which the flap is moved by an arm on a axial movement of one or other rack bar 146, 147 slats 12 situated one a t each end of the wings 11 quadran t 76, the forward edge of the flap having to vary the lift on to two sides of the craft. A ar c controlled by means interconnected with the rollers 71 moving in guides 73, 72. The flaps may modified flap mechanism comprises a depending rudder, or the actuating means therefor, so that be made of two layers of corrugated metal with the membe r 90, Fig. 13, in which is slidable a flexible operation of the rudder 22 may bring about the corrugations of the upper layer a t right-angles to shutter-like flap 96 which may be retracted from opening or closing of either slot as required or thos e on the lower surface which extend in the operativ e position by rotatio n of a reel 95. Modified preven t either slot from opening. The slats may direction of flight. mechanism s for actuating the flap involve the use be spring controlled or free and the motion trans­ of screw and nut gear operated by bevel pinions on mitte d thereto may be damped by a dashpot or transvers e shafts extending into the fuselage, and like device. In one form, one or other of the slot- in one case the flap extends as far as the forward forming slats 12 is actuate d to form a slot on move­ spar of the aerofoil. Fig. 10 shows another modifi­ men t of th e rudder bar 20 through a rod 15, a bell- crank lever 16 and a cable 17 which includes a tensioning device 18 which permits the slats to be operated under normal circumstances by the usual mean s (not shown). The slats 12 arc connected by links 13 and radius rods 14, pivoted a t one end to th e wing, t o th e rods 15. In a modification, one or othe r of the slot-forming slats 12, Fig. 3, is held closed according to the direction in which the AERONAUTICA L PLYWOOD rudde r bar 20 is operated on depression of a pedal THE Aeronautical & Panel Plywood Co., 25 which actuates a friction clutch t o cause a drum 23 to move with the rudder bar. A cable 17, Ltd., sole manufacturers of " MALLITE " including a tensioning device 18 wound around the and "APPCO" Brands all British Plywood, dru m 23 has its ends connected to bellerank levers , 218/22 6 Kingsland Road, London, E.2. 16, the other arms of which are connected to the Telephone : Bishopsgate 5641 (4 lines) slats by rods 15. The slots in this case are formed automaticall y due to th e aerodynamic forces acting on the wing. TRANSLATION S 416,715 . Controlling aircraft . Zap Develop­ men t Corporation, 230 Park Avenue, New York, OR Translations at moderate rates by U.S.A. Jan. 19, 1933, No. 1855. Convention specialist in Technical Aeronautical work date , Jan. 19, 1932. [Class 4.] apply " Translator," Riverside House, Mortlake, An aerofoil has a flap so mounted beneath its London, S.W.14. (Prospect 2743). pressure surface tha t as it is extended downwardly {Recommended by the Editor, AIRCRAFT ENGINEERING) it s trailing edge lies substantially in perpendicular, dropped from the trailing-edge of the aerofoil in all positions of adjustment. Alternatively, a flap capable of adjustment about its leading edge so as T O MANUFACTURERS , PATENTEES , t o depend from the pressure side of an aerofoil AIRCRAF T DESIGNERS , ETC . WELL-know n and old-established firm of En- * These abstracts of complete specifications of patents recently gineers about to erect large modern Works, is published arc specially complied, by permission of H.M. Stationery Office, from abridgments which arc issued by the Office classified prepared to consider proposals from Patentees, into groups. Sets of group abridgements can be obtained from Designers, Manufacturers and others for light the Patent Office, 25 Southampton Buildings, London, W.C.2, either sheet by sheet as issued, on payment of a subscription of and heavy products with view to manufacture in 5s. per group volume, or in bound volumes at 2s, each. Copies quantities under license or other suitable arrange­ of the full specifications can be obtained from the same address, price 1s. each. ments. Full particulars to T. 42, Furness's Except where otherwise stated, the specification is unaccom- Advertising Offices, Bold Street, Liverpool. 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 7 (7): 1 – Jul 1, 1935
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029953
Publisher site
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Abstract

186 AIRCRAFT ENGINEERING July, 1935 A Selection of the More Important Aircraft and Engin e Specifications Published Recently alway s forward of the trailing edge is moved by mechanism substantially wholly within the aero­ foil to cause bodily movement of the flap to the front and rear respectively as it is raised and lowered. In one form, Figs. 1, 2 and 3, a flap 25 normall y rested against the underside of a wing is moved rearwardly by connections to toothed rack s 33 which are movable, parallel to the under­ side of the wing by pinions 27, and is tilted by links 37 pivoted to the aerofoil and the flap in such position as to produce substantially vertical down­ ward movement of the trailing edge of the flap. Th e pinions 27 ar e fast with vertical shafts carrying uppe r pinions 31 meshed with racks 30 secured to a transversel y extending bar 29. At their inner ends th e bars 29 on the two sides of the machine carry or arc formed with threaded sockets 28 respectively receiving oppositely threaded ends of a rod 24 rotatabl e by the pilot, for moving the bars 29 inwardl y or outwardly, by chain and sprocket mechanism . Ailerons 15 are provided but in a modification, Fig. 15, these are omitted and means provided for moving the flaps differentially. In this case th e rack bars 146, 147 ar c engaged by oppositely threade d parts 144, 145 of a bar 114 having a telescopic joint 116, 117. The bar 114 is rotatable for camber changing by chain and sprocket gearing. Hub s 126, 127 journalled in bearings 128, 129 arc formed with internal cam slots 119 in which engage 416,879 . Controlling aircraft . Fairey, C. R., pins 118 on the relatively axially movable parts of ba r 114. The hubs 126, 127 are adapted to be Cranford Lane, Hayes, Middlesex. Oct. 26, 1933, oppositely rotated by sideways movement of control No . 29736. [Class 4.] column 135. Rotation of the hubs 127, 128 causes I n means for controlling aircraft, slot-forming cation in which the flap is moved by an arm on a axial movement of one or other rack bar 146, 147 slats 12 situated one a t each end of the wings 11 quadran t 76, the forward edge of the flap having to vary the lift on to two sides of the craft. A ar c controlled by means interconnected with the rollers 71 moving in guides 73, 72. The flaps may modified flap mechanism comprises a depending rudder, or the actuating means therefor, so that be made of two layers of corrugated metal with the membe r 90, Fig. 13, in which is slidable a flexible operation of the rudder 22 may bring about the corrugations of the upper layer a t right-angles to shutter-like flap 96 which may be retracted from opening or closing of either slot as required or thos e on the lower surface which extend in the operativ e position by rotatio n of a reel 95. Modified preven t either slot from opening. The slats may direction of flight. mechanism s for actuating the flap involve the use be spring controlled or free and the motion trans­ of screw and nut gear operated by bevel pinions on mitte d thereto may be damped by a dashpot or transvers e shafts extending into the fuselage, and like device. In one form, one or other of the slot- in one case the flap extends as far as the forward forming slats 12 is actuate d to form a slot on move­ spar of the aerofoil. Fig. 10 shows another modifi­ men t of th e rudder bar 20 through a rod 15, a bell- crank lever 16 and a cable 17 which includes a tensioning device 18 which permits the slats to be operated under normal circumstances by the usual mean s (not shown). The slats 12 arc connected by links 13 and radius rods 14, pivoted a t one end to th e wing, t o th e rods 15. In a modification, one or othe r of the slot-forming slats 12, Fig. 3, is held closed according to the direction in which the AERONAUTICA L PLYWOOD rudde r bar 20 is operated on depression of a pedal THE Aeronautical & Panel Plywood Co., 25 which actuates a friction clutch t o cause a drum 23 to move with the rudder bar. A cable 17, Ltd., sole manufacturers of " MALLITE " including a tensioning device 18 wound around the and "APPCO" Brands all British Plywood, dru m 23 has its ends connected to bellerank levers , 218/22 6 Kingsland Road, London, E.2. 16, the other arms of which are connected to the Telephone : Bishopsgate 5641 (4 lines) slats by rods 15. The slots in this case are formed automaticall y due to th e aerodynamic forces acting on the wing. TRANSLATION S 416,715 . Controlling aircraft . Zap Develop­ men t Corporation, 230 Park Avenue, New York, OR Translations at moderate rates by U.S.A. Jan. 19, 1933, No. 1855. Convention specialist in Technical Aeronautical work date , Jan. 19, 1932. [Class 4.] apply " Translator," Riverside House, Mortlake, An aerofoil has a flap so mounted beneath its London, S.W.14. (Prospect 2743). pressure surface tha t as it is extended downwardly {Recommended by the Editor, AIRCRAFT ENGINEERING) it s trailing edge lies substantially in perpendicular, dropped from the trailing-edge of the aerofoil in all positions of adjustment. Alternatively, a flap capable of adjustment about its leading edge so as T O MANUFACTURERS , PATENTEES , t o depend from the pressure side of an aerofoil AIRCRAF T DESIGNERS , ETC . WELL-know n and old-established firm of En- * These abstracts of complete specifications of patents recently gineers about to erect large modern Works, is published arc specially complied, by permission of H.M. Stationery Office, from abridgments which arc issued by the Office classified prepared to consider proposals from Patentees, into groups. Sets of group abridgements can be obtained from Designers, Manufacturers and others for light the Patent Office, 25 Southampton Buildings, London, W.C.2, either sheet by sheet as issued, on payment of a subscription of and heavy products with view to manufacture in 5s. per group volume, or in bound volumes at 2s, each. Copies quantities under license or other suitable arrange­ of the full specifications can be obtained from the same address, price 1s. each. ments. Full particulars to T. 42, Furness's Except where otherwise stated, the specification is unaccom- Advertising Offices, Bold Street, Liverpool. panied by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jul 1, 1935

There are no references for this article.