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Month in the Patent Office

Month in the Patent Office 631,918. Aircraft and ship structures. English Elec­ tric Co. Ltd., Hollock, R. N., and Bradford, F. October 29, 1947. The skin of an aircraft or other lightweight struc­ ture is secured to a stringer attached to a rib by a These abstracts of British Patent Specifications are taken, by permission, from the officially prepared member which enables the stringer to be adjusted abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, about two independent axes, the attachment member 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies being capable of longitudinal axial adjustment. The of the full specifications are obtainable at the same address, price 2s. 8d. each. invention is shown applied to an aircraft structure, 630,183. Aircraft undercarriages. Dowty Equip­ suspension means on the aircraft, which attachment ment, Ltd., and Bound, R. H. December 15, 1947. comprises bolts 38 engageable in lugs 38a for co­ An aircraft undercarriage comprises a four-wheeled operation with a streamlined strut 39 projecting down­ bogie, of which two of the wheels, 16, 17, are inde­ wardly from the wing 40, or a suspension lug 48 pendently rotatable and are mounted on a common (FIG. 1, not shown). In the arrangement shown, lugs 41 transverse axle 15 at the lower end of the under­ carry cross-pins 42 for engagement by bifurcated carriage leg 13, the other two wheels 21, 24 being hooks 43 of release units 44, 45, so that the tank and strut 39 can be jettisoned. Fluid connexions are pro­ mounted in tandem in a fore-and-aft plane extending vided with frangible elbows 46, 47. 631,785. Aircraft wings. Vickers-Armstrongs, Ltd., and Richards, E. J. November 25, 1947. In order to delay the formation of compressibility shock waves to the same extent over the whole span of a wing, the angle of sweep back of the quarter in which the skin 1 is riveted to a stringer 3, the end of chord line is made greater over the inboard region which is secured by a pin or bolt to an eyebolt 8 en­ gaging by means of a screw thread with a bracket 7 secured to a rib 4. The angular setting of the stringer in relation to the rib is adjustable by rotation of the eyebolt 8 in the bracket 7 and by rotation of the stringer about the pin or bolt by which it is attached to the eye-bolt. The attachment may also be used for securing the skins of boats or vehicle bodies. 632,313. Screw propellers. De Havilland Aircraft Co. Ltd., and Hadwin, R. N. January 31, 1947. A vibration damper or absorber for attachment to a propeller blade, comprises a casing containing a mass consisting of a prc-determincd quantity of a mobile between and parallel to the wheels 16, 17, and being non-viscous or low-viscous liquid such as mercury, castorable and/or stcerablc. The wheels 21,24 are car­ some other mobile non-viscous liquid such as acety­ ried by brackets 18, 19 mounted on the axle 15 and lene tetrabromide or Clerici, or a combination of mer­ provided with supplementary shock absorbers 26, 27 cury and one of the latter liquids. For use at high connected to a cross-head 28 on the leg 13. Anti- temperatures a fusible metal such as Wood's metal shimmy devices may be provided for the castoring may be employed in a stainless steel casing. As shown, wheels, together with means for aligning them when the casing 3 is tapered externally to fit a recess 8 in the the aircraft is airborne. blade root, and is sealed by a closure plate 4, fitted with a closable inlet passage axially arranged in a 630,238. Drop-tanks. Faircy Aviation Co. Ltd., stem portion 5 for the introduction of the mercury 1. than at the wing tip. The leading edge may be formed Montague, E., and Collins, N. October 31, 1947. Balancing washers 7 may be mounted on the stem 5 with two or more straight portions Al, A2, FIG. 1 A drop-tank for aircraft comprising an inner re­ and retained by a nut 6. In a similar construction the having different angles of sweep back or by a smooth, ceptacle 25, outer rigid intcrdigitatcd sections 26-28 plate 4 is externally screw-threaded for engagement continuous curve C, FIG. 3. The trailing edge B may and end caps 29, 30, is preferably provided with an with casing, the internal shape of which is part- inner wall 35 between which and the top surface 28 be straight as shown in FIG. 1, or similar to the leading spherical. In another construction the internal shape is provided a beam 35 arranged for attachment to the edge. is of part-conical formation while in a further con­ struction the casing is of cylindrical shape jind is screw-threaded externally, the cavity being of annular formation. A number of the dampers may be em­ bodied in the airscrew each being tuned to deal with vibrations of a respective order. 634,267. Propeller spinners. Napier & Son Ltd., D., and Greenly, K. H. December 8, 1947. The spinner J is provided with turbine-like blading K on its moving part which draws hot air from the manifold H through the fixed blading H4. The hot air is then forced through the outer spinner casing J1, the fairing J3, and the double spinner casing / to the front orifice M where it escapes to pass over the external surface of the spinner. 92 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 (3): 1 – Mar 1, 1953

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032275
Publisher site
See Article on Publisher Site

Abstract

631,918. Aircraft and ship structures. English Elec­ tric Co. Ltd., Hollock, R. N., and Bradford, F. October 29, 1947. The skin of an aircraft or other lightweight struc­ ture is secured to a stringer attached to a rib by a These abstracts of British Patent Specifications are taken, by permission, from the officially prepared member which enables the stringer to be adjusted abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, about two independent axes, the attachment member 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies being capable of longitudinal axial adjustment. The of the full specifications are obtainable at the same address, price 2s. 8d. each. invention is shown applied to an aircraft structure, 630,183. Aircraft undercarriages. Dowty Equip­ suspension means on the aircraft, which attachment ment, Ltd., and Bound, R. H. December 15, 1947. comprises bolts 38 engageable in lugs 38a for co­ An aircraft undercarriage comprises a four-wheeled operation with a streamlined strut 39 projecting down­ bogie, of which two of the wheels, 16, 17, are inde­ wardly from the wing 40, or a suspension lug 48 pendently rotatable and are mounted on a common (FIG. 1, not shown). In the arrangement shown, lugs 41 transverse axle 15 at the lower end of the under­ carry cross-pins 42 for engagement by bifurcated carriage leg 13, the other two wheels 21, 24 being hooks 43 of release units 44, 45, so that the tank and strut 39 can be jettisoned. Fluid connexions are pro­ mounted in tandem in a fore-and-aft plane extending vided with frangible elbows 46, 47. 631,785. Aircraft wings. Vickers-Armstrongs, Ltd., and Richards, E. J. November 25, 1947. In order to delay the formation of compressibility shock waves to the same extent over the whole span of a wing, the angle of sweep back of the quarter in which the skin 1 is riveted to a stringer 3, the end of chord line is made greater over the inboard region which is secured by a pin or bolt to an eyebolt 8 en­ gaging by means of a screw thread with a bracket 7 secured to a rib 4. The angular setting of the stringer in relation to the rib is adjustable by rotation of the eyebolt 8 in the bracket 7 and by rotation of the stringer about the pin or bolt by which it is attached to the eye-bolt. The attachment may also be used for securing the skins of boats or vehicle bodies. 632,313. Screw propellers. De Havilland Aircraft Co. Ltd., and Hadwin, R. N. January 31, 1947. A vibration damper or absorber for attachment to a propeller blade, comprises a casing containing a mass consisting of a prc-determincd quantity of a mobile between and parallel to the wheels 16, 17, and being non-viscous or low-viscous liquid such as mercury, castorable and/or stcerablc. The wheels 21,24 are car­ some other mobile non-viscous liquid such as acety­ ried by brackets 18, 19 mounted on the axle 15 and lene tetrabromide or Clerici, or a combination of mer­ provided with supplementary shock absorbers 26, 27 cury and one of the latter liquids. For use at high connected to a cross-head 28 on the leg 13. Anti- temperatures a fusible metal such as Wood's metal shimmy devices may be provided for the castoring may be employed in a stainless steel casing. As shown, wheels, together with means for aligning them when the casing 3 is tapered externally to fit a recess 8 in the the aircraft is airborne. blade root, and is sealed by a closure plate 4, fitted with a closable inlet passage axially arranged in a 630,238. Drop-tanks. Faircy Aviation Co. Ltd., stem portion 5 for the introduction of the mercury 1. than at the wing tip. The leading edge may be formed Montague, E., and Collins, N. October 31, 1947. Balancing washers 7 may be mounted on the stem 5 with two or more straight portions Al, A2, FIG. 1 A drop-tank for aircraft comprising an inner re­ and retained by a nut 6. In a similar construction the having different angles of sweep back or by a smooth, ceptacle 25, outer rigid intcrdigitatcd sections 26-28 plate 4 is externally screw-threaded for engagement continuous curve C, FIG. 3. The trailing edge B may and end caps 29, 30, is preferably provided with an with casing, the internal shape of which is part- inner wall 35 between which and the top surface 28 be straight as shown in FIG. 1, or similar to the leading spherical. In another construction the internal shape is provided a beam 35 arranged for attachment to the edge. is of part-conical formation while in a further con­ struction the casing is of cylindrical shape jind is screw-threaded externally, the cavity being of annular formation. A number of the dampers may be em­ bodied in the airscrew each being tuned to deal with vibrations of a respective order. 634,267. Propeller spinners. Napier & Son Ltd., D., and Greenly, K. H. December 8, 1947. The spinner J is provided with turbine-like blading K on its moving part which draws hot air from the manifold H through the fixed blading H4. The hot air is then forced through the outer spinner casing J1, the fairing J3, and the double spinner casing / to the front orifice M where it escapes to pass over the external surface of the spinner. 92 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Mar 1, 1953

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