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Month in the Patent Office

Month in the Patent Office 48 AIRCRAFT ENGINEERING February, 1933 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 373,988 . Aeroplane wings. Panstwowe Zak- vertical position utilizing the direct thrust of the lad y Lotnicze. Mokotow, Lotniske, Warsaw. Nov. screw in conjunction with th e reaction on th e planes. 29, 1930, No. 36033. Convention date, Dec. 4, Fig . 4 shows a machine having an upturned tail 1929. Void [Published under Sect. 91 of the Acts]. provided with a skid 7 and two sets of wheels 5, 6 [Class 4.] so tha t the machine can alight and take off in the Th e wing or upper wing of an aeroplane is dis­ position shown or upon the wheels 5, 6. The posed directly on th e fuselage and is stepped down­ wheels 6 may be replaced by skids and the skid 7 wardl y at its central portion a, b adjacent the mounted on a straight fuselage having its tail planes longitudinal axis of th e aeroplane so tha t th e lower­ mounted on an upstanding fin. A machine with a most par t of this portion lies in or beneath the level longer fuselage also is described which at starting of the under-surface c, d of the wing so as to offer and alighting in a small space has to swing about th e minimum of interference with the view of a its rear skid. Fig. 8 shows a modification in which pilot seated behind the wing. hinged struts 35 are utilized when starting from or alightin g in a small space. Twin propellers on and then securing the tubular booms to th e struc­ concentric axes driven from a transverse engine or tur e so formed by riveting them to the gusset two direct driven screws on the wings may be used plates . As applied to a two boom girder formed in to prevent rotation of the fuselage due to back sections, the intermediate structure comprises torque , or wide ailerons may be used to counteract gusset plates 10, Figs. 1 and 2, to which diagonal th e torque due to a single propeller. A variable members 11 are riveted. The diagonal members pitc h screw may be used. ar e built up from T-section members having Th e Specification as open to inspection under inwardly disposed flanges 15 inter-connected by Sect. 91 (3) (a) comprises also the following subject- channe l members 13 of which the bases are secured matter . Fig 10 (Cancelled) shows a modification a t the points of inter-section by rivets 14 passed in which the rear part 13 of the fuselage is hinged throug h washers equal in thickness to the flanges 15. The T-sections are cut away at 16 and riveted to the front part at 14 and can be locked in its 375,733 . Aeroplanes. Messier, G. L. R. J., to throat members 17 shaped to embrace the normal position by a hook 19, Fig. 13 (Cancelled), 29, Avenue Léon Gambetta, Montrouge, Seine, tubula r boom 20. The gusset plates 10 may be operate d by the pilot. A spring 21 anchored to France . Feb. 12, 1932, No . 4223 . Convention date, th e rear part 13 is connected to a block adjustable extended as at 19 to provide attachments for Feb . 16, 1931. [Class 4.] in a slide 24 by a link 25, th e par t 13 tendin g to rise bracin g members or may be flanged as at 21 to To enable an opening to be provided in the when the block is in one position and to fall when increase their rigidity. The booms 20 may be of floor of an aeroplane fuselage having cantilever th e block is in the other position. This subject- solid drawn steel tube or may be formed from sheet wings springing from the lower part of it, th e wing matte r docs not appear in the Specification as ben t into tubular form and secured along a riveted spar s are secured to longitudinal members 2, Fig. 4, accepted. la p joint. In the latter case the rivet holes 22 for actin g in torsion and connected at their ends by securing the lap joint in the part of the boom cross members 21, or, as shown in Fig. 5, the y are located at the gussets are drilled on assembly with connected to members 8, 9 of a rectangular frame 381,389 . Aircraft controls; framework. th e gussets, the rivets thus passing through the an d upwardly bent parts B, B l of the spars are A.T.S. Co., Ltd., 5, Clement's Inn, Strand, London, double thickness of the lap joint and the gusset. connected together by struts 5, 51. The parts 8, and North, J. D., Hill House, Haton Hill, Norwich. Th e girder section is terminated by channel end 9 may comprise flanged tubes secured to the spar Nov. 27, 1931, No. 32850. [Class 4.] frames 23 havin g inward extensions 24 forming the plates, conical extensions 81, 91 being similarly end gusset plates. The end frames form part of th e intermediate staying structure and are riveted t o the diagonal members 11 before assembly of the booms. The end frames are apertured to allow of th e boom sections being joined together by internally screwed strengthening sleeves and oppositely- threade d spigots of the type described in Specifica­ tion 334,405. [Class 4, Aeronautics.] According t o modifications the diagonal members may be of channe l section having apertured webs or may be angle sections. The invention is applicable to girders, such as wing spars, having three or four booms. 376,789 . Aeroplanes modified for vertical flight . Fiat Soc. Anon., 250, Via Nizza, Turin, secured and connected together by cross-ties 10, 11. Italy . April 15, 1931, No . 11218. Convention date, Th e parts 8, 9 in this case are not in torsion. The April 16, 1930. [Class 4.] part s 5, B, B l of the rear spars or the rear spars An aeroplane having a one-piece fuselage is themselves may be omitted. If an opening is fitted with a large diameter propeller and has required in the upper part of the fuselage, the means enabling it to alight or take off in a nearly Th e main spar of aircraft control surfaces having strut s 5, 5 1 may be replaced by a rectangular frame substantiall y triangular or quadrilateral cross p, q, r, s similar to th e frame 8 . . 11. sections is formed from a metal tube and is placed a t one of the forward edges to act as a stringer for 376,364 . Aircraft framework. Vickers supportin g the covering. Fig. 1 shows an applica­ (Aviation), Ltd. and Wallis B. N., Weybridge tion to an aileron of triangular cross section having Works, Byfteet Road, Weybridge, Surrey. April an obtuse apex angle 2 a t which is located a hinge 7. 11, 1931, No. 10704. [Class 4.] A tubular spar 3 determines the contour of this Girders of the type comprising tubular booms angle and the covering 4 is wrapped directly round stayed apart by diagonal members extending in a th e spar. Ribs 5 are attached to the spar by continuou s zig-zag formation and secured to the flanged brackets 6. In a modification the tubular booms by means of gusset plates are assembled by spar 3 is disposed at the forward acute angle and is first riveting the diagonal members to the gusset formed with a substantially triangular cross section. plates to form the intermediate staying structure Th e ribs and rearwardly extending angle brackets which support the hinge 7 are attached to angle brackets on the spar. In an application to an * These abstracts of complete specifications of Patents recently elevator, Fig. 3, of quadrilateral section with three published are specially compiled, by permission of H.M. Stationery angles near the forward edge, the contour of the Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from centra l angle is formed by the tubular spar 3. the Patent Office, 25, Southampton buildings, London, W.C.2, Flanged brackets 6 attached to the spar support either sheet by sheet as issued, on payment of a subscription of ribs 5. The forward wall of the spar is locally 5 per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address depressed as at 12 to receive hinges 7. The spar price 1s. each. ma y be strengthened at these points by an internal Except where otherwise stated, the specification is unaccom­ tubula r liner. 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 5 (2): 1 – Feb 1, 1933

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029659
Publisher site
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Abstract

48 AIRCRAFT ENGINEERING February, 1933 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 373,988 . Aeroplane wings. Panstwowe Zak- vertical position utilizing the direct thrust of the lad y Lotnicze. Mokotow, Lotniske, Warsaw. Nov. screw in conjunction with th e reaction on th e planes. 29, 1930, No. 36033. Convention date, Dec. 4, Fig . 4 shows a machine having an upturned tail 1929. Void [Published under Sect. 91 of the Acts]. provided with a skid 7 and two sets of wheels 5, 6 [Class 4.] so tha t the machine can alight and take off in the Th e wing or upper wing of an aeroplane is dis­ position shown or upon the wheels 5, 6. The posed directly on th e fuselage and is stepped down­ wheels 6 may be replaced by skids and the skid 7 wardl y at its central portion a, b adjacent the mounted on a straight fuselage having its tail planes longitudinal axis of th e aeroplane so tha t th e lower­ mounted on an upstanding fin. A machine with a most par t of this portion lies in or beneath the level longer fuselage also is described which at starting of the under-surface c, d of the wing so as to offer and alighting in a small space has to swing about th e minimum of interference with the view of a its rear skid. Fig. 8 shows a modification in which pilot seated behind the wing. hinged struts 35 are utilized when starting from or alightin g in a small space. Twin propellers on and then securing the tubular booms to th e struc­ concentric axes driven from a transverse engine or tur e so formed by riveting them to the gusset two direct driven screws on the wings may be used plates . As applied to a two boom girder formed in to prevent rotation of the fuselage due to back sections, the intermediate structure comprises torque , or wide ailerons may be used to counteract gusset plates 10, Figs. 1 and 2, to which diagonal th e torque due to a single propeller. A variable members 11 are riveted. The diagonal members pitc h screw may be used. ar e built up from T-section members having Th e Specification as open to inspection under inwardly disposed flanges 15 inter-connected by Sect. 91 (3) (a) comprises also the following subject- channe l members 13 of which the bases are secured matter . Fig 10 (Cancelled) shows a modification a t the points of inter-section by rivets 14 passed in which the rear part 13 of the fuselage is hinged throug h washers equal in thickness to the flanges 15. The T-sections are cut away at 16 and riveted to the front part at 14 and can be locked in its 375,733 . Aeroplanes. Messier, G. L. R. J., to throat members 17 shaped to embrace the normal position by a hook 19, Fig. 13 (Cancelled), 29, Avenue Léon Gambetta, Montrouge, Seine, tubula r boom 20. The gusset plates 10 may be operate d by the pilot. A spring 21 anchored to France . Feb. 12, 1932, No . 4223 . Convention date, th e rear part 13 is connected to a block adjustable extended as at 19 to provide attachments for Feb . 16, 1931. [Class 4.] in a slide 24 by a link 25, th e par t 13 tendin g to rise bracin g members or may be flanged as at 21 to To enable an opening to be provided in the when the block is in one position and to fall when increase their rigidity. The booms 20 may be of floor of an aeroplane fuselage having cantilever th e block is in the other position. This subject- solid drawn steel tube or may be formed from sheet wings springing from the lower part of it, th e wing matte r docs not appear in the Specification as ben t into tubular form and secured along a riveted spar s are secured to longitudinal members 2, Fig. 4, accepted. la p joint. In the latter case the rivet holes 22 for actin g in torsion and connected at their ends by securing the lap joint in the part of the boom cross members 21, or, as shown in Fig. 5, the y are located at the gussets are drilled on assembly with connected to members 8, 9 of a rectangular frame 381,389 . Aircraft controls; framework. th e gussets, the rivets thus passing through the an d upwardly bent parts B, B l of the spars are A.T.S. Co., Ltd., 5, Clement's Inn, Strand, London, double thickness of the lap joint and the gusset. connected together by struts 5, 51. The parts 8, and North, J. D., Hill House, Haton Hill, Norwich. Th e girder section is terminated by channel end 9 may comprise flanged tubes secured to the spar Nov. 27, 1931, No. 32850. [Class 4.] frames 23 havin g inward extensions 24 forming the plates, conical extensions 81, 91 being similarly end gusset plates. The end frames form part of th e intermediate staying structure and are riveted t o the diagonal members 11 before assembly of the booms. The end frames are apertured to allow of th e boom sections being joined together by internally screwed strengthening sleeves and oppositely- threade d spigots of the type described in Specifica­ tion 334,405. [Class 4, Aeronautics.] According t o modifications the diagonal members may be of channe l section having apertured webs or may be angle sections. The invention is applicable to girders, such as wing spars, having three or four booms. 376,789 . Aeroplanes modified for vertical flight . Fiat Soc. Anon., 250, Via Nizza, Turin, secured and connected together by cross-ties 10, 11. Italy . April 15, 1931, No . 11218. Convention date, Th e parts 8, 9 in this case are not in torsion. The April 16, 1930. [Class 4.] part s 5, B, B l of the rear spars or the rear spars An aeroplane having a one-piece fuselage is themselves may be omitted. If an opening is fitted with a large diameter propeller and has required in the upper part of the fuselage, the means enabling it to alight or take off in a nearly Th e main spar of aircraft control surfaces having strut s 5, 5 1 may be replaced by a rectangular frame substantiall y triangular or quadrilateral cross p, q, r, s similar to th e frame 8 . . 11. sections is formed from a metal tube and is placed a t one of the forward edges to act as a stringer for 376,364 . Aircraft framework. Vickers supportin g the covering. Fig. 1 shows an applica­ (Aviation), Ltd. and Wallis B. N., Weybridge tion to an aileron of triangular cross section having Works, Byfteet Road, Weybridge, Surrey. April an obtuse apex angle 2 a t which is located a hinge 7. 11, 1931, No. 10704. [Class 4.] A tubular spar 3 determines the contour of this Girders of the type comprising tubular booms angle and the covering 4 is wrapped directly round stayed apart by diagonal members extending in a th e spar. Ribs 5 are attached to the spar by continuou s zig-zag formation and secured to the flanged brackets 6. In a modification the tubular booms by means of gusset plates are assembled by spar 3 is disposed at the forward acute angle and is first riveting the diagonal members to the gusset formed with a substantially triangular cross section. plates to form the intermediate staying structure Th e ribs and rearwardly extending angle brackets which support the hinge 7 are attached to angle brackets on the spar. In an application to an * These abstracts of complete specifications of Patents recently elevator, Fig. 3, of quadrilateral section with three published are specially compiled, by permission of H.M. Stationery angles near the forward edge, the contour of the Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from centra l angle is formed by the tubular spar 3. the Patent Office, 25, Southampton buildings, London, W.C.2, Flanged brackets 6 attached to the spar support either sheet by sheet as issued, on payment of a subscription of ribs 5. The forward wall of the spar is locally 5 per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address depressed as at 12 to receive hinges 7. The spar price 1s. each. ma y be strengthened at these points by an internal Except where otherwise stated, the specification is unaccom­ tubula r liner. panied by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Feb 1, 1933

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