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Month in the Patent Office

Month in the Patent Office AIRCRAF T ENGINEERING 325 December, 1931 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 352,42 6 Aircraft wing structures. Chag- 350,804 . Airship framework. Goodyear- niard, E., 84, Ru e de Paris, Boulogne-sur-Seine, and Zeppelin Corporation, 1144, Market Street, Akron, Legoy, H. R., 76, Boulevard de la Vilette, Paris, Ohio, U.S.A. Aug. 11, 1930, No. 24025. Con­ bot h in France. Dec. 30, 1929, No. 39810. Con­ ventio n date, Aug. 30, 1929. [Class 4.] vention date, Dec. 29, 1928. Void [Published under To enable an assembling frame to bo dispensed Sect. 91 of th e Acts]. [Class 4.] wit h when erecting polygonal wire-braced main Aeroplane wings of the type having a stressed rings of a rigid airship each main ring comprises meta l covering secured to the internal structure by a plurality of polygonal rings braced by inwardly rivetin g and in which the riveting is effected from projecting girders arranged between the constituent th e outside of the structure are characterized by rings. Each ring 10, Fig. 1, comprises two spaced th e use of widely spaced box ribs and a covering rin g girders 12, Fig . 3, havin g longitudinally spaced formed of panels fixed to the ribs and to a leading joint s 14, 15 a t the corners of the polygon. Short edge former. The internal structure of the wings, girders 17 have their outer ends connected between Figs. 1 and 3, comprises a spar L, having booms rings 12 a t the joints 14 and their inner ends con­ I1, I2, I3 braced by diagonal struts, upon which are nected by girders 21 to the joints 15. At the threade d box ribs N secured b y gussets g t o a channel sides and at the upper portion of the ring 10 the th e propeller shaft is above the wings it may be section trailing edge member A t o which the aileron girders 21 embrace three sides of the polygon and driven by an extension of a vertically disposed ar e braced by girders 22. The lower portion of shaft which connects the two engine crank-shafts th e ring 10 is braced by a framework 23. throug h bevel gearing. The engine is mounted so that its reaction torque is absorbed by laterally disposed struts. The engine casing may be hinged t o th e fuselage, and it may form part of the strut syste m of a wing. 352,260 . Screw propellers. Soc. Anon. des Ateliers d'Aviation L. Breguet and Breguet, L., 115, Rue de la Pompe, Paris. July 12, 1930, No. 21184. [Class 114.] In automatically variable pitch screw propellers, th e boss is displaceable axially on and rotatable throug h a small angle around the propeller shaft an d the blade is connected with a projection on the shaft so that its pitch is varied automatically as th e boss moves in relation to the shaft and in accordance with the ratio of the tractive effort to th e driving couple of the propeller. In one form th e boss 2 has a projection 13 carrying a roller 12 which is in contact with a cam face 11 on a fixed sleeve on the propeller shaft 1. The roller 11 thus communicates the drive from the shaft to the roller whilst allowing the boss th e two degrees of freedom. A propeller blade 3 pivotally mounted in a socket on the boss has an arm 7 engaging at 8 with a projection 9 from the shaft whereby its pitch angle is varied as the propeller boss 2 takes up new positions. In another form the driving shaft 30 is is hinged ; nose ribs N1 complete the structure. keyed to a cylindrical member 31 upon which the Ribs N comprise two vertical plates a, Fig. 4, boss is freely mounted. Keyed to this member riveted to channel section webs b. The edges of the ar e cross members 34, 35 which are coupled by plates a are flanged over as a t a1, except in the lead­ 349,895 . Mounting aeroplane engines and rod s 3G, th e member 34 havin g pins 52 whic h project ing edge portion, Fig. 12, where the flanges are propellers . Junkers, H., 21, Kaiserplatz, Dessau, into curved slots 51 in the pitch-adjusting arms 50 reversed to allow for the riveting of a leading edge Anhalt , Germany. Dec. 8, 1930, No. 37001. pinned to a projection on each blade root. The former T ; the latter has wooden beads u1, u2 a t the Convention date, Dec. 21 , 1929. [Class 4.] coupling rods 36 have pins 56 with self-adjusting inner edges. Covering panels P extend between In a flying machine driven by opposed cylinder ball races for driving rods 53 which at their other adjacen t side plates of consecutive ribs and are ends are similarly connected to pins 57 on sockets engines, the engines 11, 12 are arranged with a secured by rivets to the flanges a1 the space between 42 carrying the blades. considerable portion of the cylinders projecting th e side-plates a of each rib being sufficient to allow verticall y above or below the contour surface of of the insertion of the riveting tool. The front th e flying machine. The propeller shaft 21 is edges of the panels P are secured by screws to the arrange d remote from the wings and it can form beads u1, u2 and the rear edges by rivets to the th e spindle of one of the pinions interconnecting flanges of channel member A. The side edges of th e two engine crank-shafts 16, 17. In a modifi­ panels P have upturned flanges enabling closing cation the engines are arranged below and the members f to be riveted between adjacent panels, propeller shafts above or below the wings. When Fig . 20. Panels P may have folds o as in Fig. 4 or continuou s alternate corrugations, alternatively riveted-on stiffening sections may be used. Longi­ * These abstracts of complete specifications of Patents recently tudina l stiffening members e are riveted to the published are specially compiled, by permission of H.M. Stationery interior surface of panels P and may extend Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from beyond the edges of each panel and overlap in the the Patent Office, 25, Southampton Buildings, London, W.C.2, space between side-plates a of each rib an d there be either sheet by sheet as issued on payment of a subscription of rivete d together. According to modifications more 5s. per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address, tha n one spar may be employed, and the leading price 1s. each. edg e former T may be omitted, the panels P being Except where otherwise stated, the specification is unaccompanied mad e continuous round the leading edge. 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 3 (12): 1 – Dec 1, 1931

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029492
Publisher site
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Abstract

AIRCRAF T ENGINEERING 325 December, 1931 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 352,42 6 Aircraft wing structures. Chag- 350,804 . Airship framework. Goodyear- niard, E., 84, Ru e de Paris, Boulogne-sur-Seine, and Zeppelin Corporation, 1144, Market Street, Akron, Legoy, H. R., 76, Boulevard de la Vilette, Paris, Ohio, U.S.A. Aug. 11, 1930, No. 24025. Con­ bot h in France. Dec. 30, 1929, No. 39810. Con­ ventio n date, Aug. 30, 1929. [Class 4.] vention date, Dec. 29, 1928. Void [Published under To enable an assembling frame to bo dispensed Sect. 91 of th e Acts]. [Class 4.] wit h when erecting polygonal wire-braced main Aeroplane wings of the type having a stressed rings of a rigid airship each main ring comprises meta l covering secured to the internal structure by a plurality of polygonal rings braced by inwardly rivetin g and in which the riveting is effected from projecting girders arranged between the constituent th e outside of the structure are characterized by rings. Each ring 10, Fig. 1, comprises two spaced th e use of widely spaced box ribs and a covering rin g girders 12, Fig . 3, havin g longitudinally spaced formed of panels fixed to the ribs and to a leading joint s 14, 15 a t the corners of the polygon. Short edge former. The internal structure of the wings, girders 17 have their outer ends connected between Figs. 1 and 3, comprises a spar L, having booms rings 12 a t the joints 14 and their inner ends con­ I1, I2, I3 braced by diagonal struts, upon which are nected by girders 21 to the joints 15. At the threade d box ribs N secured b y gussets g t o a channel sides and at the upper portion of the ring 10 the th e propeller shaft is above the wings it may be section trailing edge member A t o which the aileron girders 21 embrace three sides of the polygon and driven by an extension of a vertically disposed ar e braced by girders 22. The lower portion of shaft which connects the two engine crank-shafts th e ring 10 is braced by a framework 23. throug h bevel gearing. The engine is mounted so that its reaction torque is absorbed by laterally disposed struts. The engine casing may be hinged t o th e fuselage, and it may form part of the strut syste m of a wing. 352,260 . Screw propellers. Soc. Anon. des Ateliers d'Aviation L. Breguet and Breguet, L., 115, Rue de la Pompe, Paris. July 12, 1930, No. 21184. [Class 114.] In automatically variable pitch screw propellers, th e boss is displaceable axially on and rotatable throug h a small angle around the propeller shaft an d the blade is connected with a projection on the shaft so that its pitch is varied automatically as th e boss moves in relation to the shaft and in accordance with the ratio of the tractive effort to th e driving couple of the propeller. In one form th e boss 2 has a projection 13 carrying a roller 12 which is in contact with a cam face 11 on a fixed sleeve on the propeller shaft 1. The roller 11 thus communicates the drive from the shaft to the roller whilst allowing the boss th e two degrees of freedom. A propeller blade 3 pivotally mounted in a socket on the boss has an arm 7 engaging at 8 with a projection 9 from the shaft whereby its pitch angle is varied as the propeller boss 2 takes up new positions. In another form the driving shaft 30 is is hinged ; nose ribs N1 complete the structure. keyed to a cylindrical member 31 upon which the Ribs N comprise two vertical plates a, Fig. 4, boss is freely mounted. Keyed to this member riveted to channel section webs b. The edges of the ar e cross members 34, 35 which are coupled by plates a are flanged over as a t a1, except in the lead­ 349,895 . Mounting aeroplane engines and rod s 3G, th e member 34 havin g pins 52 whic h project ing edge portion, Fig. 12, where the flanges are propellers . Junkers, H., 21, Kaiserplatz, Dessau, into curved slots 51 in the pitch-adjusting arms 50 reversed to allow for the riveting of a leading edge Anhalt , Germany. Dec. 8, 1930, No. 37001. pinned to a projection on each blade root. The former T ; the latter has wooden beads u1, u2 a t the Convention date, Dec. 21 , 1929. [Class 4.] coupling rods 36 have pins 56 with self-adjusting inner edges. Covering panels P extend between In a flying machine driven by opposed cylinder ball races for driving rods 53 which at their other adjacen t side plates of consecutive ribs and are ends are similarly connected to pins 57 on sockets engines, the engines 11, 12 are arranged with a secured by rivets to the flanges a1 the space between 42 carrying the blades. considerable portion of the cylinders projecting th e side-plates a of each rib being sufficient to allow verticall y above or below the contour surface of of the insertion of the riveting tool. The front th e flying machine. The propeller shaft 21 is edges of the panels P are secured by screws to the arrange d remote from the wings and it can form beads u1, u2 and the rear edges by rivets to the th e spindle of one of the pinions interconnecting flanges of channel member A. The side edges of th e two engine crank-shafts 16, 17. In a modifi­ panels P have upturned flanges enabling closing cation the engines are arranged below and the members f to be riveted between adjacent panels, propeller shafts above or below the wings. When Fig . 20. Panels P may have folds o as in Fig. 4 or continuou s alternate corrugations, alternatively riveted-on stiffening sections may be used. Longi­ * These abstracts of complete specifications of Patents recently tudina l stiffening members e are riveted to the published are specially compiled, by permission of H.M. Stationery interior surface of panels P and may extend Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from beyond the edges of each panel and overlap in the the Patent Office, 25, Southampton Buildings, London, W.C.2, space between side-plates a of each rib an d there be either sheet by sheet as issued on payment of a subscription of rivete d together. According to modifications more 5s. per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address, tha n one spar may be employed, and the leading price 1s. each. edg e former T may be omitted, the panels P being Except where otherwise stated, the specification is unaccompanied mad e continuous round the leading edge. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Dec 1, 1931

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