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Month in the Patent Office

Month in the Patent Office May, 1931 AIRCRAFT ENGINEERING 127 A Selection of the More Important Aircraft and Engine Specifications Published Recently valv e 22 being seated on the piston when the 340,066. Internal - combustio n Engines. valve 21 is open. The spring 15 in the rear casing 4 Junkers, H., 21, Kaiserplatz, Dessau, Anhalt, is given an initial compression by a screw 18 and Germany. Oct. 14, 1929, No. 31156. Convention lock nu t 20 so tha t its valve 21 is normally open. date, Nov. 20, 1928. [Class 7 (ii)]. B y operating a valve 29 air is admitted from a In an engine with oppositely moving pistons reservoir 30 t o a pipe 26 and enters a chamber 27 driving two crank shafts which are geared together, above th e piston 14 through the valve 22 until the the load is driven off that shaft which receives the pressur e on the piston overcomes the spring 15. heavier power from its associated piston or pistons. Air also enters th e rear brake chamber 3 through a This is the piston which has a lead or a greater pipe 25 and a reservoir 24 through a pipe 23. displacement over the other piston in the same Air from the reservoir 24 also enters the apparatus cylinder. on the front wheels but their valves 21 close imme­ Where the two shafts are connected by a train diatel y as their springs 15 are unstressed. of gearing 171-201, the drive is taken off tha t pinion Should the front wheels touch the ground first, next the heavier loaded shaft 161. thei r brakes are applied to a degree not exceeding The engine auxiliarie s such as pump s o r generators th e initial degree of braking applied to the rear are driven off the secondary shaft 151. wheel, but when the rear wheel contacts with the 341,920 . Aeroplane wheel brakes. Dunlop Rubbe r Co., Ltd., 32, Osnaburgh Street, London, an d Fellowes, F. , For t Dunlop, Erdington, Birming­ ham . Oct. 23, 1929, No. 32151. [Class 4.] A brake for aeroplane wheels comprises a roller or endless band, preferably frictionally retarded, adapte d to engage the tyre and arranged within a cowl or casing which may also enclose the wheel so as to reduce wind resistance. Various construc­ tion s of brake are described. I n Fig. 1, the roller 1 is carried by a pair of parallel arms 2 pivoted to th e cowl 4 an d is retarded when applied to th e tyr e a b y a brake band 6 which is anchored to the cowl with the interposition of a spring 9. The retarding means may instead comprise a friction pad by which the roller is moved toward s the tyre or a bush disposed between the roller an d its spindle or spring-pressed plates bearing on the ends of the roller or an inflatable cylindrical 341,251. Aeroplane wings. Nieuport-Astra, chambe r engaging the interior or exterior of the ground its valve 21 is again opened and further 50, Boulevard Gallieni, Issy-les-Moulincaux, Seine, roller. The roller spindle may be eccentrically pressure is available. Should the rear wheel leave France. Dec. 31, 1929. No. 39923. Convention mounte d so that it is engaged with the tyre by th e ground the piston 14 descends and the valve 22 date, Jan. 2. [Class 4.] turnin g the spindle. The axis of the roller may be opens a passage through the piston to exhaust inclined to the wheel axis and i t or a pair thereof In metal wings of th e typ e having a meta l covering port s 28, the chambers 27 at the front wheels ma y engage the shoulder or sides of the tyre. composed of thin metal panels d, the width of exhaustin g through ball valves 33. These valves I n another construction an endless band running which is equal t o the distance between two adjacent 33 and a similar one a t the rear wheel also ensure over a pair of rollers is adapte d to engage the tyre. main ribs a of th e wing framework and which panels th e release of braking pressure when the control are strengthened on their inner face by spars e, valv e 29 is opened. the metallic elements connecting the ends of the Variatio n of load on the front wheels, b y varying rectilinearly abuttin g spars of two adjacent panels th e compression of the springs 15, controls the are formed with sole pieces f which extend a sub­ individual pressures in the chambers 3, and should stantial distance along the spars and are riveted eithe r wheel leave the ground the brake is released to them. b y the corresponding valve 22 opening the brake cylinder to exhaust. The rear control spring 15 The main ribs a, Fig. 1, are beaded a t their outer ma y bo connected to a skid instead of a wheel axle. edges b aroun d a wire or spring c. Sole pieces f are placed cither above or between the panel d and 341,964 . Aircraft wheel brake and shock- spars c. They are extended at points coinciding absorbin g gear. Westinghouse Brake & Saxby with the positions of spars e. Fig. 1, or are rein­ Signal Co., Ltd., 82, York Road, King's Cross, forced by gussets at these points. Their outer London.—(Assignees of Down S. G.; 204, Haw­ edges g are shaped to fit round the bead b and thorn e Street, Edgewood, Pennsylvania, U.S.A.) inter-connection is effected by beading a semi- Oct. 25, 1929, No. 32467. [Class 4.] tubular member h around the whole assembly. Th e pressure in the fluid pressure brakes of the Fig, 4 shows a modification in which angle-strips front landing wheels of an aeroplane is controlled i are riveted to the borders f and adjacent panels automaticall y in accordance with the load on the are connected by riveting together the strips i of rear wheel or skid and also with the load on each each panel and a straight projecting portion of wheel. Two forward wheels F and a rear wheel G rib a. ar e shown having brakes applied by pressure fluid admitte d to diaphragm chambers 3. Each wheel is supporte d by a plunger 7 moving in a casing 4 * These abstracts of complete specifications of Patents recently against a spring 11 an d rubber pad 13, an d a par t 9 published ate specially compiled, by permission of H.M. Stationery Office, from abridgements which are issued by the Office. Printed secured to the wheel axle has an arm 17 which copies of the full specifications can be obtained from the Patent support s a hollow plunger 16 moving in another Office, 25, Southampton Buildings, London, W.C.2. price one bore in the casing 4. A spring 15 in each plunger shilling each. 16 supports a piston 14 and controls an inlet valve Except where otherwise stated, the specification is unaccompanied by drawings if none is reproduced. 21 which has an exhaust valve 22 on its stem, the 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 (5): 1 – May 1, 1931
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029402
Publisher site
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Abstract

May, 1931 AIRCRAFT ENGINEERING 127 A Selection of the More Important Aircraft and Engine Specifications Published Recently valv e 22 being seated on the piston when the 340,066. Internal - combustio n Engines. valve 21 is open. The spring 15 in the rear casing 4 Junkers, H., 21, Kaiserplatz, Dessau, Anhalt, is given an initial compression by a screw 18 and Germany. Oct. 14, 1929, No. 31156. Convention lock nu t 20 so tha t its valve 21 is normally open. date, Nov. 20, 1928. [Class 7 (ii)]. B y operating a valve 29 air is admitted from a In an engine with oppositely moving pistons reservoir 30 t o a pipe 26 and enters a chamber 27 driving two crank shafts which are geared together, above th e piston 14 through the valve 22 until the the load is driven off that shaft which receives the pressur e on the piston overcomes the spring 15. heavier power from its associated piston or pistons. Air also enters th e rear brake chamber 3 through a This is the piston which has a lead or a greater pipe 25 and a reservoir 24 through a pipe 23. displacement over the other piston in the same Air from the reservoir 24 also enters the apparatus cylinder. on the front wheels but their valves 21 close imme­ Where the two shafts are connected by a train diatel y as their springs 15 are unstressed. of gearing 171-201, the drive is taken off tha t pinion Should the front wheels touch the ground first, next the heavier loaded shaft 161. thei r brakes are applied to a degree not exceeding The engine auxiliarie s such as pump s o r generators th e initial degree of braking applied to the rear are driven off the secondary shaft 151. wheel, but when the rear wheel contacts with the 341,920 . Aeroplane wheel brakes. Dunlop Rubbe r Co., Ltd., 32, Osnaburgh Street, London, an d Fellowes, F. , For t Dunlop, Erdington, Birming­ ham . Oct. 23, 1929, No. 32151. [Class 4.] A brake for aeroplane wheels comprises a roller or endless band, preferably frictionally retarded, adapte d to engage the tyre and arranged within a cowl or casing which may also enclose the wheel so as to reduce wind resistance. Various construc­ tion s of brake are described. I n Fig. 1, the roller 1 is carried by a pair of parallel arms 2 pivoted to th e cowl 4 an d is retarded when applied to th e tyr e a b y a brake band 6 which is anchored to the cowl with the interposition of a spring 9. The retarding means may instead comprise a friction pad by which the roller is moved toward s the tyre or a bush disposed between the roller an d its spindle or spring-pressed plates bearing on the ends of the roller or an inflatable cylindrical 341,251. Aeroplane wings. Nieuport-Astra, chambe r engaging the interior or exterior of the ground its valve 21 is again opened and further 50, Boulevard Gallieni, Issy-les-Moulincaux, Seine, roller. The roller spindle may be eccentrically pressure is available. Should the rear wheel leave France. Dec. 31, 1929. No. 39923. Convention mounte d so that it is engaged with the tyre by th e ground the piston 14 descends and the valve 22 date, Jan. 2. [Class 4.] turnin g the spindle. The axis of the roller may be opens a passage through the piston to exhaust inclined to the wheel axis and i t or a pair thereof In metal wings of th e typ e having a meta l covering port s 28, the chambers 27 at the front wheels ma y engage the shoulder or sides of the tyre. composed of thin metal panels d, the width of exhaustin g through ball valves 33. These valves I n another construction an endless band running which is equal t o the distance between two adjacent 33 and a similar one a t the rear wheel also ensure over a pair of rollers is adapte d to engage the tyre. main ribs a of th e wing framework and which panels th e release of braking pressure when the control are strengthened on their inner face by spars e, valv e 29 is opened. the metallic elements connecting the ends of the Variatio n of load on the front wheels, b y varying rectilinearly abuttin g spars of two adjacent panels th e compression of the springs 15, controls the are formed with sole pieces f which extend a sub­ individual pressures in the chambers 3, and should stantial distance along the spars and are riveted eithe r wheel leave the ground the brake is released to them. b y the corresponding valve 22 opening the brake cylinder to exhaust. The rear control spring 15 The main ribs a, Fig. 1, are beaded a t their outer ma y bo connected to a skid instead of a wheel axle. edges b aroun d a wire or spring c. Sole pieces f are placed cither above or between the panel d and 341,964 . Aircraft wheel brake and shock- spars c. They are extended at points coinciding absorbin g gear. Westinghouse Brake & Saxby with the positions of spars e. Fig. 1, or are rein­ Signal Co., Ltd., 82, York Road, King's Cross, forced by gussets at these points. Their outer London.—(Assignees of Down S. G.; 204, Haw­ edges g are shaped to fit round the bead b and thorn e Street, Edgewood, Pennsylvania, U.S.A.) inter-connection is effected by beading a semi- Oct. 25, 1929, No. 32467. [Class 4.] tubular member h around the whole assembly. Th e pressure in the fluid pressure brakes of the Fig, 4 shows a modification in which angle-strips front landing wheels of an aeroplane is controlled i are riveted to the borders f and adjacent panels automaticall y in accordance with the load on the are connected by riveting together the strips i of rear wheel or skid and also with the load on each each panel and a straight projecting portion of wheel. Two forward wheels F and a rear wheel G rib a. ar e shown having brakes applied by pressure fluid admitte d to diaphragm chambers 3. Each wheel is supporte d by a plunger 7 moving in a casing 4 * These abstracts of complete specifications of Patents recently against a spring 11 an d rubber pad 13, an d a par t 9 published ate specially compiled, by permission of H.M. Stationery Office, from abridgements which are issued by the Office. Printed secured to the wheel axle has an arm 17 which copies of the full specifications can be obtained from the Patent support s a hollow plunger 16 moving in another Office, 25, Southampton Buildings, London, W.C.2. price one bore in the casing 4. A spring 15 in each plunger shilling each. 16 supports a piston 14 and controls an inlet valve Except where otherwise stated, the specification is unaccompanied by drawings if none is reproduced. 21 which has an exhaust valve 22 on its stem, the

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: May 1, 1931

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