7 8 AIRCRAFT ENGINEERIN G April, 1929 A Selection from Important Recently Published Aircraf t and Aero Engine Specifications No . 301,639. Aircraft. Ordidge, F. H., City, Long Island, New York, U.S.A. June 30, oblique folds under stress, as described in the The Woods, Manor Road, Ruislip, and Wil 1928, No. 19053. paren t Specification. Fig. 2 shows a wing in liams, D. L. H., Hillside, Ickenham Road, Cylinders, construction of and mounting; driving which the central portion forms a box girder, Ickenham, both in Middlesex. Nov. 24, 1927, gear.—In engines wherein the pistons drive on of which the webs x, 5 of the spars an d ribs and No . 31680. t o a central cam 14 fixed on the shaft 13, the also the upper and lower coverings are formed of thin metal developing oblique folds under Land wheels, runners, and skids; shock- cylinder barrels are formed in two parts, the stress. The webs are strengthened by channel absorbers, applications of.—In order to transmit inner part 30 of each cylinder projecting into th e casing 10 and being slotted centrally as at members y, 7 secured to the webs and booms wing torsion from the free ends to the roots 40, 41, Fig. 3, to allow the cam to pass. The and the skin is supported by similar members. thereof, the landing carriage is constructed in Holes 1, 8, 11 give access to the interior of the two portions, each comprising two triangular wing, the edges of the holes being reinforced struts , b, c and j , k, m, connected at their apices t o carry the wheel, and pivoted at their and watertight covers being provided. Water- bases fore-and-aft of one of th e wings, th e former towards the wing-tip, the latter near its root. The strut b, c has an extension a, which forms th e wheel-axle. The member j is constructed a s a spring or hydraulic shock absorber, and the tigh t hollow fairing pieces w are secured to the axle a is pivotally connected to the piston of box girder by hinges. The booms of the spars th e shock-absorber. In th e modification shown pistons are interconnected by links 18 and the have several layers of metal of different thick th e axle a is connected to a sleeve g, slidable cylinder parts 30 are cut away at the sides to ness, the outer layers being the thickest. A on the member j , and connected to th e piston. allow for th e passage of these links ; the tongues wing with a single spar also is described, the which are thus formed in the cylinder parts 30 No . 302,156. Brakes for Aeroplanes , &c. front portion of the wing being formed as a are rigidly connected by cross pieces 50, 51. Cerini, L., 22, Via Clitunno, Rome. Dec. 6, torsion-resisting girder. A wing with three The outer part 20 and inner part 30 of each 1928, No. 36073. Convention date, Dec. 10, spars also is described. cylinder have corresponding flanges 34, 32 for 1927. Not yet accepted. Abridged as open to attachmen t to th e case, a spigot and socket joint No . 303,058. Beams; Aircraft Stays. inspection under Sect. 91 of the Acts. being provided between the two parts. A peg Dornier Metallbauten Ges. and Domier, C., A brake is controlled by relative movement is provided on th e case t o determine th e position Friedrichshafen-on-Bodensee, Germany. Oct. between th e wheel an d th e fuselage in such a way of the two parts during assemblage. 22, 1928, No . 30566. Convention date, Dec. 27, tha t the resultant of the forces acting on the 1927. Not yet accepted. Abridged as open to wheel always passes through a point G1 just No . 302,945. Launching Aeroplanes. inspection under Sect. 91 of the Acts. in front of the Regan, P., and Richards, A., Admiraltv, Hollow metal beams for aircraft and other centre of grav London. Oct. 5, 1926, No. 24670. structures are formed from seamless tubes of ity. As shown, A catapult comprises a moving carriage uniform or non-uniform thickness, by modifying th e whee l is bearing a faster-moving trolley. In the form th e cross section to a square, triangular, allowed a limi shown, a trolley 16 running on a carriage 11 rectangular, or other shape. A plain tube of te d movement is drawn a t twice the speed of the carriage by circular section is shaped into the beam sec against shock ropes 13 passing over wheels 12 on the carriage, tions shown in Figs. 2 and 3, or int o a hexagonal absorbers m, and and the carriage is drawn along a runway 1 a t section ; from the non-uniform tube, Fig. 5, are th e pivoted lever twice th e speed of a pneumatic ram 6 b y similar produced sections, such as Fig. 7, having one l controlling the connections. The ram may be operated by side of greater thickness t o resist larger stresses; brake is rocked firing a charge of cordite, and towards the end b y a rod dd con of its stroke is retarded by the necessity of nected to the forcing oil through small holes. The trolley and fuselage as the carriage are returned by ropes 21, 23 passing wheel moves, th e over wheels 20, 22. The runway 1, which braking force ma y have removable extensions can be turned being increased b y motor or hand gear on rails 3 round on centre as it moves forward, and vice versa. The wheels post 2, and can be fixed by clamps 4. The are mounted on separate axles a ben t as shown and pivoted to the fuselage, and the automatic adjustmen t of the brakes keeps the machine on a straight course in spite of lateral forces tending to make one wheel get ahead of the other. The brake can be disabled by a manual adjustmen t of the rod dd. The Specification docs no t admit of satisfactory abridgment. carriage ropes may be operated by screw-and- nu t gear instead of by a ram, or rope gear may No . .302,559. Internal-combustion En from the tube shown in Fig. 9 are formed beams be dispensed with, the carriage being operated gines . Caminez, H., Alton Apartments , Garden having two thick sides, such as Figs. 10 and 11 ; b y a ram through multiplying mechanism. from the tube shown in Fig. 13 is produced the No . 303,360. Aircraft. Rohrbach Metall- beam section shown in Fig. 14, having two * The following abstracts of complete specifica Flugzeugbau Ges., 9, Kiautschoustrassc, Berlin. tions of Patents recently published are specially thick and two thin uniform sides; and from the Dec. 20, 1928, No. 37690. Convention date, compiled by permission of H.M. Stationery Office, tub e shown in Fig. 15 is produced the beam from abridgments appearing in the Patent Journal. Dec. 31, 1927. Addition to 274,085. Not yet section, Fig. 16, having increased thickness at Printed copies of the full specifications can be accepted. Abridged as open to inspection th e angles. The sides of the beams may be obtained from the Patent Office, 25, Southampton under Sect. 91 of the Acts. recessed inwardly at intervals, as shown in Buildings, London, W.2, price one shilling each. Fig. 7, or may be formed with openings A, Planes, construction of.—A hollow metal air Except where otherwise stated if no illustration Figs. 2 an d 3, giving access t o screws or rivets B craft wing has its beams or ribs, or both, con is reproduced the specification is unaccompanied and with inturned edges. by drawings. structed with thin metal webs which develop
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 1929
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