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Aviation History
1917
1917 - 0503.PDF
MAY 24, 1917. The control can be converted in a few minutes from the Dep type to the Curtiss type, the shoulder yoke operating the ailerons in the latter type being folded out of the way when not required. All control cables run over ball bearing bronze pulleys. The tail planes consist of a non-lifting stabilising surface, to which are hinged two elevator flaps, a vertical fin and a non- balanced rudder hinged to the fuselage stern post. The elevators are hinged to the stabilising plane in a semi-circular groove, which fits closely to the tubular leading edge of the elevator, so that no gap is formed. The rudder is similarly hinged. The landing chassis consists of two lami- nated ash U members upon which is sprung a tubular steel axle, having a streamline covering, carrying a pair of 26 in. x 5 in. disc wheels. The shock absorber acts on the pantagraph principle, the axle being bound to the U members by rubber cord, and ' .*••-• anchored to the same by two shackle bars, to similar pulleys on the upper ends of the struts and running one above the other. The axle is thus forced to move in a verti- beneath the top planer cal path, thereby evenly distributing the strain on the rubber Two pairs of struts support the central panel of the top cord. Where the shackles are clamped to the forward part of plane above the fuselage, and two pairs on each side of the the U member, the wood is protected by strips of sheet bronze. Three-quarter front view of the Standard H-3 tractor biplane. The "Pantograph " shock-absorbing device on theStandard H-3 chassis. Sketch showing the attachment of the interplane strut and compression rib to the main wing spar, with fittings. latter separate the top and bottom planes. The ends of thestruts are bronze tipped, secured by a single removable pin to the socket. The latter is bent to shape out of sheet steel,and is welded to a plate which is clamped by four bolts on the spar without piercing the latter. Anchorages for thebracing cables are formed on the fitting as shown in the sketch.The fuselage is rectangular in section, tapering to a vertical knife-edge at theTear. It is 25 ft. long with a maximum width and depth of 2 ft. 9 in. and3 ft. 6 in. respectively. The longerons are of ash, tapering rearwards from1 in. square. The uprights are tapered and channeled, and are attached to thelongerons by sheet metal clips. The pilot's cockpit is situated well aft ofthe planes, and the passenger's at the trailing edge. A 135 h.p. 6-cylindervertical Hall Scott engine is installed in the nose of the fuselage, being sup-ported by stout bearers, the forward ends of which are carried by a heavy-gauge steel plate forming the extremity of the fuselage. The engine portion ofthe fuselage is covered with sheet aluminium, and a rounded nose of thesame material is mounted on the front. The rest of the fuselage is covered withfabric including the turtle deck, which is built up of spruce battens. The following are the principal dimensions of the StandardH-3 Span, 40 ft. ; chord, 6 ft. 6 in. ; gap, 6 ft. 6 in. ; height, 10 ft. 7 in. ; gliding angle, 1 in 8 ; weight empty, 1,700 lbs. ;useful load, 800 lbs. ; speed range, 46-84 m.p.h. ; climbing speed, 3,500 ft. in 10 minutes. gj The Standard -H-3 tractor biplane and its designer, Charles H. Day. 503
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