Access the full text.
Sign up today, get DeepDyve free for 14 days.
References for this paper are not available at this time. We will be adding them shortly, thank you for your patience.
634,345. Aerofoils. Griffith, A. A. September 18, 1947. Drawings to Specification. The thickness-chord ratio of a swept-back or swept- forward aerofoil increases progressively in the span- wise direction from a point intermediate the root and These abstracts of British Patent Specifications are taken, by permission, from the officially prepared tip towards the tip to maintain the isobars thereon at a abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, substantially constant inclination to the direction of free stream, whereby the shock-stalling characteristics 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the aerofoil are improved. of the full specifications are obtainable at the same address, price 2s. 8d. each. 635,823. Aircraft structures. King, E. P. June 1,1945. In forming a laminated structure two preformed 633,695. Propelling aircraft; propeller casings. during both translational flight and vertical ascent it structures arc first formed by bonding metal sheets to Brcguct, L. July 27, 1946. Convention date, Feb. 15. assumes an attitude substantially parallel to the fibrous material with synthetic resin, the two fibrous A propeller 1 in a stationary tubular casing 2 direction of air flow, variations in said attitude, to suit layers being subsequently bonded together or to an rotates inside a guard ring 3 which is mounted for free different flight conditions, being achieved by an ad intermediate layer or structure by means of a cold rotation inside the casing on bearings 4, the free flow justable tab pivoted on the trailing edge of the setting adhesive at normal or slightly elevated tempera stabilizer. The stabilizer, 11, FIG. 2, is freely pivoted on ture. FIG. 1 shows a metal layer 21 attached to a a substantially horizontal transverse tube 13 and is fibrous layer 22. The metal layer may be first rough provided with an adjustable tab 12 pivoted at 15 and ened mechanically, clectrolytically or chemically. Two formed with a lever 16. The extremity of lever 16 is such preformed sheets may be joined with their pivoted to one end of a threaded telescopic member metallic layers outwards, with or without the inter 17, 18 of which the other end is connected to a univer position of veneers of wood or strips 23, of balsa sal coupling 21 offset below the axis of the tube 13. wood, FIG. 4. Alternatively the sheets may be spaced Rotation of the universal coupling 21 to cause exten apart with laminated stringers 24, FIG. 7. The spaces sion or contraction of the member 17, 18 is clfcctcd between the stringers are left empty or filled with by gearing 24 directly controlled by the pilot through lightweight material such as expanded rubber. A rib a chain drive 27. FIG. 4 shows the tab 12 set to give the 27, FIG. 9, may be secured to one of two composite stabilizer 11 a positive incidence relative to the airflow sheets by a rivet 28 before the two sheets are secured direction /;. When the airflow changes to the direction together. They may be secured with a further rib be v and moves the stabilizer into the position 11a differ tween. FIG. 11 shows a method of forming a com ential movement of the linkage 17, caused by the offset posite sheet using two metallic sheets 28, 29 with their pivot b, moves the tab 12 into line with the stabilizer 11 edges butting at 30. A cross-grain piece of veneer 31 is and causes the latter to lie at zero incidence with re laid on the join with a strip of metal 32 on top. The spect to the airflow direction v. In most cases the fibrous layer 34 is then laid over the whole and all the layers secured together. Alternatively the fibrous of air between the blade tips and the guard ring being layer 34 may be laid directly on the metal sheets and reduced to a minimum by reducing the clearance bet the pieces 21, 32 on top. FIG. 13 shows a number of ween tips and rings and shaping the blade ends to separate sheets assembled in an autoclave for forming conform with the interior of the ring. The flow of air into a single composite sheet with a single fibrous through the casing is regulated by a ring 5 adjustably backing layer. The component parts are laid on a mounted in front of the casing to form an adjustable metal platen 36 supported on a channel frame 37. slat and controllable gills or flaps 7 at the rear. The A layer of hessian or wire gauze is laid over the parts inlet is provided with a fixed 'cone' 13; annular de which arc then covered with a sheet of rubber, etc., flectors 14 ensure a homogeneous distribution of the secured to the edges of the platen. Heat and pressure air flow; the outlet is profiled at 15. The air com are then applied and any vapours produced exhausted pressed by the propeller is heated by engine cooling, through holes 38 and 39 in the platen by pipes 40, 41. exhaust gases, and/or burners for the purpose of in A curved platen may be used and the specification creasing thrust. The propeller may be driven by an describes the manufacture of a double skinned aero internal combustion engine or a turbine motor. The plane fuselage in this way. The metal and fibrous ele rotatable guard ring 3 may be replaced by fixed baffle ments of the inner and outer skins arc separately plates. assembled on platens in the form of male and female moulds respectively and bonded with syntheticjresin. The two bonded skins, on the two moulds, are then 634,339. Helicopters. Autogiro Co. of America. united with cold setting adhesive. An aeroplane wing, August 8, 1947. Convention date, March 24, 1942. FIGS. 16 and 17, is built in two halves and joined by In helicopter aircraft of the type on which an air tongues 72, 73. The inner and outer surfaces of each screw is mounted transversely offset from the rotor centre of pressure of the aerofoil is located aft of the half are formed of metal skins 58, backed by "fibrous axis for effecting translational flight and for balancing axis of the tube 13 and in order to balance the rota layers 59 and arc spaced by stringers 60. Near the ends tional effect caused by the lift acting about said axis, a of the shear member 61 the space between the layers bias spring z is fitted. In an alternative arrangement a 59 is filled with laminated strips 62. The shear mem constant setting of the tab 12 relative to the stabilizer ber 61 is secured to the wing surfaces by plywood 11 irrespective of the attitude of said stabilizer is ob angles 63 and the half-ribs 68 and 69 by plywood tained by making the centre line of the control rod 17 angles 70, 71. The shear member is of laminated con approximately intersect the axis of the tube 13. On struction, formed in two parts, attached to the two helicopters fitted with two transversely disposed halves of the wing, joined by a tongue 65 or by pairs contra-rotating rotors, two independent stabilizers of angles. may be located, one under the influence of each rotor. the rotational effects of the rotor on the fuselage, the anti-rotational effect, which decreases with an increase in forward speed, is augmented by mounting on one extremity of the tail plane furthest from the airscrew an adjustable cambered fin. The incidence of fin 7, pivoted at 8, may be pre-sct on the ground or pilot- controlled in flight and the surface is cambered to pro duce a moment about the rotor axis tending to aug ment the anti-rotational effect of airscrew 3, within the slipstream of which is located a fixed fin 5 and a con trollable rudder 6. Specification 393,976 is referred to. 634,340. Helicopters. Autogiro Co. of America. August 8, 1947. Convention date, July 7, 1942. A helicopter is provided at the rear of the rotor with a floating stabilizer, freely pivoted on a substantially horizontal axis and positioned in such a manner that 1~'* Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Apr 1, 1953
Access the full text.
Sign up today, get DeepDyve free for 14 days.