GB446509A - Improvements in or relating to aircraft - Google Patents

Abstract

446,509. Aircraft with rotary - wing systems. BILLING, N. P., Royal Court Chambers, Sloane Square, London. Oct. 25, 1934, Nos. 30670 and 34102. [Class 4] An aircraft comprises a bladed rotor having two or more radial blades, each of which is combined with a supplementary aerofol spaced outwardly from the axis of rotation and adjustable about a substantially vertical axis. As shown, the aircraft body houses a seat 21 and an engine unit 22 adjustable through screw gear 47 in an arcuate guide 46. Arms 23 extend laterally from the body to support rotors 24. Landing-wheels 27 are carried in fairings 28 and are supported in arms 25. Cruciform stabilizing-fins, to one pair of which a rudder is articulated are provided on the body. The arms 23 terminate in a cup 31 carrying pylons 33. A boss 36 having sockets 37 to receive the root of each rotor blade 24 rotates on anti-friction bearings 80, 81, 82 and is driven through a worm 40 and worm-wheel 39. The blade roots are mounted on pivots 51, 56 for horizontal and vertical movement, controlled by laminated springs 57, the pivots 56 being carried by members 55 free to turn in the sockets 37. The members 55 are provided with crank-arms 61 provided with rollers 62 which engage a sleeve 63. The sleeve is adjustable on the pylon 33 to vary the incidence of the rotor blades. A cam 68 is slidably mounted on the pylon and is engaged by a cam follower 73 to which is connected rods 78 having flexible portions 79. The rods pass through the rotor blades and are connected at their outer ends to cranks 91 which control feathering movement of the auxiliary surfaces 90 axial adjustment of the cam 68 causes to a greater or less degree feathering of the auxiliary surfaces. Upward or downward movement of the cam causes respectively rearward or forward motion of the craft. The cams 68 are adjusted by cables 69, Fig. 16, connected to a lever 100 movable about a pivot 101. The sleeves 64 are adjusted from a hand-wheel 102, Fig. 18 through bevel-wheels 114, 115, worm 118 and worm-wheel 119, lever 112 and an endless cable 65 connected to the sleeves. Two rotors may be superimposed. The fuselage may be provided with air inlets and outlets 105, 106 into passages connecting which, the exhaust of a radial cylinder power unit is delivered. The exhaust impinges on turbine vanes 107 to rotate a wheel and suck air into the inlet ports. The incidence of the two rotor blades may be adjusted differentially. According to the first Provisional Specification a rotor may be disposed at the rear of the aircraft and according to the second Provisional Specification, two superposed rotors may be driven in reverse directions and a free-wheel may be interposed in the rotor drive.