Patent GB-332312-A (GB)
Title: Flying machine
IPC: B64C27/26
Filed: 1929-04-30
Abstract: 332,312. Isacco, V. April 30, 1929. Addition to 276,997. Machines supported by rotary wing systems; propelling; steering and balancing; tanks, arrangement of.-Machines of the kind described in the parent Specification have means for controlling separately and simultaneously the throttles and the ignition of the engines carried at the wing tips, means for locking the sustaining system to the fuselage at will, and means for controlling the lateral and longitudinal stability by additional pivoted surfaces located between the blades of the rotary wing system. Where the engines at the wing tips drive single propellers, hinged surfaces are provided to compensate for the gyroscopic couple and their controls may be connected to the throttle controls. A modified universal joint for the sustaining blades also is described. Each engine throttle is controlled by a lever 32, Figs. 7 and 8, pivoted about a shaft 30 and having locking quadrants 33, the shaft 30 being movable by a master lever 31 for controlling both throttles simultaneously. Where four engines are used, three levers 32 are provided, one controlling two engines. The levers 32 are connected bv cables 35 to bars 45 extending through slots 46 in a fixed central column 14 to the inner rings 39 of two ball bearings, the outer rings being connected by cables 38 to the throttles 42 on carburettors 43. The outer rings of the ball races are returned by springs 52 and cables 61. The ignition of all the engines is controlled by a master switch 49, and that of the individual engines by switches 50 in series with the switch 49. The switches 50 are connected to brushes 51 contacting with rings 54 on the propeller hub 12, cables 40 connecting these rings to magnetos 56. Alternatively the positions of the brushes and rings 51, 54 may be reversed. The carburettor 43 on each wing is hinged to take up a position determined by gravity and centrifugal force, and is fed from a service tank 59 supplied with petrol from a main tank 58 within the wing, stop cocks 60, 63 being provided. The cock 60 may be replaced by an automatic valve for controlling the supply of fuel in accordance with the speed of rotation of the wings. An oil tank 64 with a cock 65 supplies oil to the engine. A four-bladed wing system is described universally jointed to a common hub which has four rigid outriggers carrying blades which can be cyclically adjusted by the pilot to control the lateral and longitudinal balance of the machine.. The longitudinal control is coupled to an elevator. For locking and releasing the hub of the rotating wing system, a member 74, Fig. 14, can be slid along the column 14 to engage or disengage a member 73 on the hub. The cable 75 which pulls down the member 74 against the pull of springs 78 may also have a lost motion connection 83 to a clutch member 91 so that the wing system can be set in rotation or stepped gradually respectively after release, or before being positively locked. The clutch member 91 also enables rapid steering movements to be made by clutching the column 14 to the rotating wing system, For articulating the blade shafts 13 to the hub, a spherical member 34 is screwed on its end and fastened by a bolt 95, the member 34 being held in position in a screwed socket in the hub by members 47, 94. The incidence of the rotating blades may be controlled by the pilot by means of hinged rear flaps 25, Fig. 15. The engines at the wing tips may each drive two propellers in opposite directions or. where one propeller is used, a small aileron 98 is provided to compensate for the effect of the gyroscopic couple. These ailerons are controlled by the pilot and may be operated in conjunction with the throttle control. The engines may be arranged to give a thrust higher than the blade axis so that a smaller aileron is required, or the thrust may be through the axis. These ailerons 98 may be arranged to form continuations of the main rear flaps 25 on the blades.