GB590863A - Improvements in or relating to rotating-wing aircraft - Google Patents

Abstract

590,863. Helicopters. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-OUEST. April 24, 1945, No. 10249. Convention date, Feb. 15, 1944. [Glass 4] A rotating wing aircraft comprising main and balancing rotors is provided with means responsive to the difference between the main rotor torque and the torque from the balancing rotor, or to the difference of torques respectively proportional thereto, for adjusting the balancing rotor. In the construction according to Fig. 5, the transmission between the engine. 14 and the main lifting rotor 1 includes a reduction gear 3, of which the pinions are mounted on a lever 4 which moves in accordance with torque variations, the movements being transmitted by a link 8 to a pivotally mounted member 5 carrying the tail propeller 2, to impart cyclical pitch variations to the blades of the latter. The drive shaft 37 of the tail propeller includes a cardan joint 38 to accommodate rotary movement of the mounting 5. A vibration damper 10 is connected to the link 8. According to a further construction, Figs. 2 and 3 (not shown), the movements of the link 8 may effect pitch variations in the blades of a tail propeller mounted on a horizontal transverse axis, while in a third construction, Fig. 4 (not shown), the link adjusts the inclination of the propeller shaft to vary the horizontal thrust component. For steering, the pilot's control member is operated to exert a force on the torque lever 4 and thus unbalance the torques of the two rotors. Specification 265,547, [Class 4], is referred to.