| 摘要 |
FIELD: aeronautical engineering; helicopters with coaxial main rotors. ^ SUBSTANCE: proposed helicopter has fuselage, power plant with transmission and gearbox on whose shafts coaxial main rotor is mounted, control system with differential blade pitch control mechanism made in form of leverage with non-rotating rod located inside shaft of upper main rotor which is movable in axial direction and is kinematically linked with bell cranks mounted above upper main rotor and connected with blade carriers. Helicopter is provided with hollow fixed support located inside shaft of upper main rotor; its lower end is rigidly secured to gearbox housing; upper end of support has through diametrical slots and units for mounting the equipment. Rod of leverage mechanism is located inside support and kinematic linkage is made in form of slider consisting of two bushes concentrically embracing each other; outer bush is rotating. Slider is mounted on external surface protruding from upper shaft and is connected via through slots rod; articulated to rotating bush of slider are bell cranks. ^ EFFECT: possibility of mounting equipment above coaxial main rotors. ^ 2 dwg |
