Abstract

81784111 ABSTRACT A rotary wing aircraft includes a non-rotating structural backbone formed to accommodate power and signal transmission components. First and second variable pitch rotor blades are connected to the backbone and supported for rotation about an axis of rotation in first and second rotor planes of rotation and first and second pitch controllers are connected to the backbone for controlling a cyclic pitch of the first and second rotor blades. An engine or motor is located below the second rotor plane of rotation and configured to provide power to drive the first variable pitch rotor blade about the axis of rotation. A torque tube extends through an interior of a central column of the backbone and is configured to transmit rotational motion from the engine or motor to the first variable pitch rotor blade to drive the first variable pitch rotor blade about the axis of rotation. Date Recue/Date Received 2020-09-17

IPC Classes  ?

• B64C 27/78 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
• B64C 27/80 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement for differential adjustment of blade pitch between two or more lifting rotors

Abstract

A rotary wing aircraft comprising a non-rotating structural backbone extending parallel to a rotor axis of rotation. First and second variable pitch rotor blades are supported for rotation about the respective axis of rotation. A first and second pitch controllers located between the first rotor plane of rotation and the second rotor plane of rotation for controlling the pitch of the respective variable pitch rotor blades. A plurality of first and second pitch control links coupled to the respective pitch controller so that displacement of the respective pitch control links operates the respective pitch controller. The first and second pitch controllers are rotated about the rotor axis of rotation relative to each other by an angle so that the first and second pitch control links are interleaved around the circumference of the non-rotating structural backbone and alternately connected to the first and second pitch controllers thereby forming a compact installation.

IPC Classes  ?

• B64U 40/10 - On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
• B64U 10/17 - Helicopters
• B64U 30/24 - Coaxial rotors
• B64U 30/296 - Rotors with variable spatial positions relative to the UAV body
• B64C 27/78 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
• B64C 27/80 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement for differential adjustment of blade pitch between two or more lifting rotors

Abstract

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

IPC Classes  ?

• B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings