초록 ▼

The device for the individual control of the blades includes at least two sets of rotating swashplates centered on the rotor axis and non-rotating swashplates at least inclinable in all directions under the action of at least two actuators inserted between the first set and a non-rotating structure,

The device for the individual control of the blades includes at least two sets of rotating swashplates centered on the rotor axis and non-rotating swashplates at least inclinable in all directions under the action of at least two actuators inserted between the first set and a non-rotating structure, and under the action of at least one other actuator inserted between this structure and the second set. Each non-rotating plate is held by a connecting piece to the non-rotating structure, and each rotating plate is rotated with the rotor and connected to at least one blade respectively of the rotor via a respective pitch rod. The device also includes at least as many actuators as the rotor has blades, and all the actuators are non-rotating.

대표청구항 ▼

[ What is claimed is:] [1.]1. Device for individually controlling all blades of a rotor having a least four blades on a same plane for a rotary wing structure of an aircraft, comprising:a first set of swashplates comprisinga first rotating plate having a centre of rotation on an axis of rotation of

[ What is claimed is:] [1.]1. Device for individually controlling all blades of a rotor having a least four blades on a same plane for a rotary wing structure of an aircraft, comprising:a first set of swashplates comprisinga first rotating plate having a centre of rotation on an axis of rotation of the rotor, anda first non-rotating plate on which said first rotating plate rotates and having a center of pivoting on the axis of rotation of the rotor coincident with a centre of rotation of the first rotating plate and defining a centre of said first set of swashplates,at least two first operating actuators by which said first set is inclinable in all directions about the center thereof, said first actuators being inserted between a non-rotating structure of the aircraft and said first set, each said first actuator being articulated to the first non-rotating plate, and being held by a connecting means to said non-rotating structure,a connection between the first rotating plate and the rotor about the axis of the rotor by which the first rotating plate is rotated,respective first pitch rods by which the first rotating plate is connected to each of at least two first blades of the rotor,at least a second set of swashplates having a centre also lying on the axis of the rotor,at least one second operating actuator by which said second set is inclinable in all directions about a centre thereof and which is inserted between the non-rotating structure and said second set,wherein said second set includes a second non-rotating plate which is articulated to said second actuator and which is held by a connecting means to the non-rotating structure, while a second rotating plate of said second set is also rotated by a connection to the rotor about the axis of the rotor, and is connected to each of at least two second blades of the rotor by respective second pitchrods,wherein there are as many said first and second operating actuators and other operating actuators as the rotor has blades, and all of the operating actuators are non-rotating, andwherein the first and second rotating plates are each connected to a maximum of three blades by respective first and second pitch rods.