Method for Compensation of Gyroscopic Forces of a Rotor in a Helicopter
AssigneeHeliScandia ApS
InventorGert Lading
Life of this patent
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Abstract
In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11).
Claims11
A method for controlling the pitch and roll of a helicopter with a controller, wherein the helicopter comprises a fuselage (31) and a rotor (24, 26) with wings (26) above the fuselage, the rotor having a rotor axis and being provided on a support structure, the support structure being connected to the fuselage by an actuator driven coupling (34), the coupling comprising an actuator system (36) capable of moving the support structure with the rotor relative to the fuselage in two dimensions normal to the rotor axis for thereby from a start orientation causing a change of orientation of the support structure with the rotor relatively to a vertical direction (19), wherein the vertical direction is the direction from the centre of gravity of the helicopter to the centre of gravity of the earth, the controller (2) comprising an input channel (5) for receiving input signals (4) for changing the orientation of the support structure with the rotor relative to the vertical direction (19) and an output channel (6) for sending output signals (7) to the actuator system (36) for moving the support structure of the rotor relative to the fuselage on the basis of the input signals,
- the method comprising
- receiving by the controller the input signals for changing the orientation of the support structure with the rotor axis in a first tilting direction (17) relatively to the vertical direction,
- as a response to the input signal, sending an output signal to the actuator system (36)
- as a response to the output signal, starting the actuator system to cause a movement of the support structure with the rotor relative to the fuselage in a direction (22) substantially normal to the first tilting direction and substantially normal to the rotor axis and along a first part of a circular path in the direction of the rotation of the rotor.
Dependencies are inferred from the claim text.