Method of controlling a main rotor of a rotorcraft, an associated control system, and a rotorcraft fitted with such a control system

Patent metadata

Field	Value
Publication number	US-9926075-B2
Application number	US-201615356733-A
Country	US
Kind code	B2
Filing date	Nov 21, 2016
Priority date	Nov 24, 2015
Publication date	Mar 27, 2018
Grant date	Mar 27, 2018

Abstract

A control method and system for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation. The control system has a control member for controlling the collective pitch of the blades of the main rotor. The control member is movable over an amplitude of positions between two extreme physical stops. A calculation unit calculates a collective pitch angle for the blades of the main rotor, referred to as an “auto-rotation collective pitch”. This enables the main rotor to rotate at a speed of rotation that is optimum for the stage of flight in auto-rotation of the rotorcraft. A motor means controls the position of the control member at a predetermined position, referred to as the “auto-rotation position”, in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”.

First claim

What is claimed is:

1. A control method for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation of the rotorcraft, the control method comprising:
a calculation step for calculating a collective pitch angle for the blades of the main rotor, referred to as the “auto-rotation collective pitch”, the “auto-rotation collective pitch” generating a speed of rotation of the main rotor that is optimized for the stage of flight in auto-rotation of the rotorcraft; and
a drive step of applying motor drive to a control member for controlling the collective pitch of the blades of the main rotor, the control member being movable over an amplitude of positions lying between two extreme physical stops, the drive step being performed by motor means and being used when a pilot of the rotorcraft manually moves the control member over the amplitude of positions of the control member and positions the control member beyond a first stop position of the control member, the first stop position being generated by the motor means exerting a first predetermined force opposing a manual actuation force exerted by the pilot on the control member, the first predetermined force acting locally over the amplitude of positions of the control member when the control member is arranged at the first stop position, the manual actuation force exerted by the pilot on the control member being capable of exceeding the first predetermined force;
wherein the motor means enable the position of the control member to be servo-controlled on a predetermined position referred to as the “auto-rotation position” in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”, and wherein the first stop position of the control member coincides with a “desynchronization position” in which the control member generates a control setpoint for servo-controlling a current collective pitch of the blades of the main rotor on a “desynchronization collective pitch” for desynchronizing rotary motion between the main rotor and a power plant of the rotorcraft.

2. A method according to claim 1 , wherein the amplitude of positions of the control member includes a second stop position for the control member, the second stop position being generated by the motor means exerting a second predetermined force opposing the manual actuation force exerted by the pilot of the rotorcraft on the control member, the second predetermined force acting locally on the amplitude of positions of the control member when the control member is arranged at the second stop position, the second predetermined force being greater than the manual actuation force exerted by the pilot on the control member.

3. A method according to claim 2 , wherein the second stop position of the control member coincides with a limit position of the control member in which the control member generates a control setpoint for servo-controlling a current collective pitch of the blades of the main rotor on a minimum pitch for the blades of the main rotor generating a maximum speed of rotation of the main rotor during the stage of flight in auto-rotation of the rotorcraft.

4. A method according to claim 1 , wherein the control method includes a step of generating sense signals for informing the pilot of the rotorcraft, the sense signals being representative of the current collective pitch of the blades of the main rotor and of the “auto-rotation collective pitch” calculated during the calculation step.

5. A method according to claim 4 , wherein the sense signals are representative of the minimum pitch of the blades of the main rotor generating a maximum speed of rotation of the main rotor during the stage of flight in auto-rotation of the rotorcraft.

6. A method according to claim 1 , wherein the motor means enable a stick of the control member to be moved relative to a support secured to a structure of the rotorcraft and to exert a position return force on the stick of the control member when a current position of the control member is different from the “auto-rotation position”.

7. A control system for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation of the rotorcraft, the control system comprising:
a control member for controlling the collective pitch of the blades of the main rotor, the control member being movable over an amplitude of positions lying between two extreme physical stops;
a calculation unit for calculating a collective pitch angle for the blades of the main rotor referred to as an “auto-rotation collective pitch”, the “auto-rotation collective pitch” enabling the main rotor to rotate at a speed of rotation that is optimum for the stage of flight in auto-rotation of the rotorcraft; and
motor means for generating over the amplitude of positions of the control member a first stop position for the control member, the first stop position being generated by exerting a first predetermined force opposing a manual actuation force exerted by a pilot of the rotorcraft on the control member, the first predetermined force acting locally over the amplitude of positions of the control member when the control member is arranged at the first stop position, the manual actuation force exerted by the pilot on the control member being capable of exceeding the first predetermined force;
wherein the motor means servo-control the position of the control member on a predetermined position referred to as the “auto-rotation position” in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”, and wherein the first stop position of the control member coincides with a “desynchronization position” in which the control member generates a control setpoint for servo-controlling a current collective pitch of the blades of the main rotor on a “desynchronization collective pitch” for desynchronizing rotary motion between the main rotor and a power plant of the rotorcraft.

8. A control system according to claim 7 , wherein the motor means generate over the amplitude of positions of the control member a second stop position for the control member, the second stop position being generated by exerting a second predetermined force opposing the manual actuation force exerted by the pilot of the rotorcraft on the control member, the second predetermined force acting locally on the amplitude of positions of the control member when the control member is arranged at the second stop position, the second predetermined force being greater than the manual actuation force exerted by the pilot on the control member.

9. A control system according to claim 8 , wherein the second stop position of the control member coincides with a limit position of the control member in which the control member generates a control setpoint for servo-controlling a current collective pitch of the blades of the main rotor on a minimum pitch for the blades of the main rotor generating a maximum speed of rotation of the main rotor during the stage of flight in auto-rotation of the rotorcraft.

10. A control system according to claim 7 , wherein the control system includes information means generating sense signals for informing the pilot of the rotorcraft, the sense signals being representative of the current collective pitch of the blades of the main rotor and of the “auto-rotation collective pitch” calculated by the calculation unit.

11. A control system according to claim 10 , wherein the sense signals are representative of the minimum pitch of the blades of the main rotor generating

Assignees

• Airbus Helicopters

Inventors

• Vallart Jean-Baptiste

Classifications

• B64C27/14 Primary

  Direct drive between power plant and rotor hub · CPC title

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C13/04 Primary

  actuated personally · CPC title

• B64D25/00

  Emergency apparatus or devices, not otherwise provided for · CPC title

• B64C27/57 Primary

  automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust · CPC title