Device for regulating the speed of rotation of a rotorcraft rotor, a rotorcraft fitted with such a device, and an associated regulation method

Patent metadata

Field	Value
Publication number	US-9815561-B2
Application number	US-201615272898-A
Country	US
Kind code	B2
Filing date	Sep 22, 2016
Priority date	Sep 25, 2015
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

A device for regulating the speed of rotation of at least one main rotor of a rotorcraft, which speed is known as the speed NR. Such a rotorcraft comprises at least one manual flight control member for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of a current position of the at least one control member; and detector means enabling a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air.

First claim

What is claimed is:

1. A device for regulating the speed of rotation of at least one main rotor of a rotorcraft, which speed is known as the speed NR, the rotorcraft comprising:
at least one manual flight control member for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of a current position of the at least one control member; and
detector means enabling a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air;
wherein the device for regulating the speed NR includes management means for automatically controlling the speed NR on at least two mutually distinct predetermined speeds NR 1 and NR 2 , the at least two predetermined speeds NR 1 and NR 2 being selected as alternatives as a function firstly of the control setpoint C delivered by the control member, and secondly of the current state of the rotorcraft as detected by the detector means, the management means serving to control the speed NR on:
a first speed NR 1 when the control setpoint C delivered by the control member is greater than a first predetermined threshold value C 1 ; and
a second speed NR 2 less than the first speed NR 1 when the following two conditions are satisfied;
the control setpoint C delivered by the control member is less than or equal to the first predetermined threshold value C 1 ; and
the detected current state of the rotorcraft corresponds to the “ground” state.

2. A device according to claim 1 , wherein the management means control the speed NR on a third speed NR 3 less than the second speed NR 2 when the control setpoint C delivered by the control member is less than or equal to a second predetermined threshold value C 2 and when the detected current state of the rotorcraft corresponds to the “ground” state, the second predetermined threshold value C 2 being less than the first predetermined threshold value C 1 .

3. A device according to claim 1 , wherein the rotorcraft includes a selector member serving, when the selector member is actuated by a pilot of the rotorcraft, to deliver an instruction manually to the management means in order to control the speed NR at least temporarily on a fourth speed NR 4 greater than the first speed NR 1 .

4. A device according to claim 1 , wherein the device includes verification means for acting at regular time intervals to verify an operating state of an engine of the rotorcraft for driving rotation of the at least one main rotor, the verification means being suitable for transmitting information to the management means representative of an engine failure in order to enable the management means to inhibit any reduction of the speed NR when the detected current state corresponds to the “ground” state.

5. A device according to claim 1 , wherein the device includes calculation means for acting at regular time intervals to calculate the absolute travel speed of the rotorcraft, the management means serving to control the speed NR on:
the first speed NR 1 when the following two conditions are satisfied:
the detected current state of the rotorcraft corresponds to the “ground” state; and
the absolute travel speed of the rotorcraft is greater than a predetermined absolute travel speed V 1 ; and

the second speed NR 2 when the following three conditions are satisfied;
the control setpoint C delivered by the control member is less than or equal to the first predetermined threshold value C 1 ;
the detected current state of the rotorcraft corresponds to the “ground” state; and
the absolute travel speed of the rotorcraft is less than or equal to the predetermined absolute travel speed V 1 .

6. A device according to claim 1 , wherein the device includes measurement means for acting at regular time intervals to measure the altitude of the rotorcraft relative to the ground, the management means serving to control the speed NR on:
the first speed NR 1 when the following two conditions are satisfied:
the detected current state of the rotorcraft corresponds to the “ground” state; and
the altitude of the rotorcraft relative to the ground is greater than a predetermined altitude A 1 ; and

the second speed NR 2 when the following three conditions are satisfied;
the control setpoint C delivered by the control member is less than or equal to the first predetermined threshold value C 1 ;
the detected current state of the rotorcraft corresponds to the “ground” state; and
the altitude of the rotorcraft relative to the ground is less than or equal to the predetermined altitude A 1 .

7. A device according to claim 1 , wherein the first predetermined threshold value C 1 lies in a range of values extending from 30% to 60% of a maximum setpoint corresponding to an extreme position for the control member.

8. A device according to claim 2 , wherein the second predetermined threshold value C 2 lies in a range of values extending from 15% to 40% of a maximum setpoint corresponding to an extreme position of the control member.

9. A rotorcraft including:
at least one main rotor driven by at least one engine;
at least one manual flight control member for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of the current position of the at least one control member; and
detector means for detecting a current state from among at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air;
wherein the rotorcraft includes a regulator device for regulating the speed NR in accordance with claim 1 .

10. A method of regulating the speed of rotation of at least one main rotor of a rotorcraft known as the speed NR, the method comprising at least the steps consisting in:
a manual flight control step for delivering a collective pitch control setpoint C for the blades of the at least one main rotor, the control setpoint C being a function of a current position of at least one control member; and
a detection step consisting in detecting a current state to be detected from at least two distinct states of the rotorcraft, namely a “ground” state in which the rotorcraft is in contact with the ground, at least in part, and a “flight” state in which the rotorcraft is at least being sustained in the air;
wherein, after the manual control step and after the detection step, the method comprises a management step consisting in automatically controlling the speed NR on at least two mutually distinct predetermined speeds NR 1 and NR 2 , the at least two predetermined speeds NR 1 and NR 2 being selected as alternatives as a function firstly of the control setpoint C delivered by the control member, and secondly the detected current state of the rotorcraft, the management step serving to control the speed NR on:
a first speed NR 1 when the control setpoint C delivered by the control member is greater than a first predetermined threshold value C 1 ;
a second speed NR 2 less than the first speed NR 1 when the following two conditions are satisfied;
the control setpoint C delivered by the control member is less than or equal to the first predetermined threshold value C 1 ; and
the detected current state of the rotorcraft corresponds to the “ground” state.

11. A method according to claim 10 , wherein the management step controls the speed NR on a third

Assignees

• Airbus Helicopters

Inventors

• Vallart Jean-Baptiste
• Taheri Setareh
• Certain Nicolas

Classifications

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• B64C27/57 Primary

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

• B64C27/12

  Rotor drives · CPC title

• B64D31/09 Primary

  in response to power plant failure · CPC title

• B64D31/06 Primary

  actuated automatically · CPC title