System for controlling a rotorcraft rotor, a rotorcraft fitted with such a system, and an associated control method

Patent metadata

Field	Value
Publication number	US-9963225-B2
Application number	US-201615096366-A
Country	US
Kind code	B2
Filing date	Apr 12, 2016
Priority date	Apr 13, 2015
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

A control system for controlling a rotorcraft rotor, to a rotorcraft fitted therewith, and to a corresponding control method. The system comprises selector means for defining at least two disjoint position ranges for the control member between two physical abutments corresponding to the movement limits of the control member, a first position range being defined between at least two first limit values about a zero force position of the control member, and at least one second position range being defined between at least one of the at least two first limit values and at least one second limit value; and control means for allocating a first control law to the first position range of the control member and a second control law to the second position range of the control member, the first and second control laws being selected to be mutually distinct.

First claim

What is claimed is:

1. A control system for controlling a rotorcraft rotor, the control system comprising at least one control member for use in piloting the rotor,
the control system further comprising:
selector means for defining at least two disjoint position ranges and for the control member between two physical abutments corresponding to the movement limits of the control member,
a first position range being defined between at least two first limit values about a zero force position of the control member, and
at least one second position range being defined between at least one of the at least two first limit values and at least one second limit value; and

control means for allocating a first control law to the first position range of the control member and a second control law to the second position range of the control member, the first and second control laws being selected to be mutually distinct.

2. A control system according to claim 1 , wherein the control system includes monitor means allowing to identify a landed state of the rotorcraft on a support.

3. A control system according to claim 1 , wherein the first control law is of the type that is linear in position, each position of the control member in the first position range corresponding to a position of a plane of the rotor.

4. A control system according to claim 1 , wherein the second control law is of the type that is linear in speed, each position of the control member in the second position range corresponding to a speed of tilt of a plane of the rotor.

5. A control system according to claim 1 , wherein the at least one second limit value coincides with one of the two physical abutments of the control member.

6. A control system according to claim 1 , wherein the second position range of the control member comprises two range portions, each of the two range portions being defined between one of the at least two first limit values of the first range and one of the at least one second limit values, the two second portions of the second position range being arranged on respective sides of the first position range of the control member.

7. A control system according to claim 1 , wherein the control system includes adjustment means suitable for modifying a reference position of a plane of the rotor relative to a drive plane, the reference position corresponding to an angle of inclination of the rotor when the control member is in the zero force position.

8. A control system according to claim 1 , wherein the control member includes a projection of length less than 30 cm between a free end of the projection and a hinge giving the projection at least one degree of freedom to move in rotation relative to a stand.

9. A control system according to claim 8 , wherein the hinge imparts two degrees of freedom to the projection to move in rotation relative to the stand, and wherein the at least two disjoint position ranges and described by the projection are in the form of cones with different angles, the at least two first limit values forming an angle of a first cone forming the first range and the at least one second limit value forming an exterior angle of a hollow second cone forming the second range.

10. A rotorcraft, including at least one control system according to claim 1 .

11. A method of controlling a rotorcraft rotor by means of a control member, wherein the method comprises the steps of:
defining at least two distinct position ranges and of the control member, a first position range being defined between at least two first limit values about a zero force position of the control member, and at least one second position range being defined between at least one of the at least two first limit values and at least one second limit value; and
allocating a first control law to the first position range of the control member and a second control law to the second position range of the control member, the first and second control laws being selected to be mutually distinct.

12. A method according to claim 11 , wherein the method includes a step of identifying a landed state of the rotorcraft on a support.

13. A method according to claim 11 , wherein the first control law being of the type that is linear in position, with each position of the control member in the first position range corresponds to a position of a plane of the rotor.

14. A method according to claim 11 , wherein the second control law being of the type that is linear in speed, with each position of the control member in the second position range corresponds to a speed of tilting a plane of the rotor.

15. A method according to claim 11 , wherein at least one second limit value is selected in such a manner that it coincides with a physical abutment of the control member.

16. A method according to claim 11 , wherein two second limit values are defined for the second position range of the control member, and wherein the second position range of the control member is formed by two range portions, the two range portions being arranged on respective sides of the first position range of the control member.

Assignees

• Airbus Helicopters

Inventors

• Vallart Jean-Baptiste
• Byzery Romeo

Classifications

• B64C27/56 Primary

  characterised by the control initiating means, e.g. manually actuated · CPC title

• B64C13/0421

  control sticks for primary flight controls · CPC title

• B64C13/044

  operated by feet, e.g. pedals · CPC title

• B64C13/0427

  for actuating trim · CPC title

• B64C27/58

  Transmitting means, e.g. interrelated with initiating means or means acting on blades (means acting on blades B64C27/72) · CPC title