Method of controlling aerodynamic means of an aircraft, an associated control system, and an aircraft provided with such a control system

Patent metadata

Field	Value
Publication number	US-10589844-B2
Application number	US-201615180651-A
Country	US
Kind code	B2
Filing date	Jun 13, 2016
Priority date	Jun 30, 2015
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

A control method for controlling aerodynamic means of an aircraft having mechanically decoupled flight controls enabling the aircraft to be piloted by at least two pilots. The aircraft has at least two control members operated by respective ones of the at least two pilots and each enabling control signals to be generated for causing the aerodynamic means to move relative to an incident air stream. The control method includes piloting logic (“operational” logic). The operational logic includes a dual operating mode in which each control member can control the aerodynamic means. In the dual operating mode, only one of the at least two control members, (the “activated” member), has exclusive control over a full travel amplitude of the aerodynamic means. The other control member, (the “deactivated” member), then is temporarily inoperative on the aerodynamic means.

First claim

What is claimed is:

1. A control method for controlling aerodynamic means of an aircraft having mechanically decoupled flight control members enabling the aircraft to be piloted by at least two pilots, the aircraft having a first control member on a left side of a cockpit of the aircraft for being operated by a first pilot who is in charge of the first control member and a second control member on a right side of the cockpit of the aircraft for being operated by a second pilot who is in charge of the second control member and each control member enabling control signals to be generated for causing the aerodynamic means to move relative to an incident air stream, the control method using piloting logic referred to as “operational” logic, the operational logic including a dual operating mode, a left single-pilot operating mode, and a right single-pilot operating mode, the aircraft further including a single switch movable between three stable positions including a first position corresponding to the dual operating mode, a second position corresponding to the right single-pilot operating mode, and a third position corresponding to the left single-pilot operating mode, each of the positions of the single switch being reversibly-reachable for manual selection by at least one of the pilots of the dual operating mode in the first position of the single switch, the left single-pilot operating mode in the second position of the single switch, or the right single-pilot operating mode in the third position of the single switch;
wherein in the dual operating mode,
only one of the control members, referred to as the “activated” member, has exclusive control over a full travel amplitude of the aerodynamic means, the other of the control members, referred to as the “deactivated” member, then being temporarily inoperative on the aerodynamic means;
it is possible to manually activate the deactivated member, thereby automatically deactivating the activated member responsive to the deactivated member being activated, the deactivated member being activated becoming the activated member having exclusive control over the full travel amplitude of the aerodynamic means; and
the manual activation of the deactivated member is performed by other means distinct from the single switch;

wherein in the left single-pilot operating mode,
only the first control member, referred to as the “activated” member, has exclusive control over the full travel amplitude of the aerodynamic means, the second control member, referred to as the “deactivated” member, then being inoperative on the aerodynamic means; and
the first control member always remains activated and the second control member always remains deactivated;

wherein in the right single-pilot operating mode,
only the second control member, referred to as the “activated” member, has exclusive control over the full travel amplitude of the aerodynamic means, the first control member, referred to as the “deactivated” member, then being inoperative on the aerodynamic means; and
the second control member always remains activated and the first control member always remains deactivated.

2. The control method according to claim 1 , wherein the manual activation of the deactivated member being activated is performed by the pilot in charge of the deactivated member being activated by pressing an activation button.

3. The control method according to claim 1 , wherein the manual activation of the deactivated member being activated is performed by the pilot in charge of the deactivated member being activated by moving the deactivated member.

4. The control method according to claim 1 , wherein the deactivated member is held in position by a holding force.

5. The control method according to claim 4 , wherein the deactivated member is held in position in a central position, referred to as a “neutral” position, corresponding to the middle of the full movement stroke of the deactivated member while it is activated.

6. The control method according to claim 4 , wherein the holding force is greater than a threshold value and serves to prevent any manual actuation of the deactivated member by the pilot in charge of the deactivated member.

7. The control method according to claim 4 , wherein the holding force is less than a threshold value and is suitable for being overcome by the pilot in charge of the deactivated member actuating the deactivated member manually.

8. The control method according to claim 7 , wherein the manual activation of the deactivated member being activated is performed by the pilot in charge of the deactivated member being activated by moving the deactivated member being activated, and wherein overcoming the holding force of the deactivated member being activated causes the deactivated member being activated to be manually activated as a result of the movement of the deactivated member being activated.

9. The control method according to claim 1 , wherein each new manual activation of a newly activated but initially deactivated member causes reactivation of a newly deactivated but initially activated member to be prohibited, at least for a predetermined duration.

10. The control method according to claim 9 , wherein one of the pilots of the aircraft may select to prohibit reactivation of a newly deactivated but initially activated member, at least for a predetermined duration, by means of a first selector element that is operable solely by the one of the pilots.

11. The control method according to claim 1 , wherein the control method includes another piloting logic, referred to as “training” logic, which, when activated by a second selector element, deactivates the operational logic, and wherein, in the training logic, the control members are activated simultaneously for controlling the total travel amplitude of the aerodynamic means by summing.

12. A control system for controlling aerodynamic means of an aircraft having mechanically decoupled flight control members enabling the aircraft to be piloted by at least two pilots, the control system including a first control member on a left side of a cockpit of the aircraft for being operated by a first pilot and a second control member on a right side of the cockpit of the aircraft for being operated by a second pilot and each control member enabling control signals to be generated, the control signals being transmitted to a processor unit of the control system to generate control setpoints for at least one actuator that moves the aerodynamic means relative to an incident air stream, wherein the control system performs a control method according to claim 1 .

13. An aircraft having mechanically decoupled flight control members and a control system for controlling aerodynamic means and enabling the aircraft to be piloted by at least two pilots, the control system having a first control member on a left side of a cockpit of the aircraft for being operated by a first pilot and a second control member on a right side of the cockpit of the aircraft for being operated by a second pilot and each control member enabling a control signal to be generated, the control signals being transmitted to a processor unit of the control system to generate control setpoints for at least one actuator that moves the aerodynamic means relative to an incident air stream, wherein the control system is selected in accordance with a control system according to claim 12 .

14. The aircraft according to claim 13 , wherein the aircraft includes data link means for receiving at least control setpoints from an additional control member outside the aircraft, the additional control member enabling one of the control m

Assignees

• Airbus Helicopters

Inventors

• Ott Adrien
• Byzery Romeo
• Vallart Jean-Baptiste

Classifications

• B64C13/507

  with artificial feel · CPC title

• B64C13/506

  overriding of personal controls; with automatic return to inoperative position · CPC title

• B64C13/505

  having duplication or stand-by provisions · CPC title

• B64C13/12 Primary

  Dual control apparatus · CPC title

• B64C13/0421 Primary

  control sticks for primary flight controls · CPC title