Method and device for controlling at least one actuator control system of an aircraft, associated computer program product and aircraft

Patent metadata

Field	Value
Publication number	US-9856032-B2
Application number	US-201514729509-A
Country	US
Kind code	B2
Filing date	Jun 3, 2015
Priority date	Jun 16, 2014
Publication date	Jan 2, 2018
Grant date	Jan 2, 2018

Abstract

A method and device for controlling at least one actuator control system of an aircraft, an associated computer program product and aircraft are disclosed. In one aspect, the method includes determining a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, calculating a first control command signal to be sent to an engine control system in order to obtain the variation in thrust, and transmitting the first control command signal to the engine control system. The controlled variable can be an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector and the set point can be an acceleration set point along the direction.

First claim

What is claimed is:

1. A method for controlling at least one actuator control system of an aircraft configured to act on a force applied to the aircraft, the aircraft having an air speed vector and a ground speed vector, the aircraft having at least one engine and an engine control system configured to cause the varying of a thrust force generated by the engine or engines, the engine control system forming a first actuator control system, the method being implemented by an electronic control device and comprising:
determining, during flight of the aircraft, a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, the variation in thrust being determined so as to modify the controlled variable to approach the set point;
calculating, during the flight of the aircraft, a first control command signal to be sent to the engine control system in order to obtain the variation in thrust; and
transmitting, during the flight of the aircraft, the first control command signal to the engine control system,
wherein the controlled variable is an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector, and
wherein the set point is an acceleration set point along the direction.

2. The method of claim 1 , wherein the controlled variable is an acceleration along the direction taken by the air speed vector.

3. The method of claim 1 , wherein the aircraft further includes an aerodynamic brake control system configured to act on a drag force on the aircraft, the aerodynamic brake control system forming a second actuator control system, and wherein the method further comprises:
determining a variation in drag of the aircraft for controlling the variable relating to the aircraft relative to the set point;
calculating a second control command signal to be sent to the aerodynamic brake control system in order to obtain the variation in drag; and
transmitting the second control command signal to the aerodynamic brake control system.

4. The method of claim 1 , wherein the aircraft further comprises wheels and a control system among a ground traction control system and a ground brake control system configured to act on at least one force among a tractive force and a braking force exerted on the ground by the wheels, the ground traction control system forming a third actuator control system and the ground brake control system forming a fourth actuator control system, wherein the method further comprises:
determining a variation in acceleration of the aircraft on the ground for controlling the variable relating to the aircraft relative to the set point;
calculating at least one ground control command signal among a third control command signal to be sent to the ground traction control system and a fourth control command signal to be sent to the ground brake control system in order to obtain the variation in ground acceleration; and
transmitting each ground control command signal to the corresponding control system.

5. The method of claim 1 , wherein the determined variation is a function of an estimated value of the controlled variable, and wherein the estimated value of the controlled variable depends on at least one value among an estimated time derivative of a measured air speed and an estimated acceleration along the direction taken by a speed vector selected from the air speed vector and the ground speed vector.

6. The method of claim 1 , wherein the aircraft further comprises a control lever, and wherein the method further comprises:
measuring a mechanical variable value relative to the control lever; and
calculating an acceleration set point value as a function of the measured mechanical variable value.

7. The method of claim 6 , wherein the value of the set point acceleration is calculated in an iterative manner as a function of the measured mechanical variable value and a previous value of the acceleration set point.

8. The method of claim 1 , wherein the aircraft further comprises a control lever, the control lever including at least one predetermined reference position, and wherein, when the control lever is positioned in a corresponding predetermined reference position, the value of the acceleration set point is equal to a predefined value associated with the predetermined reference position.

9. The method of claim 1 , wherein the aircraft further comprises an avionics system configured to generate the acceleration set point, and wherein the value of the acceleration set point is received from the avionics system.

10. The method of claim 1 , wherein the aircraft further comprises a display screen, and wherein the method further comprises displaying, on the screen, the value of the acceleration set point.

11. The method of claim 10 , wherein the displaying the value of the acceleration set point comprises displaying a reference symbol and an acceleration on slope set point symbol, the algebraic deviation on the ordinate between the reference symbol and the acceleration on slope set point symbol representing the value of the acceleration set point.

12. A non-transitory computer readable medium including a computer program comprising of software instructions that, when carried out by a computer, implement the method according to claim 1 .

13. An electronic control device for controlling at least one actuator control system of an aircraft for acting on a force applied to the aircraft, the aircraft having an air speed vector and a ground speed vector, the aircraft comprising at least one engine and an engine control system configured to cause the varying of a thrust force generated by the engine or engines, with the engine control system forming a first actuator control system, the control device comprising:
a determination capability configured to determine, during flight of the aircraft, a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, the variation in thrust being determined so as to modify the controlled variable to approach the set point;
a calculation and transmission capability configured to: i) calculate, during the flight of the aircraft, a first control command signal to be sent to the engine control system in order to obtain the variation in thrust, and ii) transmit, during the flight of the aircraft, the first control command signal to the engine control system,
wherein the controlled variable is an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector, and
wherein the set point is an acceleration set point along the direction.

14. The electronic control device of claim 13 , wherein the aircraft further comprises an aerodynamic brake control system configured to act on a drag force on the aircraft, with the aerodynamic brake control system forming a second actuator control system,
wherein the determination capability is further configured to determine a variation in drag of the aircraft for controlling the variable relating to the aircraft relative to the set point, and
wherein the device further comprises a calculation and transmission capability configured to: i) calculate a second control command signal to be sent to the aerodynamic brake control system in order to obtain the variation in drag, and ii) transmit the second control command signal to the aerodynamic brake control system.

15. The electronic control device of claim 13 , wherein the aircraft further comprises wheels and a control system among a ground traction control system and a ground brake control system configured to a

Assignees

• Thales Sa

Inventors

• Lissajoux Sylvain
• Claybrough Matthieu
• Garnavault Christophe

Classifications

• B64D31/06 Primary

  actuated automatically · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64C25/44

  Actuating mechanisms · CPC title

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title