Method of operating actuators simultaneously for moving aircraft flaps, an aircraft flap drive device, and an aircraft provided with such a device

• US 9,114,872 B2
• Filed: 02/29/2012
• Issued: 08/25/2015
• Est. Priority Date: 03/01/2011
• Status: Active Grant

• Current Assignee: Safran Electronics & Defense
• Original Assignee: Sagem Defense Securite SA (Safran SA)
• Inventors: Marques, Frederic, Mercier, Guillaume, Menio, Stephane
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Rodziwicz, Aaron
• Application Number:
  US14/002,062
• Publication Number:
  US 20130334372A1
• Time in Patent Office: 1,273 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00

Abstract

A method of operating actuators simultaneously for moving at least two aircraft movable aerodynamic surfaces, the method comprising the steps of: controlling the actuators to move the aerodynamic surfaces towards a predetermined position; during the movement, detecting a slowest actuator; and adapting the control of the actuators to match the actions of the slowest actuator. A drive device for aerodynamic surfaces and an aircraft including such a device.

Claims

1. A method of operating actuators simultaneously for moving at least two aircraft movable aerodynamic surfaces, the method comprising the steps of:

controlling the actuators to move the aerodynamic surfaces towards a predetermined position;

during the movement, detecting a slowest actuator; and

adapting the control of the actuators to match the actions of the slowest actuator.

2. A method according to claim 1, wherein, when an actuator reaches the predetermined position, that actuator is stopped and the actuator is braked to hold it in the predetermined position.

3. A method according to claim 1, wherein each actuator comprises an electric motor and the method comprises a stage of detecting a failure from a combination of at least some of the following parameters:

aerodynamic surface position;

motor position;

motor power supply current;

actuator load.

4. A method according to claim 3, wherein each actuator includes a brake, and the parameters used during the failure detection mode also include the braking torque.

5. A method according to claim 3, wherein, in the event of detecting a failure of at least one of the actuators, all of the actuators are stopped.

6. A method according to claim 3, for controlling at least four aerodynamic surfaces distributed on both wings of the aircraft, wherein, in the event of detecting a failure of at least one of the actuators of one of the aerodynamic surfaces on one of the wings, the actuators of that aerodynamic surface are stopped as are the actuators of the corresponding aerodynamic surface situated on the other wing.

7. A method according to claim 6, wherein the actuators of the other wings are controlled to move.

8. A method according to claim 1, wherein the slowest actuator is detected by comparing the positions of the actuators at a given instant.

9. A device for driving aircraft flaps, the device comprising actuators for moving the aerodynamic surfaces and a control unit that is connected to the actuators and to actuator position sensors and that is programmed to bring the actuators into predetermined positions and to implement the method according to claim 1.

10. An aircraft comprising a fuselage and two aerodynamic surfaces disposed on either side of the fuselage and coupled to a drive device, wherein the drive device is according to the preceding claim.