Method for determining a state of a component in a high lift system of an aircraft

• US 9,701,419 B2
• Filed: 12/21/2015
• Issued: 07/11/2017
• Est. Priority Date: 12/22/2014
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Van Bruggen, Jan-Arend, Neb, Eugen, Brady, Michael, Hartwig, Wolfgang, Criou, Olivier, Latzel, Stefan, Heintjes, Mark
• Primary Examiner(s): Kiswanto, Nicholas
• Assistant Examiner(s): Taveras, Kenny A
• Application Number:
  US14/977,125
• Publication Number:
  US 20160176539A1
• Time in Patent Office: 568 Days
• Field of Search: None
• CPC Class Codes: B64C 13/341 having duplication or stand-by provisions
• CPC Class Codes: B64C 9/16 at the rear of the wing
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear

Abstract

A method for determining a state of a component in a high lift system of an aircraft comprises the steps of extending at least one high lift surface, which is coupled with two drive struts, wherein at least one of the two drive struts is a load sensing drive strut, to a first extended position, acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

Claims

1. A method for determining a state of a component in a high lift system of an aircraft, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft;

drive stations coupled with the power control unit;

movable high lift surfaces; and

a control unit, wherein each high lift surface is coupled with at least two of the drive stations by means of drive struts, wherein at each high lift surface at least one of the associated drive struts is a load sensing drive strut;

the method comprising the steps of;

extending at least one high lift surface to a first extended position,

acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed,

comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and

producing an alarm signal of the acquired load differs from the nominal load including the predetermined threshold.

2. The method of claim 1, further comprising

acquiring a second load sensed by a load sensing drive strut associated with the at least one high lift surface at a second extended position at a second flight state of the aircraft having a second speed, which is lower than the first flight speed, and

adjusting the value of the first load through subtracting the value of the second load, before comparing the first load with a known nominal load for the first extended position.

3. The method of claim 2, wherein the second extended position is substantially equal to the first extended position.

4. The method of claim 2, wherein in the second flight state the aircraft has touched the ground.

5. The method of claim 2, wherein the second speed is less than 60 knots.

6. The method of claim 5, wherein a set of loads is continuously acquired until a retraction of the high lift surfaces is initiated, wherein the second load is the minimum acquired load of the set of loads.

7. The method of claim 1, wherein the alarm signal includes an indication that the drive station, to which the load sensing drive strut is coupled, is disconnected, when the acquired load is below the nominal load under consideration of a first predetermined threshold.

8. The method of claim 1, wherein the alarm signal includes an indication that a neighboring drive station from the drive station, to which the load sensing drive strut is coupled, is disconnected, when the acquired load is above the nominal load under consideration of a second predetermined threshold.

9. The method of claim 1, further comprising a previous step of collecting a set of acquired loads during flight with at least one set of flight parameters with high lift surfaces in at least one extended position and storing the set of acquired loads correlated with the at least one set of flight parameters as known nominal loads.

10. A high lift system of an aircraft, comprising:

a central power control unit for providing rotational power;

a transmission shaft;

drive stations coupled with the power control unit by means of the transmission shaft;

movable high lift surfaces; and

a control unit,

wherein each high lift surface is coupled with at least two of the drive stations by means of drive struts,

wherein at each high lift surface at least one of the associated drive struts is a load sensing drive strut,

wherein the control unit is adapted for acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed at a first extended position, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

11. The high lift system of claim 10,

the control unit further comprising a memory,

wherein the control unit is adapted for storing known nominal loads associated with a plurality of flight states in the memory.

12. The high lift system of claim 10,

wherein the control unit is adapted for retrieving known nominal loads.

13. An aircraft, comprising a wing and a high lift system of claim 10.

14. A method for determining a state of a component in a high lift system of an aircraft, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft;

drive stations coupled with the power control unit;

movable high lift surfaces; and

a control unit, wherein each high lift surface is coupled with at least two of the drive stations by means of drive struts, wherein at each high lift surface at least one of the associated drive struts is a load sensing drive strut;

the method comprising the steps of;

extending at least one high lift surface to a first extended position,

acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed,

comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and

producing an alarm signal of the acquired load differs from the nominal load including the predetermined threshold,

acquiring a second load sensed by a load sensing drive strut associated with the at least one high lift surface at a second extended position at a second flight state of the aircraft having a second speed, which is lower than the first flight speed,

adjusting the value of the first load through subtracting the value of the second load, before comparing the first load with a known nominal load for the first extended position,

wherein the second extended position is substantially equal to the first extended position.

15. The method of claim 14, wherein in the second flight state the aircraft has touched the ground, and

the second speed is less than 60 knots.

16. The method of claim 15,

wherein a set of loads is continuously acquired until a retraction of the high lift surfaces is initiated, wherein the second load is the minimum acquired load of the set of loads, and

wherein the alarm signal includes an indication that the drive station, to which the load sensing drive strut is coupled, is disconnected, when the acquired load is below the nominal load under consideration of a first predetermined threshold.