Monitoring of a flight control actuator of an aircraft

• US 9,120,581 B2
• Filed: 03/05/2012
• Issued: 09/01/2015
• Est. Priority Date: 03/16/2011
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: De Verbigier, Laurence, Begout, Frank, Andrieu, Laurent, Costes, Regis
• Primary Examiner(s): Nguyen, John Q
• Assistant Examiner(s): WHALEN, MICHAEL F
• Application Number:
  US13/412,199
• Publication Number:
  US 20120239244A1
• Time in Patent Office: 1,275 Days
• Field of Search: 701/29.1, 701/29.4, 701/31.9, 701/32.7, 701/32.9, 701/33.4, 701/34.4
• US Class Current: 1/1
• CPC Class Codes: B64C 13/504 using electro-hydrostatic actuators [EHA's]
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

The invention concerns a system for monitoring a flight control actuator of an aircraft, including:

• • an actuator (1),
  • sensors (3a-3d) in the actuator (1) to collect, during each flight of the aircraft, series of measurements of parameters relative to the said actuator,
  • processing means (5) to calculate a set of damage indicators using, cumulatively, the series of measurements observed during each of the aircraft'"'"'s successive flights, and
  • a memory (7; 7a) to store the said set of damage indicators, where the said memory is integrated in the actuator.

Claims

1. A monitoring system for monitoring a flight control actuator of an aircraft, comprising:

an actuator including;

sensors that collect, during each flight of the aircraft, a series of measurements of parameters relative to said actuator,

memory, physically integrated in said actuator, that stores a set of damage indicators, and

a control module physically integrated in said actuator and connected to said sensors; and

a processor, which is installed on board the aircraft and is external to said actuator, that calculates the set of damage indicators using, cumulatively, the series of measurements collected during each of the aircraft'"'"'s flights,

wherein said control module sends the series of measurements via a communication system of the aircraft to said processor, and

wherein said processor calculates the damage indicators in real time, before sending the damage indicators to said control module, said control module storing the calculated damage indicators from said processor in said memory.

2. The monitoring system according to claim 1, wherein said processor:

calculates current indicators representing a series of current measurements observed in each current flight of the aircraft of the aircraft'"'"'s flights, and

calculates damage indicators for the set of damage indicators by totaling, one-by-one in a corresponding fashion, each of the current indicators with each of the damage indicators, taken during one or more flights previous to each said current flight, and stored in said memory.

3. The monitoring system according to claim 1, wherein said processor analyzes the set of damage indicators to diagnose a state of damage of said actuator.

4. The monitoring system according to claim 1, wherein the set of damage indicators includes at least one indicator of expired estimated service life of said actuator, and said processor compares the at least one indicator of expired estimated service life with a predetermined reference value to determine a remaining estimated service life of said actuator.

5. The monitoring system according to claim 1, wherein the set of damage indicators includes at least one failure indicator indicating a risk of failure of said actuator, and said processor compares the at least one failure indicator with a predefined threshold value to detect a risk of failure.

6. The monitoring system according to claim 1, wherein the set of damage indicators includes at least one indicator from among the following:

a number of flight cycles, a number of flight hours, total displacement, a number of times a limit load has been exceeded, a number of activations, a number of fatigue cycles, and a number of endurance cycles.

7. The monitoring system according to claim 1, wherein the series of measurements collected during each said flight of the aircraft is recorded in a second memory on board the aircraft, different from said memory of said actuator, and said processor calculates the set of damage indicators when the aircraft is not in flight.

8. An aircraft including the monitoring system according to claim 1.

9. The monitoring system according to claim 1, wherein said actuator, with said memory physically integrated therein, is removable from the monitoring system as a single unit.

10. The monitoring system according to claim 1, wherein said sensors include at least one position sensor that senses position of said actuator.

11. The monitoring system according to claim 1, wherein said sensors include at least one thermal sensor that senses a thermal characteristic of said actuator.

12. The monitoring system according to claim 1, wherein said sensors include two or more of at least one position sensor, at least one thermal sensor, and at least one pressure or stress sensor.

13. The monitoring system according to claim 1, wherein only aggregate values of the damage indicators are stored in said memory.

14. A method for monitoring a flight control actuator of an aircraft, the flight control actuator including a plurality of sensors, non-volatile memory and a control module connected to the plurality of sensors and the memory, the method comprising:

collecting, during each flight of the aircraft, a series of measurements of parameters relative to the flight control actuator using the plurality of sensors;

sending the series of measurements via a communication system of the aircraft to a external processor, which is installed on board the aircraft and external to the flight control actuator;

calculating using the external processor a set of damage indicators, using, in cumulative fashion, the series of measurements collected during each of the aircraft'"'"'s flights;

sending the calculated set of damage indicators from the external processor to the non-volatile memory of the flight control actuator; and

recording the set of damage indicators in the non-volatile memory, which is physically integrated in the flight control actuator.

15. A non-transitory computer-readable storage medium storing computer-readable instructions that, when executed by a computer, cause the computer to perform the method according to claim 14.