METHOD OF ASSISTING DECISION-TAKING CONCERNING THE AIRWORTHINESS OF AN AIRCRAFT

• US 20110178725A1
• Filed: 01/13/2011
• Published: 07/21/2011
• Est. Priority Date: 01/20/2010
• Status: Abandoned Application

• Current Assignee: Airbus
• Original Assignee: Airbus
• Inventors: BUCHHEIT, Catherine
• Application Number:
  US13/005,987
• Publication Number:
  US 20110178725A1
• Time in Patent Office: Days
• US Class Current: 702/35
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: G01M 5/0033 by determining damage, crack or wear
• CPC Class Codes: G01M 5/0083 by measuring variation of impedance, e.g. resistance, capacitance, induction

Abstract

The aircraft includes

• • at least one sensor permanently fastened to the aircraft and suitable, while the aircraft is in use, for providing data relating to at least one instantaneous size of at least one crack; and
  • means suitable for acting as a function of the data to determine information concerning the airworthiness of the aircraft.

Claims

1. An aircraft, including:

at least one sensor permanently fastened to the aircraft and suitable, while the aircraft is in use, for providing data relating to at least one instantaneous size of at least one crack; and

means suitable for acting as a function of the data to determine information concerning the airworthiness of the aircraft.

3. An aircraft according to claim 1, wherein the sensor comprises conductors connected in a parallel configuration, presenting respective impedances that are different from one another and arranged in such a manner that each conductor is suitable for breaking when the size of the crack or one of the cracks crosses a predetermined threshold specific to the conductor, the respective thresholds associated with the conductors differing from one another.

4. An aircraft according to claim 3, wherein the impedances form a geometric series.

5. An aircraft according to claim 1, wherein the sensor is suitable for detecting partial interruption of the fastening of the sensor to the aircraft.

2. An aircraft, including:

at least one sensor permanently fastened to the aircraft and suitable, while the aircraft is in use, for providing data relating to at least one instantaneous size of at least one crack; and

means suitable for transmitting remotely from the aircraft the data from the sensor and/or a result of processing said data.

12. An aircraft according to claim 2, wherein the sensor comprises conductors connected in a parallel configuration, presenting respective impedances that are different from one another and arranged in such a manner that each conductor is suitable for breaking when the size of the crack or one of the cracks crosses a predetermined threshold specific to the conductor, the respective thresholds associated with the conductors differing from one another.

13. An aircraft according to claim 12, wherein the impedances form a geometric series.

14. An aircraft according to claim 2, wherein the sensor is suitable for detecting partial interruption of the fastening of the sensor to the aircraft.

6. An aircraft, including means suitable for:

receiving from a remote transmitter, data relating to at least one instantaneous size of at least one crack of the aircraft; and

acting as a function of the data to determine information about the airworthiness of the aircraft.

7. A method of analyzing the airworthiness of an aircraft, wherein, while the aircraft is in use:

at least one sensor permanently fastened to the aircraft delivers data relating to at least one instantaneous size of at least one crack; and

means acting as a function of the data determine information about the airworthiness of the aircraft.

10. A method according to claim 7, implemented while the aircraft is in flight.

11. A method according to claim 7, implemented while the aircraft is taxiing.

8. A method of analyzing the airworthiness of an aircraft, wherein, while the aircraft is in use:

at least one sensor permanently fastened to the aircraft delivers data relating to at least one instantaneous size of at least one crack; and

means transmit remotely from the aircraft the data from the sensor and/or a result of processing said data.

15. A method according to claim 8, implemented while the aircraft is in flight.

17. A method according to claim 8, implemented while the aircraft is taxiing.

9. A method of analyzing the airworthiness of an aircraft, wherein, while the aircraft is in use, means:

receive from a remote transmitter, data relating to at least one instantaneous size of at least one crack of the aircraft; and

act as a function of the data to determine information about the airworthiness of the aircraft.

16. A method according to claim 9, implemented while the aircraft is in flight.

18. A method according to claim 9, implemented while the aircraft is taxiing.