Device for monitoring the integrity and soundness of a mechanical structure, and method for operating such a device

• US 9,418,039 B2
• Filed: 01/31/2012
• Issued: 08/16/2016
• Est. Priority Date: 01/31/2011
• Status: Active Grant

• Current Assignee: Airbus Group SAS (Airbus SE)
• Original Assignee: Airbus Group SAS (Airbus SE), Eurocopter
• Inventors: Foucher, Bruno, Rouet, Vincent, Reynet, Remy
• Primary Examiner(s): Bugg, George
• Assistant Examiner(s): Akki, Munear
• Application Number:
  US13/982,426
• Publication Number:
  US 20130307703A1
• Time in Patent Office: 1,659 Days
• Field of Search: 340/870.3, 340/693.2, 340/945, 340/686.1, 340/13.26, 73/290.2, 734/88, 735/84, 737/00
• US Class Current: 1/1
• CPC Class Codes: G01M 5/00 Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings G01M9/00 takes precedence
• CPC Class Codes: G01N 37/00 Details not covered by any other group of this subclass
• CPC Class Codes: G06F 15/0275 for measuring
• CPC Class Codes: G07C 5/008 communicating information to a remotely located station transmission systems for measured values G08C
• CPC Class Codes: G07C 5/085 using electronic data carriers

Abstract

The invention relates to a device for monitoring the integrity and soundness of a mechanical structure, such as an aircraft. The device comprises a control unit, a radio frequency transmission means, and an electric battery. The control unit recovers data from a set of digital and/or analog sensors. The radio frequency transmission means enables the control unit to transmit the data received from the sensors to a man/machine interface. The electric battery powers the device and is rechargeable. The device further comprises a module for recovering electromagnetic energy capable of converting the recovered electromagnetic energy into electric power so as to recharge the battery and/or directly power the device.

Claims

1. A device for monitoring integrity and soundness of a mechanical structure of an aircraft, comprising:

a control unit to collect data from a set of digital or analog sensors to monitor integrity and soundness of the mechanical structure of the aircraft, the sensors are active during a flight of the aircraft and on standby for the aircraft on the ground;

a radio frequency transmitter for the control unit to transmit data received from the sensors to a human/machine interface;

a rechargeable accumulator to supply electrical energy to the device; and

an electromagnetic energy salvage unit to transform surrounding electromagnetic waves of the aircraft in flight into electrical energy to recharge the accumulator or directly supply the electrical energy to the device in response to a determination that the sensors are active, the electromagnetic energy salvage unit is on standby in response to a determination that the sensors are on standby.

2. The device of claim 1, further comprising an outside energy salvage unit configured to supply electrical energy to the device to ensure its energizing autonomy.

3. The device of claim 2, wherein the outside energy salvage unit is configured to convert into electrical energy from at least one of the following:

mechanical energy, solar energy or calorific energy.

4. The device of claim 1, wherein the radio frequency transmitter is an RFID chip.

5. The device of claim 1, wherein the set of sensors comprises at least one of the following:

a temperature sensor, a humidity sensor, a pressure sensor, an accelerometer, a distortion sensor, or an ultrasound sensor.

6. The device of claim 1, wherein the control unit, the radio frequency transmitter and the accumulator are configured to be housed in a case having dimensions equal to a credit card.

7. The device of claim 6, wherein the case has a length of 85 mm and a width of 55 mm.

8. The device of claim 6, wherein the case is integrated in a penultimate composite material layer of an object of the structure of the aircraft.

10. A method of operating a device of claim 1 for monitoring and soundness of the mechanical structure, comprising the steps of:

salvaging outside energy to supply the device with the electrical energy;

detecting signals from the set of sensors during a flight of the aircraft; and

recording signal data during a period where at least one of the signals is higher than a predetermined limit, the signal data recording preceding and succeeding the period by one to two seconds.

11. The method of claim 10, further comprising the step of salvaging outside mechanical energy to supply the device with the electrical energy.

9. The device of 6, wherein the case is bonded to a surface of an object of the structure of the aircraft.