Method of and apparatus for monitoring the condition of structural components

• US 8,779,943 B2
• Filed: 05/09/2007
• Issued: 07/15/2014
• Est. Priority Date: 07/05/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Entelmann, Wolfgang, Speckmann, Holger, Wlcken, Piet, Bckenheimer, Clemens
• Primary Examiner(s): Bugg, George
• Assistant Examiner(s): Labbees, Edny
• Application Number:
  US12/307,044
• Publication Number:
  US 20090309762A1
• Time in Patent Office: 2,624 Days
• Field of Search: 701/29, 701/30, 701/34, 701/29.1, 701/30.1, 356/35.5, 382/152, 382/149, 382/181, 382/276, 737/60, 340/945
• US Class Current: 340/945
• 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: B64D 47/08 Arrangements of cameras
• CPC Class Codes: G01M 11/081 by using a contact-less detection method, i.e. with a camera
• CPC Class Codes: G01M 5/0016 of aircraft wings or blades
• CPC Class Codes: G01M 5/005 by means of external apparatus, e.g. test benches or portable test systems
• CPC Class Codes: G01M 5/0091 by using electromagnetic excitation or detection

Abstract

The present invention relates to a method of monitoring the condition of structural components, in which an optical sensor in conjunction with a computing unit ascertains image deviations from successive images of the structural components to be monitored, and therefrom ascertains changes in shape of the structure. Robust three-dimensional scanning of the structural components is possible when using two or more sensors. The invention further relates to an apparatus for monitoring the condition of structural components having an optical sensor and an apparatus having two or more sensors. Finally the invention relates to an aircraft in which the methods or apparatuses according to the invention are used.

Claims

1. A method of monitoring the condition of structural components of an aircraft comprising:

producing images of the structural component with at least a first camera and a second camera, the first and second cameras being mutually spaced;

communicating the images to at least one computing unit;

ascertaining the geometry data of a monitored region of the structural component from the images;

ascertaining geometry deviations of discrete regions of the structural component from the comparison of the ascertained geometry data with a reference geometry data set; and

ascertaining changes in shape of the structural component from the geometry deviations by the at least one computing unit,

wherein the size of objectives of the first and second cameras and the spacing of the first and second cameras depend on the size of the monitored region of the structural component to be monitored,

wherein the first camera looks onto a first external pivotable mirror and the second camera looks onto a second external pivotable mirror, wherein each of the first and second external mirrors is pivoted for continuously scanning a surface of the structural component and for enlarging the viewing angle of the first camera and the second camera.

2. The method according to claim 1, wherein the size of the objectives and the spacing of the first and second cameras depend on a desired level of accuracy.

3. The method according to claim 1, wherein, if a smaller region is being monitored, objectives having a larger volume and a smaller spacing between the first and second cameras are selected, wherein, if a larger region is being monitored, objectives having a smaller volume and a larger spacing between the first and second cameras are selected.

4. The method according to claim 1, wherein the first and second cameras operate in the non-visible wavelength range, in particular in the infrared wavelength range.

5. The method according to claim 1, wherein the ascertained change in shape is classified in terms of severity of damage or stresses on the structural component.

6. The method according to claim 5, wherein measures are triggered, in particular an alarm is given, in dependence on the severity of the damage.

7. An apparatus for monitoring the condition of structural components of an aircraft, comprising:

a first camera for producing images of the structural component, the first camera looking onto a first external pivotable mirror, the first external pivotable mirror configured to pivot to continuously scan a surface of the structural component;

a second camera for producing images of the structural component, the second camera looking onto a second external pivotable mirror, the second external pivotable mirror configured to pivot to continuously scan the surface of the structural component and to enlarge the viewing angle of the first camera and the second camera, respectively, the first and second cameras being mutually spaced; and

at least one computing unit,

wherein the computing unit is adapted to receive the images, to ascertain the geometry data of a monitored region of the structural component from the images, to ascertain geometry deviations of discrete regions of the structural component from the comparison of the ascertained geometry data with a reference geometry data set, and to ascertain changes in shape of the structural component from the geometry deviations, wherein the size of objectives of the first and second cameras and the spacing of the first and second cameras depend on the size of the monitored region of the structural component to be monitored.

8. An aircraft, in particular a passenger aircraft, comprising an apparatus for monitoring the condition of structural components of the aircraft according to claim 7.