Method and an arrangement for purposes of determining an incidence of loading of an aircraft structure

• US 20130213141A1
• Filed: 09/27/2011
• Published: 08/22/2013
• Est. Priority Date: 10/26/2010
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Reitmann, Joerg, Meissner, Rene
• Granted Patent: US 9,234,813 B2
• Time in Patent Office: Days
• US Class Current: 73/802
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: G01B 11/16 for measuring the deformation in a solid, e.g. optical strain gauge
• 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: G01M 5/0041 by determining deflection or stress
• CPC Class Codes: G01M 5/0091 by using electromagnetic excitation or detection

Abstract

A method and an arrangement to determine an incidence of loading of an aircraft structure. A true reality of at least one aircraft structural section is superposed with the virtual reality of the aircraft structural section, and any deviation is established by means of a comparison of the two realities; this deviation is evaluated with reference to its consequences in terms of the structural mechanics involved.

Claims

1-9. -9. (canceled)

10. A method for purposes of determining at least one incidence of loading of an aircraft structure comprising the steps:

optically registering at least one section of the aircraft structure for purposes of determining an “

actual”

state of the aircraft structural section,

comparing the “

actual”

state with a stored “

design”

state of the aircraft structural section,

assessing based on structural mechanics whether an overload of at least one part of the aircraft section has occurred.

11. The method in accordance with claim 10, including the step of using a digitised model of the aircraft structural section as the “

design”

state, and compiling a real model on the basis of the registered data as the “

actual”

state.

12. The method in accordance with claim 10, including the step of using an alien acoustic signal that has been determined as a starting point for the assessing step.