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Assistant method for auxiliary detection of so-called ''hard'' landing of aircraft

An auxiliary detection and aircraft technology, applied in the direction of instruments, electrical testing/monitoring, testing/monitoring control systems, etc., can solve problems such as inaccurate re-recording of stress, and achieve the effects of easy installation, accuracy compatibility, and failure prevention

Active Publication Date: 2014-04-09
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] In fact, either the peaks are taken individually and each peak reflects the condition of a precise part of the aircraft (rather than many parts), or the peaks combine different instant corresponding measurements and therefore cannot accurately re-record a precise Part stress

Method used

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  • Assistant method for auxiliary detection of so-called ''hard'' landing of aircraft
  • Assistant method for auxiliary detection of so-called ''hard'' landing of aircraft
  • Assistant method for auxiliary detection of so-called ''hard'' landing of aircraft

Examples

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Embodiment Construction

[0063] figure 1 Aircraft 10 is shown landing on airport runway 12 . In this example, the path of the aircraft 10 is shown as it undergoes a rebound action and thus has two touch points 14 and 16 in contact with the runway ground before stopping at the end of the runway. The aircraft 10 is in communication with a terminal 18 arranged here at the airport to exchange data.

[0064] Aircraft 10 carries on board a system 20 for implementing the present invention, an embodiment of which is shown in detail in figure 2 . The ultimate purpose of the system 20 is to provide a report which informs the severity of the drop, detailing precisely where required the condition of the different structural elements potentially altered as a result of the drop.

[0065] like figure 2 As shown, the system 20 for determining the severity of a landing includes:

[0066] - multiple sensors 22 i , which are distributed in different parts of the aircraft 10;

[0067] - an information processing...

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PUM

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Abstract

A method for estimating a loading criterion relating to the load experienced by a structural component of an aircraft, and assistance with detecting a so-called “hard” landing. The method includes measuring parameters of the aircraft and calculating at least one loading criterion for the loading of the structural component using at least one neural network receiving the parameters as input. Assistance with detecting a hard landing then includes determining of a time of impact of the aircraft on a landing strip from the measured parameters, then estimating a plurality of the parameters at the determined time of impact so as to calculate the at least one loading criterion relating to the loading of the structural component.

Description

technical field [0001] The invention relates to a method and a system for measuring load criteria followed by structural elements of an aircraft, in particular a civil transport aircraft, an auxiliary method and corresponding auxiliary system for detecting a hard landing of said aircraft, and an aircraft with such a system. Background technique [0002] According to the present invention, it can be understood that the so-called load refers to the entire force borne by the aircraft structure, especially the analyzed element. "Load" in its general sense includes various forces, moments, load factors (or accelerations), structural stresses. [0003] For obvious safety purposes, the aircraft structure should be inspected and possible damage repaired as soon as the aircraft has been subjected to heavy loads, especially in the case of a hard landing (according to the English term "hard landing" commonly used in the field). A hard landing is characterized by a large vertical load ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B23/02
CPCG05B23/0254
Inventor N·拉斯特M·迪歇纳E·雷
Owner AIRBUS OPERATIONS GMBH