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Method for detecting a break in an aircraft lift system

An aircraft and system area technology, applied in instruments, measuring devices, aircraft parts, etc., to solve problems such as large tolerances or errors, erroneous fracture detection results, and inability to design monitors.

Active Publication Date: 2022-07-05
LIEBHERR AEROSPACE LINDENBERG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] A disadvantage of these known methods in the prior art is that the detected sensor information cannot be shared with other functions (e.g. load limitation) when taking position measurements
[0009] Also, it is impossible to design a robust monitor due to large tolerances or errors in the system, resulting in false fracture detection results and unnecessary maintenance measures

Method used

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  • Method for detecting a break in an aircraft lift system
  • Method for detecting a break in an aircraft lift system

Examples

Experimental program
Comparison scheme
Effect test

example 3

[0062] Example 3 with the following load values: R=│L1_r│ / (│L1_1│+│L2_1│), where: r-right; l-left

example 4

[0063] Example 4 with the following load values: R=(│L1_r│+│L2_r│) / (│L1_1│+│L2_1│), where: r-right; 1-left

[0064] Among them, two-level limit values ​​can be used for better fault isolation. The following events can be inferred from the different ratios (R):

[0065] RThere is a break in the right load path L1

[0066] Low_THR2

[0067] Low_THR1No fault status

[0068] Up_THR1There is a break in the left load path L2

[0069] Up_THR2 There is a fracture in the left load path L1

[0070] Accordingly, the reference numbers L1 and L2 may refer to load paths and load values ​​detected in the respective load paths.

[0071] Break detection in the load path can be implemented redundantly by means of several monitors or monitoring methods / monitoring devices accessing different load information. The results of these monitors can be combined by an AND operation or an OR operation.

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Abstract

The present invention relates to a method of detecting a break in a high-lift system of an aircraft, in particular an aircraft, taking into account the load values ​​in the area of ​​said high-lift system.

Description

technical field [0001] The present invention relates to a method for detecting a disconnection in a high-lift system of an aircraft, in particular an aircraft, taking into account the load values ​​in the area of ​​said high-lift system. Background technique [0002] The same type of method is used to monitor a high-lift system with a central drive system. Such lift systems are currently used in all common single-aisle long-range aircraft. Therein, the central drive unit of the high-lift system is connected with the corresponding drive station of each segment of the landing flap system or slat system along the entire wingspan by means of a hinge system. [0003] The invention is used to detect fractures in structural-side single segments of drive stations, kinematic systems (Kinematik) and / or high-lift systems. In the event of such a rupture, the intact load path of the at least two load paths originally provided for the single segment has to bear the full air load alone. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00B64F5/60
CPCB64C13/24B64F5/60G01M13/00B64C13/00G01M5/0016G01M5/0033
Inventor 拉斐尔·拉德纳克里斯汀·科洛菲尔伯德·希维布希
Owner LIEBHERR AEROSPACE LINDENBERG