Structural health monitoring system for aircraft

A technology of health monitoring system and aeronautical structure, which is applied in the testing, instruments, measuring devices of machine/structural components, etc., can solve the problem of single function of health monitoring system, and achieve the effect of improving integration and overcoming single function.

Inactive Publication Date: 2014-12-03
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Abstract
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Problems solved by technology

[0005] In view of this, the present invention proposes an aircraft structural health monitoring system to integrate multiple structura

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  • Structural health monitoring system for aircraft
  • Structural health monitoring system for aircraft
  • Structural health monitoring system for aircraft

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Embodiment Construction

[0023] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only parts related to the present invention are shown in the drawings but not all content.

[0024] figure 1 It is a structural diagram of an aircraft structural health monitoring system provided by an embodiment of the present invention. see figure 1 , the structural health monitoring system of the aircraft includes: a sensor network 110, a first subsystem 120, a second subsystem 130, a third subsystem 140, a fourth subsystem 150, a fifth subsystem 160 and a sixth subsystem 170 .

[0025] The sensor network 110 is respectively connected to the first subsystem 120, the second subsystem 130, the third subsystem 140,...

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Abstract

The invention discloses a structural health monitoring system for an aircraft. The structural health monitoring system comprises a sensor network for providing sensor signals to each subsystem; a first subsystem for carrying out quantitative monitoring on multiple damage of a large-size aviation structure; a second subsystem for monitoring tiny cracks in a high-stress area of an aviation metal structure and monitoring the damage of delamination, debinding and fibre breakage and the like in the high-stress area of an aviation composite material structure; a third subsystem for carrying out positioning on external bumping of the aviation composite material structure and load reconstruction; a fourth subsystem for carrying out distributed real-time measurement on strain of a key area of the aviation structure and corresponding load reconstruction; a fifth subsystem for carrying out prediction on the service life and residual intensity of the aviation structure; and a sixth subsystem for controlling and coordinating the work of the other subsystems. The structural health monitoring system provided in the embodiment of the invention overcomes the defect that the function of a conventional aircraft structure health monitoring system is single.

Description

technical field [0001] The invention relates to the technical field of structural health monitoring, in particular to an aircraft structural health monitoring system. Background technique [0002] At present, research on structural health monitoring (SHM) for aeronautical structures has become increasingly important. SHM is developed from traditional non-destructive testing technology. This technology uses a network of sensing / actuating elements integrated in the structure to perform real-time online detection of the structural state, which can effectively improve the safety of aeronautical structures, reduce maintenance costs and extend the service period. [0003] SHM technology is included in many research programs of domestic and foreign civil aviation companies. The Boeing Company of the United States has carried out humidity monitoring research on Delta767, and explored the adoption of SHM new technology on the new aircraft B787, conducted special demonstration and re...

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Application Information

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IPC IPC(8): G01M99/00
Inventor 卿新林高丽敏蔡建
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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