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Aircraft health state monitoring system based on distributed fiber sensing

A distributed optical fiber and health status technology, which is applied in the field of intelligent sensing, can solve the problems of inability to monitor the health status of the aircraft online and many manual interventions, and achieve the effects of strong anti-electromagnetic interference, sensitive induction, and good stability

Inactive Publication Date: 2017-03-29
BEIJING AUTOMATION CONTROL EQUIP INST
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  • Abstract
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  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved in the present invention is: the existing aircraft health status monitoring system has a lot of manual intervention, and the influence of human factors is relatively large, so it is impossible to realize real-time online monitoring of the aircraft health status

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  • Aircraft health state monitoring system based on distributed fiber sensing
  • Aircraft health state monitoring system based on distributed fiber sensing
  • Aircraft health state monitoring system based on distributed fiber sensing

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Embodiment Construction

[0021] The system for monitoring the health state of an aircraft based on distributed optical fiber sensing of the present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0022] The aircraft health state monitoring system of the present invention adopts the distributed optical fiber sensing technology based on Brillouin scattering, uses optical fibers as sensors and forms an optical fiber network, performs online data collection at the monitoring terminal, and realizes the thermal field and thermal field distribution of the aircraft along the optical fiber network. Full-process information monitoring of health parameters such as force field, and accurate positioning of abnormal events.

[0023] The system composition of the present invention is as follows figure 1 As shown, the system includes: a laser signal source, a first optical coupler, a sensing fiber, a frequency-shift reference optical path modulation module, a...

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Abstract

The invention relates to an aircraft health state monitoring system based on distributed fiber sensing, and belongs to the technical field of intelligent sensing. The health state monitoring system comprises a laser signal source, a first optical coupler, sensing fibers, a frequency-shift reference optical path modulation module, a detection pulse optical path modulation module, a coherent detection module, a circulator and a data processing module. The system solves the problem that the health state of an aircraft cannot be monitored online in real time due to a present aircraft health state monitoring system has too much manual intervention and is influenced by artificial factors greatly; distributed fiber sensing is sensitive to environment change, and the fibers are light, thin, high in anti-electromagnetic interference capability, resistant to corrosion, high in stability, capable of realizing absolute measurement, easy to reuse and capable of being buried in an engineering structure; and the work process of the system needs no artificial intervention, the cost of labor and material cost is reduced, and the thermal field, bearing and other states of the aircraft can be monitored online in real time.

Description

technical field [0001] The invention belongs to the technical field of intelligent sensing, and in particular relates to an aircraft health state monitoring system based on distributed optical fiber sensing. Background technique [0002] The aircraft system has a complex structure, has been in service in harsh environments for a long time, and is subject to the comprehensive action of various loads. Monitoring the health status of aircraft, such as structural damage status and temperature field information, is an important means to avoid sudden catastrophic accidents caused by structural failure of aircraft, reduce maintenance costs, and extend service life. [0003] Traditional aircraft health state detection requires corresponding detection methods for different damage modes, mainly using instruments for non-destructive testing of structures. Conventional non-destructive testing methods include eddy current testing, penetrant testing, X-ray testing, ultrasonic testing, and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01D21/02
Inventor 申争光苑景春董静宇康磊时兆峰
Owner BEIJING AUTOMATION CONTROL EQUIP INST
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