In-orbit ultra-long service life prediction method for fiber grating strain sensor for satellite

A strain sensor, fiber grating technology, applied in the direction of using optical devices, instruments, measurement devices, etc., can solve the problem of inability to accurately evaluate the service life of the measurement system, and achieve strong practicability, operability, and short experiment time. Effect

Active Publication Date: 2019-08-23
SHANDONG INST OF AEROSPACE ELECTRONICS TECH
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Problems solved by technology

[0005] The reason why a single fiber grating sensor is not used as the research object is that the strain transfer effect of the adhesive will be introduced after the system is composed, which will bring new effects, and the use of the measurement system cannot be accurately evaluated only by the change of the optical characteristics of the fiber grating sensor itself life

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  • In-orbit ultra-long service life prediction method for fiber grating strain sensor for satellite
  • In-orbit ultra-long service life prediction method for fiber grating strain sensor for satellite
  • In-orbit ultra-long service life prediction method for fiber grating strain sensor for satellite

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Embodiment Construction

[0048] Such as figure 1 As shown, an on-orbit ultra-long life prediction method of a fiber grating strain sensor for satellites mainly includes building a strain test system for a fiber grating strain sensor. At least three sets of strain test systems are used. The temperature of the incubator is different, and the temperature of the incubator is higher than the actual working environment temperature of the optical fiber strain sensor, and the experiment is carried out synchronously; the wavelength measurement value of the strain sensor is monitored λ im Change with time, converted to strain change Δλ im Change with time, and further obtain the change of the percentage of strain change with time; through percentage fitting, the performance change constant β at three temperatures is obtained; the relationship between the performance change constant and temperature is obtained by fitting, and β and 1 / T satisfy the negative exponent relationship, the actual working temperature T...

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Abstract

The invention relates to an on-orbit ultra-long service life prediction method for a fiber grating strain sensor for a satellite. The method comprises the steps that a measurement system serves as a research object, a final physical quantity to be measured serves as an evaluation object, performance degradation curves of the whole sensing measurement system at three different temperatures are researched, numerical fitting is carried out, and the service life of the fiber grating strain sensing system at a certain temperature is further obtained through extrapolation. The method has the advantages that on the premise that reliable life prediction is guaranteed, the influence of process factors is avoided, operability is high, accuracy is high, and certain reference significance is achievedfor life speculation of the on-board fiber grating strain sensor and devices with similar ultra-long life requirements.

Description

technical field [0001] The invention belongs to the technical field of optical fiber sensing, and in particular relates to an on-orbit ultra-long service life prediction method of an optical fiber grating strain sensor used for satellites. Background technique [0002] For spacecraft such as long-lived satellites and space stations, they often work in orbit for a long time, and the design of their cabins and sensors for cabin monitoring have long-life requirements. For example, the space station has a design life of more than 15 years, so the fiber grating sensor for monitoring physical quantities such as strain on its cabin also needs a service life of more than 15 years. [0003] Fiber Bragg grating strain sensors are generally pasted on the spacecraft cabin with adhesives, which can avoid damage to the cabin structure by welding, screw mounting and other installation methods. The deformation of the cabin is sequentially passed through the adhesive, sensor substrate, glass...

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Application Information

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IPC IPC(8): G06F17/50G01B11/16
CPCG01B11/165G06F2119/04G06F2119/12G06F30/20
Inventor 罗玉祥申景诗张永伟吕宏彬张建德王翀
Owner SHANDONG INST OF AEROSPACE ELECTRONICS TECH
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