CN108398144A - Aerospace fiber grating sensing system and method - Google Patents
Aerospace fiber grating sensing system and method Download PDFInfo
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- CN108398144A CN108398144A CN201711420701.0A CN201711420701A CN108398144A CN 108398144 A CN108398144 A CN 108398144A CN 201711420701 A CN201711420701 A CN 201711420701A CN 108398144 A CN108398144 A CN 108398144A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
- G01D5/26—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light
- G01D5/32—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light
- G01D5/34—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells
- G01D5/36—Forming the light into pulses
- G01D5/38—Forming the light into pulses by diffraction gratings
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D18/00—Testing or calibrating apparatus or arrangements provided for in groups G01D1/00 - G01D15/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D3/00—Indicating or recording apparatus with provision for the special purposes referred to in the subgroups
- G01D3/028—Indicating or recording apparatus with provision for the special purposes referred to in the subgroups mitigating undesired influences, e.g. temperature, pressure
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- Measuring Temperature Or Quantity Of Heat (AREA)
- Investigating Or Analysing Materials By Optical Means (AREA)
Abstract
本发明公开了一种宇航用光纤光栅传感系统及方法。其中，该系统包括光纤光栅解调仪、光纤光栅传感器探头和传输光缆；其中，所述光纤光栅解调仪发出的光通过所述传输光缆传输给所述光纤光栅传感器探头，所述光纤光栅传感器探头将包含待测结构的温度或应变量的光信号反射回所述光纤光栅解调仪，所述光纤光栅解调仪对反射回的光信号进行处理得到待测结构的温度或应变量。本发明解决了光纤光栅传感系统在宇航环境中应用的抗辐照的问题。
The invention discloses a fiber grating sensing system and method for aerospace. Wherein, the system includes a fiber Bragg grating demodulator, a fiber Bragg grating sensor probe and a transmission cable; wherein, the light emitted by the fiber Bragg grating demodulator is transmitted to the fiber Bragg grating sensor probe through the transmission cable, and the fiber Bragg grating sensor The probe reflects the optical signal containing the temperature or strain of the structure to be measured back to the fiber grating demodulator, and the fiber grating demodulator processes the reflected light signal to obtain the temperature or strain of the structure to be measured. The invention solves the problem of radiation resistance of the fiber grating sensing system applied in the aerospace environment.
Description
Technical Field
The invention belongs to the technical field of optical fiber sensors, and particularly relates to an optical fiber grating sensing system and method for aerospace.
Background
Compared with the traditional electrical sensing system, the fiber grating sensing system has the advantages of electromagnetic interference resistance, corrosion resistance, electrical insulation, multiplexing of multiple sensors and the like. The advantages of the fiber grating sensing system enable the fiber grating sensing system to be widely applied to the fields of engineering structure monitoring, electric power, petrochemical industry, oceans, medicine and the like.
In recent years, in the field of aerospace, the fiber grating sensing system also becomes a hotspot for research and application of novel measurement technology. However, due to special environmental conditions such as radiation and vacuum of aerospace, the application of the fiber grating sensing system to the aerospace environment has various technical difficulties. At present, the invention patent of the fiber bragg grating sensing system aiming at the aerospace irradiation environment does not exist in China. The fiber grating sensing system in the current application has extremely short service life under the irradiation action of the aerospace environment, and the output measurement result is easy to drift. How to overcome the influence of the irradiation effect of the aerospace environment on optoelectronic devices and electronic components of the fiber bragg grating sensing system has no specific and feasible technical means.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the fiber bragg grating sensing system and the method for aerospace are provided, and the problem of radiation resistance of the fiber bragg grating sensing system in the aerospace environment is solved.
The purpose of the invention is realized by the following technical scheme: according to an aspect of the present invention, there is provided a fiber grating sensing system for aerospace, including: the fiber grating sensor comprises a fiber grating demodulator, a fiber grating sensor probe and a transmission optical cable; the optical fiber grating sensor probe reflects an optical signal containing the temperature or the strain of the structure to be detected back to the optical fiber grating demodulator, and the optical fiber grating demodulator processes the reflected optical signal to obtain the temperature or the strain of the structure to be detected.
In the fiber grating sensing system for aerospace, the fiber grating demodulator comprises a shell, a circuit system and an optical measurement system; wherein the circuit system and the optical measurement system are both disposed within the housing; the circuit system with optical measurement system is connected, the light that optical measurement system sent passes through transmission cable transmits the fiber grating sensor probe, the fiber grating sensor probe will contain the temperature of the structure that awaits measuring or the light signal reflection of dependent variable return optical measurement system, circuit system handles the light signal of reflection and obtains the temperature of the structure that awaits measuring or the dependent variable.
In the fiber bragg grating sensing system for aerospace, the circuit system comprises a secondary power circuit and a light path control and signal acquisition processing circuit; the secondary power supply circuit converts power supply voltage, receives a control signal of an external system and is used for controlling the on-off of the fiber bragg grating demodulator; the optical path control and signal acquisition and processing circuit is used for controlling the optical measurement system and acquiring and processing an electric signal to obtain the temperature or the strain of the structure to be measured.
In the fiber bragg grating sensing system for aerospace, the optical measuring system comprises a light source, a fiber coupler, a spectrum detection module, an optical switch, a central wavelength calibration unit and a fiber connector; the light source emits a light source and transmits the light source to the optical switch and the central wavelength calibration unit through the optical fiber coupler respectively; the central wavelength calibration unit calibrates the measurement deviation of the optical measurement system in real time according to the wavelength of the central wavelength calibration unit; the optical switch carries out time-division multiplexing processing among channels on the spectrum from the optical fiber coupler and transmits the processed spectrum to the optical fiber connector; the optical fiber connector transmits the processed spectrum to the fiber bragg grating sensor probe through the transmission optical fiber; the fiber bragg grating sensor probe converts the processed spectrum into an optical signal containing the temperature or the strain of the structure to be detected, reflects the optical signal back to the optical fiber connector, and transmits the optical signal to the spectrum detection module through the optical switch and the coupler in sequence; the spectrum detection module carries out photoelectric conversion on an optical signal containing the temperature or the strain of the structure to be detected to obtain an electric signal.
In the fiber grating sensing system for aerospace, the secondary power supply circuit includes: the system comprises an anti-radiation filter, an anti-radiation power supply module and a relay; the anti-radiation filter is used for filtering an external power supply; the anti-irradiation power supply module realizes the conversion of power supply voltage; and the relay receives an external signal to realize the on-off control of the fiber grating demodulator.
In the fiber grating sensing system for aerospace, the optical path control and signal acquisition processing circuit includes: the system comprises an anti-irradiation FPGA chip, an anti-irradiation DSP chip, an input signal conditioning circuit, an analog-to-digital conversion circuit, a communication interface circuit, an anti-irradiation FPGA configuration chip, an anti-irradiation program memory, an optical switch driving circuit and a broadband light source driving circuit; the spectrum detection module provides a response signal for the anti-radiation FPGA chip; the analog-to-digital conversion circuit collects analog electric signals of the spectrum detection module, converts the analog electric signals into digital electric signals and sends the digital electric signals to the anti-irradiation FPGA chip; the anti-irradiation FPGA chip receives the digital electric signal of the analog-to-digital conversion circuit, preprocesses the digital electric signal, sends the digital electric signal to the anti-irradiation DSP chip for demodulation operation processing, and sends an operation result to external equipment through the communication interface circuit; the anti-irradiation FPGA configuration chip transmits configuration information to the anti-irradiation FPGA when the light path control and signal acquisition processing circuit is electrified; the anti-irradiation program memory transmits an operation instruction to the anti-irradiation DSP chip when the light path control and signal acquisition processing circuit is electrified; the broadband light source driving circuit provides stable driving current and a temperature control function for the light source; the optical switch driving circuit drives and controls the optical switch to realize the switching of the optical path channel.
In the fiber grating sensing system for aerospace, the central wavelength calibration unit includes: a standard center wavelength device and a temperature sensor; the standard central wavelength device is used for providing a standard central wavelength reference value for the fiber grating demodulator; the standard central wavelength device is connected with the optical fiber coupler, so that the spectrum measuring module of the optical measuring system receives reflected light of the standard central wavelength device, transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibrating unit, calculates a difference between the central wavelength measured value of the standard central wavelength device and a standard wavelength value which the circuit system should have, and uses the difference value for compensation of measurement deviation of the fiber grating demodulator; the temperature sensor is used for monitoring the temperature change of the standard central wavelength device and providing central wavelength reference values at different temperatures.
In the fiber grating sensing system for aerospace, the calibrating of the central wavelength by the central wavelength calibrating unit according to the wavelength of the central wavelength calibrating unit comprises: the wavelength of the reflected light of the central wavelength calibration unit is a standard wavelength value, the optical measurement system receives the reflected light of the central wavelength calibration unit, and transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, and calculates a difference between the central wavelength measured value of the central wavelength calibration unit and the standard wavelength value to which the central wavelength measured value should be subjected, and the difference is used for compensating the measurement deviation of the fiber grating demodulator.
According to another aspect of the present invention, there is also provided a fiber grating sensing method for aerospace, including the steps of: the light emitted by the fiber grating demodulator is transmitted to the fiber grating sensor probe through a transmission optical cable; the fiber bragg grating sensor probe reflects an optical signal containing the temperature or the strain quantity of the structure to be measured back to the fiber bragg grating demodulator; and the fiber grating demodulator processes the reflected optical signal to obtain the temperature or the strain of the structure to be measured.
In the fiber grating sensing method for aerospace, the fiber grating demodulator comprises a shell, a circuit system and an optical measurement system; wherein the circuit system and the optical measurement system are both disposed within the housing; the circuit system with optical measurement system is connected, the light that optical measurement system sent passes through transmission cable transmits the fiber grating sensor probe, the fiber grating sensor probe will contain the temperature of the structure that awaits measuring or the light signal reflection of dependent variable return optical measurement system, circuit system handles the light signal of reflection and obtains the temperature of the structure that awaits measuring or the dependent variable.
In the fiber grating sensing method for aerospace, the circuit system comprises a secondary power circuit and a light path control and signal acquisition processing circuit; the secondary power supply circuit converts power supply voltage, receives a control signal of an external system and is used for controlling the on-off of the fiber bragg grating demodulator; the optical path control and signal acquisition and processing circuit is used for controlling the optical measurement system and acquiring and processing an electric signal to obtain the temperature or the strain of the structure to be measured.
In the fiber bragg grating sensing method for aerospace, the optical measuring system comprises a light source, a fiber coupler, a spectrum detection module, an optical switch, a central wavelength calibration unit and a fiber connector; the light source emits a light source and transmits the light source to the optical switch and the central wavelength calibration unit through the optical fiber coupler respectively; the central wavelength calibration unit calibrates the measurement deviation of the optical measurement system in real time according to the wavelength of the central wavelength calibration unit; the optical switch carries out time-division multiplexing processing among channels on the spectrum from the optical fiber coupler and transmits the processed spectrum to the optical fiber connector; the optical fiber connector transmits the processed spectrum to the fiber bragg grating sensor probe through the transmission optical fiber; the fiber bragg grating sensor probe converts the processed spectrum into an optical signal containing the temperature or the strain of the structure to be detected, reflects the optical signal back to the optical fiber connector, and transmits the optical signal to the spectrum detection module through the optical switch and the coupler in sequence; the spectrum detection module carries out photoelectric conversion on an optical signal containing the temperature or the strain of the structure to be detected to obtain an electric signal.
In the fiber grating sensing method for aerospace, the secondary power supply circuit includes: the system comprises an anti-radiation filter, an anti-radiation power supply module and a relay; the anti-radiation filter is used for filtering an external power supply; the anti-irradiation power supply module realizes the conversion of power supply voltage; and the relay receives an external signal to realize the on-off control of the fiber grating demodulator.
In the fiber grating sensing method for aerospace, the optical path control and signal acquisition processing circuit comprises: the system comprises an anti-irradiation FPGA chip, an anti-irradiation DSP chip, an input signal conditioning circuit, an analog-to-digital conversion circuit, a communication interface circuit, an anti-irradiation FPGA configuration chip, an anti-irradiation program memory, an optical switch driving circuit and a broadband light source driving circuit; the spectrum detection module provides a response signal for the anti-radiation FPGA chip; the analog-to-digital conversion circuit collects analog electric signals of the spectrum detection module, converts the analog electric signals into digital electric signals and sends the digital electric signals to the anti-irradiation FPGA chip; the anti-irradiation FPGA chip receives the digital electric signal of the analog-to-digital conversion circuit, preprocesses the digital electric signal, sends the digital electric signal to the anti-irradiation DSP chip for demodulation operation processing, and sends an operation result to external equipment through the communication interface circuit; the anti-irradiation FPGA configuration chip transmits configuration information to the anti-irradiation FPGA when the light path control and signal acquisition processing circuit is electrified; the anti-irradiation program memory transmits an operation instruction to the anti-irradiation DSP chip when the light path control and signal acquisition processing circuit is electrified; the broadband light source driving circuit provides stable driving current and a temperature control function for the light source; the optical switch driving circuit drives and controls the optical switch to realize the switching of the optical path channel.
In the fiber grating sensing method for aerospace, the central wavelength calibration unit includes: a standard center wavelength device and a temperature sensor; the standard central wavelength device is used for providing a standard central wavelength reference value for the fiber grating demodulator; the standard central wavelength device is connected with the optical fiber coupler, so that the spectrum measurement module of the optical measurement system receives reflected light of the standard central wavelength device, transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, calculates a difference between the central wavelength measured value of the standard central wavelength device and a standard wavelength value which the circuit system should have, and uses the difference value for compensation of measurement deviation of the fiber grating demodulator; the temperature sensor is used for monitoring the temperature change of the standard central wavelength device and providing central wavelength reference values at different temperatures.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention solves the problem of radiation resistance of the fiber grating sensing system applied in an aerospace environment.
(2) The invention adopts the central wavelength calibration unit to calibrate the measurement drift caused by irradiation in real time, so that the measurement precision of the fiber grating sensing system has long-term stability.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
fig. 1 is a schematic composition diagram of an aerospace fiber grating sensing system according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic composition diagram of an aerospace fiber grating sensing system according to an embodiment of the present invention. As shown in fig. 1, the fiber grating sensing system for aerospace includes: the fiber grating sensing system comprises a fiber grating demodulator, a fiber grating sensor probe and a transmission optical cable.
The fiber grating demodulator consists of a shell structure, a circuit system and an optical measurement system. The shell structure provides a fixed mounting structure for a circuit system and an optical measurement system of the fiber grating demodulator, and plays roles of integrally shielding irradiation, slowing down mechanical vibration and impact influence, dissipating heat and the like. The circuit system comprises a secondary power supply circuit and a light path control and signal acquisition processing circuit; the secondary power supply circuit is used for converting power supply voltage for a circuit system of the fiber grating demodulator, receiving a control signal of an external system and realizing the on-off of the fiber sensing system; the optical path control and signal acquisition processing circuit can realize the control of an optical measurement system of the fiber bragg grating demodulator, the acquisition and processing of electric signals and send the measurement result to an external system through a communication interface. The optical measurement system comprises a broadband light source, an optical fiber coupler, a spectrum detection module, an optical switch, a central wavelength calibration unit and an optical fiber connector.
When the fiber grating sensing system for aerospace is started up and works under the control of the external power supply and the control interface, the light path control and signal acquisition processing circuit of the fiber grating demodulator is started, the optical measurement system in the demodulator is controlled to perform photoelectric conversion on optical measurement signals reflected by the fiber grating sensor, the converted electric signals are transmitted to the light path control and signal acquisition processing circuit of the fiber grating demodulator to be demodulated and operated, and the demodulated results are transmitted to external equipment through the communication interface. In order to ensure the long-term stability of the demodulation result precision, a central wavelength calibration unit is designed in the fiber grating demodulator to calibrate the measurement drift caused by irradiation in real time; and the irradiation-resistant fiber bragg grating sensor probe is used, so that the influence of irradiation on measurement is reduced.
A broadband light source provides a light source for the optical measurement system.
And the optical fiber coupler distributes the optical power from the broadband light source and transmits the optical power to the optical switch and the central wavelength calibration unit respectively.
The central wavelength calibration unit calibrates the measurement deviation of the optical measurement system in real time. The wavelength of the reflected light of the central wavelength calibration unit is a standard wavelength value, the optical measurement system receives the reflected light of the central wavelength calibration unit, and transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, and calculates a difference between the central wavelength measured value of the central wavelength calibration unit and the standard wavelength value, and the difference is used for compensating the measurement deviation of the fiber grating demodulator.
And the optical switch performs time division multiplexing processing among channels on the spectrum from the optical fiber coupler and transmits the processed spectrum to the optical fiber connector.
The fiber optic connector further transmits the spectrum to the transmission fiber and the fiber grating sensor probe.
And the spectrum detection module is used for performing photoelectric conversion on the spectrum signal reflected by the fiber bragg grating sensor probe.
And the transmission optical cable is used for realizing the optical signal transmission of the fiber grating demodulator and the fiber grating sensor probe.
The fiber grating sensor probe is used for measuring the temperature or the strain of a structure to be measured and transmitting a measurement result back to the fiber grating demodulator through the transmission optical cable for processing.
Specifically, the center wavelength calibration unit includes: a standard center wavelength device and a temperature sensor; the standard central wavelength device is used for providing a standard central wavelength reference value for the fiber grating demodulator; the standard central wavelength device is connected with the optical fiber coupler, so that the spectrum measurement module of the optical measurement system receives reflected light of the standard central wavelength device, transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, calculates a difference between the central wavelength measured value of the standard central wavelength device and a standard wavelength value which the circuit system should have, and uses the difference value for compensation of measurement deviation of the fiber grating demodulator; the temperature sensor is used for monitoring the temperature change of the standard central wavelength device and providing central wavelength reference values at different temperatures.
Specifically, the secondary power supply circuit includes: the anti-radiation filter, the anti-radiation power supply module and the relay. The anti-irradiation filter carries out filtering processing on an external power supply; the anti-irradiation power supply module realizes the conversion of power supply voltage; the relay receives external signals to realize the on-off control of the fiber grating demodulator.
Specifically, the optical path control and signal acquisition processing circuit includes: the system comprises an anti-radiation FPGA chip, an anti-radiation DSP chip, an input signal conditioning circuit, an analog-to-digital conversion circuit, a communication interface circuit, an anti-radiation FPGA configuration chip, an anti-radiation program memory, an optical switch driving circuit and a broadband light source driving circuit.
The anti-irradiation FPGA chip provides a control signal for the spectrum detection module, and the spectrum detection module provides a response signal for the anti-irradiation FPGA chip.
The analog-to-digital conversion circuit collects the analog electric signals of the spectrum detection module, converts the analog electric signals into digital electric signals and sends the digital electric signals to the anti-irradiation FPGA chip.
The anti-irradiation FPGA chip receives the digital electric signal of the analog-to-digital conversion circuit, preprocesses the digital electric signal, sends the digital electric signal to the anti-irradiation DSP chip for demodulation operation processing, and sends the operation result to external equipment through the communication interface circuit.
And the anti-irradiation FPGA configuration chip transmits the configuration information to the anti-irradiation FPGA when the light path control and signal acquisition processing circuit is electrified.
And the anti-irradiation program memory transmits the running program to the anti-irradiation DSP chip when the light path control and signal acquisition processing circuit is electrified.
The broadband light source driving circuit provides stable driving current and a temperature control function for the broadband light source.
The optical switch driving circuit drives and controls the optical switch to realize the switching of the optical path channel.
The center wavelength calibration unit includes: standard center wavelength device, temperature sensor, fiber grating. The standard central wavelength device is used for providing a standard central wavelength reference value for the fiber grating demodulator; the temperature sensor is used for monitoring the temperature change of the central wavelength calibration unit so as to carry out temperature compensation; the fiber grating is used for carrying out actual measurement wavelength reference.
Preferably, the fiber coupler is a 3dB fiber coupler.
Preferably, the spectral measurement module comprises a diffraction grating and a detector array, which can measure the spectrum in a wavelength range larger than 40 nm.
The fiber grating sensor probe comprises a fiber grating and a packaging structure. The fiber grating is prepared by adopting specific materials and processes, so that the fiber grating has the radiation resistance; the packaging structure adopts high-density materials, and the influence of irradiation on the fiber bragg grating is further reduced.
The external power supply and the control interface supply power for a secondary power supply circuit of the space navigation fiber grating sensing system, and the space navigation fiber grating sensing system is started to work. The optical path control and signal acquisition processing circuit of the fiber grating demodulator is started, the optical path control and signal acquisition processing circuit controls the light source to emit light signals, and the light signals are distributed to the central wavelength calibration unit and the optical switch through the fiber coupler. The central wavelength calibration unit feeds back the optical signal with calibration information to the spectrum measurement module through the optical fiber coupler. The optical signal is distributed to different measuring channels of the optical fiber connector through the optical switch, the optical fiber connector is connected with the transmission optical cable with the fiber bragg grating sensor probe, and after the fiber bragg grating sensor probe senses temperature or strain information, the optical signal with the temperature or strain information is fed back to the spectrum measuring module along the transmission optical cable, the optical fiber connector, the optical switch and the optical fiber coupler. The spectrum measurement module carries out photoelectric conversion on optical signals reflected by the fiber grating sensor probe, and then transmits the converted electric signals to a light path control and signal acquisition processing circuit of a fiber grating demodulator for demodulation operation processing. And the light path control and signal acquisition processing circuit transmits the demodulation result to external equipment through a communication interface. In order to ensure the long-term stability of the demodulation result precision, a central wavelength calibration unit is designed in the fiber grating demodulator to calibrate the measurement drift caused by irradiation in real time; and the irradiation-resistant fiber bragg grating sensor probe is used, so that the influence of irradiation on measurement is reduced.
The embodiment also provides an aerospace fiber grating sensing method, which comprises the following steps: the light emitted by the fiber grating demodulator is transmitted to the fiber grating sensor probe through a transmission optical cable; the fiber bragg grating sensor probe reflects an optical signal containing the temperature or the strain quantity of the structure to be measured back to the fiber bragg grating demodulator; and the fiber grating demodulator processes the reflected optical signal to obtain the temperature or the strain of the structure to be measured.
In the embodiment, the anti-irradiation electronic component is used, so that the circuit of the fiber grating sensing system can stably work in the irradiation environment for a long time.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (10)
1. An optical fiber grating sensing system for aerospace, characterized by comprising: the fiber grating sensor comprises a fiber grating demodulator, a fiber grating sensor probe and a transmission optical cable; wherein,
the light that fiber grating demodulation appearance sent passes through transmission cable transmits the fiber grating sensor probe, the fiber grating sensor probe will contain the temperature of the structure that awaits measuring or the light signal reflection of dependent variable return the fiber grating demodulation appearance, the fiber grating demodulation appearance is handled the light signal of reflecting back and is obtained the temperature of the structure that awaits measuring or dependent variable.
2. The fiber grating sensing system for aerospace of claim 1, wherein: the fiber grating demodulator comprises a shell, a circuit system and an optical measurement system; wherein,
the circuit system and the optical measurement system are both arranged in the shell;
the circuit system with optical measurement system is connected, the light that optical measurement system sent passes through transmission cable transmits the fiber grating sensor probe, the fiber grating sensor probe will contain the temperature of the structure that awaits measuring or the light signal reflection of dependent variable return optical measurement system, circuit system handles the light signal of reflection and obtains the temperature of the structure that awaits measuring or the dependent variable.
3. The fiber grating sensing system for aerospace of claim 2, wherein: the circuit system comprises a secondary power supply circuit and a light path control and signal acquisition processing circuit; wherein,
the secondary power supply circuit converts the power supply voltage, receives a control signal of an external system and is used for controlling the on-off of the fiber bragg grating demodulator;
the optical path control and signal acquisition and processing circuit is used for controlling the optical measurement system and acquiring and processing an electric signal to obtain the temperature or the strain of the structure to be measured.
4. The fiber grating sensing system for aerospace of claim 3, wherein: the optical measurement system comprises a light source, an optical fiber coupler, a spectrum detection module, an optical switch, a central wavelength calibration unit and an optical fiber connector; wherein,
the light source emits a light source and transmits the light source to the optical switch and the central wavelength calibration unit through the optical fiber coupler respectively;
the central wavelength calibration unit calibrates the measurement deviation of the optical measurement system in real time according to the wavelength of the central wavelength calibration unit;
the optical switch carries out time-division multiplexing processing among channels on the spectrum from the optical fiber coupler and transmits the processed spectrum to the optical fiber connector;
the optical fiber connector transmits the processed spectrum to the fiber bragg grating sensor probe through the transmission optical fiber;
the fiber bragg grating sensor probe converts the processed spectrum into an optical signal containing the temperature or the strain of the structure to be detected, reflects the optical signal back to the optical fiber connector, and transmits the optical signal to the spectrum detection module through the optical switch and the coupler in sequence;
the spectrum detection module carries out photoelectric conversion on an optical signal containing the temperature or the strain of the structure to be detected to obtain an electric signal.
5. The fiber grating sensing system for aerospace of claim 3, wherein: the secondary power supply circuit includes: the system comprises an anti-radiation filter, an anti-radiation power supply module and a relay; the anti-radiation filter is used for filtering an external power supply; the anti-irradiation power supply module realizes the conversion of power supply voltage; and the relay receives an external signal to realize the on-off control of the fiber grating demodulator.
6. The fiber grating sensing system for aerospace of claim 4, wherein: the light path control and signal acquisition processing circuit includes: the system comprises an anti-irradiation FPGA chip, an anti-irradiation DSP chip, an input signal conditioning circuit, an analog-to-digital conversion circuit, a communication interface circuit, an anti-irradiation FPGA configuration chip, an anti-irradiation program memory, an optical switch driving circuit and a broadband light source driving circuit; the spectrum detection module provides a response signal for the anti-radiation FPGA chip; the analog-to-digital conversion circuit collects analog electric signals of the spectrum detection module, converts the analog electric signals into digital electric signals and sends the digital electric signals to the anti-irradiation FPGA chip; the anti-irradiation FPGA chip receives the digital electric signal of the analog-to-digital conversion circuit, preprocesses the digital electric signal, sends the digital electric signal to the anti-irradiation DSP chip for demodulation operation processing, and sends an operation result to external equipment through the communication interface circuit; the anti-irradiation FPGA configuration chip transmits configuration information to the anti-irradiation FPGA when the light path control and signal acquisition processing circuit is electrified; the anti-irradiation program memory transmits an operation instruction to the anti-irradiation DSP chip when the light path control and signal acquisition processing circuit is electrified; the broadband light source driving circuit provides stable driving current and a temperature control function for the light source; the optical switch driving circuit drives and controls the optical switch to realize the switching of the optical path channel.
7. The fiber grating sensing system for aerospace of claim 4, wherein: the center wavelength calibration unit includes: a standard center wavelength device and a temperature sensor; the standard central wavelength device is used for providing a standard central wavelength reference value for the fiber grating demodulator; the standard central wavelength device is connected with the optical fiber coupler, so that the spectrum measurement module of the optical measurement system receives reflected light of the standard central wavelength device, transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, calculates a difference between the central wavelength measured value of the standard central wavelength device and a standard wavelength value which the circuit system should have, and uses the difference value for compensation of measurement deviation of the fiber grating demodulator; the temperature sensor is used for monitoring the temperature change of the standard central wavelength device and providing central wavelength reference values at different temperatures.
8. The fiber grating sensing system for aerospace of claim 4, wherein: the real-time calibration of the measurement deviation of the optical measurement system by the central wavelength calibration unit according to its own wavelength comprises: the wavelength of the reflected light of the central wavelength calibration unit is a standard wavelength value, the optical measurement system receives the reflected light of the central wavelength calibration unit, and transmits an electric signal to the circuit system through photoelectric conversion, the circuit system calculates a central wavelength measured value of the central wavelength calibration unit, and calculates a difference between the central wavelength measured value of the central wavelength calibration unit and the standard wavelength value to which the central wavelength measured value should be subjected, and the difference is used for compensating the measurement deviation of the fiber grating demodulator.
9. A fiber grating sensing method for aerospace is characterized by comprising the following steps:
the light emitted by the fiber grating demodulator is transmitted to the fiber grating sensor probe through a transmission optical cable;
the fiber bragg grating sensor probe reflects an optical signal containing the temperature or the strain quantity of the structure to be measured back to the fiber bragg grating demodulator;
and the fiber grating demodulator processes the reflected optical signal to obtain the temperature or the strain of the structure to be measured.
10. The fiber grating sensing method for aerospace of claim 9, wherein: the fiber grating demodulator comprises a shell, a circuit system and an optical measurement system; wherein,
the circuit system and the optical measurement system are both arranged in the shell;
the circuit system with optical measurement system is connected, the light that optical measurement system sent passes through transmission cable transmits the fiber grating sensor probe, the fiber grating sensor probe will contain the temperature of the structure that awaits measuring or the light signal reflection of dependent variable return optical measurement system, circuit system handles the light signal of reflection and obtains the temperature of the structure that awaits measuring or the dependent variable.
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