CN218524182U - Aircraft measurement system based on fiber bragg grating - Google Patents
Aircraft measurement system based on fiber bragg grating Download PDFInfo
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- CN218524182U CN218524182U CN202222010204.6U CN202222010204U CN218524182U CN 218524182 U CN218524182 U CN 218524182U CN 202222010204 U CN202222010204 U CN 202222010204U CN 218524182 U CN218524182 U CN 218524182U
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Abstract
The utility model provides an aircraft measurement system based on fiber grating can solve current aircraft physical quantity measurement inaccuracy and easily receive electromagnetic interference's problem. The measurement system includes: the device comprises a processor, a scanning laser, an optical splitter, an optical coupler, a photoelectric detector and a fiber bragg grating sensor unit; the processor is electrically connected with the scanning laser, and the scanning laser scans and outputs pulse light according to a set step length; the scanning laser is connected with the input port of the optical splitter through an optical fiber; n output ports of the optical splitter are respectively connected with one output port of the N optical couplers through optical fibers; the input ports of the N optical couplers are respectively connected with the N fiber grating sensor groups through optical fibers; the other output ports of the N optical couplers are respectively connected with N input ports of the photoelectric detector through optical fibers, and optical signals are converted into electric signals through the photoelectric detector; the output port of the photoelectric detector is electrically connected with the processor.
Description
Technical Field
The utility model relates to a measurement system, concretely relates to aircraft measurement system based on fiber grating belongs to fiber grating sensing technology field.
Background
Fiber gratings are essentially passive filters formed by periodically modulating the refractive index of the fiber core. The fiber bragg grating has the following advantages: the anti-electromagnetic interference capability is strong, and the optical fiber cannot be interfered by electromagnetic waves in the transmission process; the volume is small, and the fiber grating is compatible with optical fiber; the transmission distance is long, the precision is high, the fiber grating measurement precision is not influenced by the light intensity, and the fiber grating sensor has the characteristics of easiness in networking measurement and integration and the like, so that the fiber grating sensor is widely applied to the fields of fiber communication and sensing.
The physical quantities of the current aircraft include: temperature, vibration, atmospheric pressure etc. use the device mostly to be the electric sensor when measuring, and it has the great and less scheduling problem of precision of receiving the temperature influence at present.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides an aircraft measurement system based on fiber grating can solve current aircraft physical quantity and measure the inaccuracy and easily receive electromagnetic interference's problem.
The technical scheme of the utility model is that: an optical fiber grating-based aircraft measurement system comprising: the device comprises a processor, a scanning laser, an optical splitter, an optical coupler, a photoelectric detector and a fiber bragg grating sensor unit; the optical coupler is a 1 × 2 optical coupler;
the object to be measured is an aircraft, N physical quantities to be measured of the aircraft are provided, and N is an integer greater than or equal to 1;
the optical splitter is a 1 × N optical splitter; the photoelectric detector is an N-path photoelectric detector; the fiber bragg grating sensor unit comprises N fiber bragg grating sensor groups; each fiber grating sensor group corresponds to the measurement of one physical quantity;
the processor is electrically connected with the scanning laser, so that the scanning laser scans and outputs pulsed light according to a set step length;
the scanning laser is connected with the input port of the optical splitter through an optical fiber;
n output ports of the optical splitter are respectively connected with one output port of the N optical couplers through optical fibers; the input ports of the N optical couplers are respectively connected with the N fiber bragg grating sensor groups through optical fibers; the other output ports of the N optical couplers are respectively connected with N input ports of the photoelectric detector through optical fibers, and optical signals are converted into electric signals through the photoelectric detector; and the output port of the photoelectric detector is electrically connected with the processor.
On the basis of the scheme, the optical isolator further comprises an optical isolator; the scanning laser is connected with an optical isolator through an optical fiber, and the optical isolator is connected with the input port of the optical splitter through the optical fiber.
On the basis of the above scheme, further, there are four physical quantities to be measured of the aircraft, which are respectively: temperature, vibration, strain and air pressure;
the fiber grating sensor unit comprises a fiber grating temperature sensor group, a fiber grating vibration sensor group, a fiber grating strain sensor group and a fiber grating air pressure sensor group.
On the basis of the scheme, further, a fiber grating temperature sensor is arranged at each temperature measuring point on the aircraft to be measured, and the fiber grating temperature sensors are connected in series through optical fibers to form a fiber grating temperature sensor group;
arranging a fiber bragg grating vibration sensor at each vibration measuring point on the aircraft to be measured, wherein the fiber bragg grating vibration sensors are connected in series through optical fibers to form a fiber bragg grating vibration sensor group;
arranging a fiber bragg grating strain sensor at each strain measurement point on the aircraft to be measured, wherein the fiber bragg grating strain sensors are connected in series through optical fibers to form a fiber bragg grating strain sensor group;
and arranging one fiber bragg grating air pressure sensor at each air pressure measuring point on the aircraft to be measured, wherein the fiber bragg grating air pressure sensors are connected in series through optical fibers to form a fiber bragg grating air pressure sensor group.
On the basis of the scheme, the ARM processor is further adopted for processing.
Has the advantages that:
(1) The utility model relates to an aircraft measurement system based on fiber bragg grating, which can measure each physical quantity of the aircraft with high precision when measuring; the measurement system can solve the problems of low measurement precision and susceptibility to electromagnetic interference of the traditional measurement system.
(2) By providing the multi-path optical splitter and the multi-path photodetector, a plurality of physical quantities can be measured at the same time.
(3) An optical isolator is arranged between the scanning laser and the optical splitter, so that reflected light in the optical fiber can be prevented from entering the scanning laser and damaging the scanning laser.
Drawings
Fig. 1 is the structure diagram of the aircraft measurement system based on fiber grating of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
The embodiment provides an aircraft measurement system based on fiber bragg grating, and solves the problem that the physical quantity of the existing aircraft is inaccurate.
As shown in fig. 1, the measuring system includes: the system comprises an ARM processor, a scanning laser, an optical fiber, an optical isolator, an optical splitter, an optical coupler, a photoelectric detector and a fiber bragg grating sensor unit; the object to be measured is an aircraft.
The measurement system can be used for simultaneously measuring a plurality of physical quantities of the aircraft, and in the example, the physical quantities to be measured comprise: temperature, vibration, strain and air pressure; based on the optical splitter, the optical splitter adopts a 1 × 4 optical splitter, namely, the optical splitter has 1 input port and four output ports; the fiber grating sensor unit comprises a fiber grating temperature sensor, a fiber grating vibration sensor, a fiber grating strain sensor and a fiber grating air pressure sensor.
And arranging one fiber bragg grating temperature sensor at each temperature measuring point on the aircraft to be measured, wherein the fiber bragg grating temperature sensors are connected in series through optical fibers to form a fiber bragg grating temperature sensor group.
And arranging one fiber bragg grating vibration sensor at each vibration measuring point on the aircraft to be measured, wherein the fiber bragg grating vibration sensors are connected in series through optical fibers to form a fiber bragg grating vibration sensor group.
And arranging a fiber bragg grating strain sensor at each strain measurement point on the aircraft to be measured, wherein the fiber bragg grating strain sensors are connected in series through optical fibers to form a fiber bragg grating strain sensor group.
And arranging a fiber bragg grating air pressure sensor at each air pressure measuring point on the aircraft to be measured, wherein the fiber bragg grating air pressure sensors are connected in series through optical fibers to form a fiber bragg grating air pressure sensor group.
The four fiber bragg grating sensor groups form four measuring ends.
Meanwhile, four 1 × 2 optical couplers are correspondingly arranged, namely, each optical coupler is provided with an input port and two output ports, and the input ports are respectively communicated with the two output ports; the four optical couplers are respectively an optical coupler A, an optical coupler B, an optical coupler C and an optical coupler D. The photodetector adopts a 4-path photodetector, and has four input ports and one output port.
The ARM processor is electrically connected with the scanning laser (namely connected through a data line), the scanning laser is connected with the optical isolator through optical fibers, the optical isolator is connected with the input port of the optical splitter through the optical fibers, and the four output ports of the optical splitter are connected with the four measuring ends through four optical fiber passages provided with optical couplers respectively. As shown in fig. 1, in this example, the first output port of the optical splitter is connected to the first output port of the optical coupler a through an optical fiber, and the input port of the optical coupler a is connected to the fiber grating temperature sensor group through an optical fiber. That is, the path between the first output port and the input port of the optical coupler a is used to realize the input of the pulsed light from the first output port to the input port; meanwhile, a return optical signal of the fiber grating temperature sensor enters the optical coupler A through the input port of the optical coupler A, and therefore a temperature measuring loop is formed.
Similarly, the second output port of the optical splitter is connected with the first output port of the optical coupler B through an optical fiber, and the input port of the optical coupler B is connected with the fiber bragg grating vibration sensor group through an optical fiber; the third output port of the optical splitter is connected with the first output port of the optical coupler C through an optical fiber, and the input port of the optical coupler C is connected with the fiber bragg grating strain sensor group through an optical fiber; and a fourth output port of the optical splitter is connected with a first output port of the optical coupler D through an optical fiber, and an input port of the optical coupler D is connected with the fiber bragg grating air pressure sensor group through an optical fiber.
The second output ports of the four optical couplers are respectively connected with the four input ports of the photoelectric detector through optical fibers, and the output port of the photoelectric detector is electrically connected with the ARM processor. The light returned from the measurement end is input through the input port of the optical coupler and then output to the photodetector.
In this example, the ARM processor with high selective valence is a model STM32F103C8T6, and is a 32-bit microcontroller based on an ARM Cortex-M kernel STM32 series, and the working dominant frequency is 72MHz. The ARM processor is communicated with the scanning laser, so that the scanning laser scans and outputs pulse light according to a set step length (in the example, the step length is 8 pm); the light emitted by the scanning laser is light with gradually changing wavelength according to the electric pulse.
The optical isolator is used for preventing reflected light in the optical fiber from entering the scanning laser and damaging the scanning laser, namely, pulsed light output by the scanning laser passes through the optical isolator, and the reflected light is prevented from damaging the scanning laser. The optical isolator used in this example has a center wavelength of 1550nm.
The optical fiber is a common quartz optical fiber and is used for connecting optical devices to form a measuring loop.
The optical splitter is a distribution device which is based on a quartz substrate integrated waveguide and realizes the optical power splitting function, and is a passive optical device. The device has the advantages of small volume, wide light splitting wavelength range and good light splitting uniformity. Pulsed light output by the scanning laser passes through the optical isolator and then passes through the optical splitter.
The pulsed light enters the four optical couplers respectively after passing through the optical splitter. The optical coupler has the function of realizing the splitting of optical signals among different optical paths according to the splitting ratio or the combination of multiple optical paths, and is a passive optical device which is used in the optical fiber sensing technology. The optical couplers used in this example all had a splitting ratio of 1:1 × 2 directional coupler of 1, the transmission direction of which enters from the input port according to 1: the light splitting ratio of 1 is respectively output to the optical path by the two output ports.
The fiber bragg grating temperature sensor is manufactured by using fiber bragg grating and a mechanical structure, a fixed center wavelength is adopted when the fiber bragg grating temperature sensor is manufactured, when the external temperature changes, the center wavelength of the sensor drifts, and the drift amount is in direct proportion to the temperature change amount.
The pulse light passing through the optical coupler B enters the fiber bragg grating vibration sensor to carry out vibration measurement on a vibration measuring point of the aircraft, the fiber bragg grating vibration sensor is a vibration sensor manufactured by utilizing a fiber bragg grating and a mechanical structure, a fixed center wavelength is adopted when the sensor is manufactured, when external vibration changes, the center wavelength of the sensor drifts, and the drift amount is in direct proportion to the vibration amount.
The fiber bragg grating strain sensor is manufactured by using fiber bragg grating and a mechanical structure, a fixed central wavelength is adopted when the fiber bragg grating strain sensor is manufactured, when external strain changes, the central wavelength of the fiber bragg grating strain sensor drifts, and the drift amount is in direct proportion to the strain amount.
The fiber grating air pressure sensor is manufactured by using a fiber grating and a mechanical structure, a fixed center wavelength is adopted when the fiber grating air pressure sensor is manufactured, the center wavelength drifts when the external air pressure changes, and the drift amount is in direct proportion to the air pressure amount.
Light reflected by each sensor enters the photoelectric detector through the four optical couplers and is converted into an electric signal, and the electric signal is collected, analyzed and demodulated by the ARM processor. The 4-path photoelectric detector is used for amplifying and filtering light returned by each sensor and processing the light by a subsequent circuit, and is the key of the optical fiber sensing system.
The ARM processor is communicated with the scanning laser, and in the embodiment, the scanning laser is set by the serial assistant as follows: the scanning range is 1528 nm-1568 nm, the scanning speed is 2KHz, and the scanning mode is continuous scanning. The scanning laser device is set by the upper computer and then emits scanning laser (namely pulse light), and the scanning laser enters the light path through the optical fiber and the optical isolator. And the optical signals respectively enter the measuring ends connected with the four 1 × 2 optical couplers through a 1 × 4 optical splitter, and then respectively enter the sensors distributed on the aircraft to be measured. The reflected light of the sensor passes through four 1 multiplied by 2 optical couplers and reverse loops respectively, then is amplified and filtered by a photoelectric detector and converted into an electric signal (the prior art), and then is converted into a circuit part by a data acquisition card to work. And finally, the ARM processor collects circuit signals of 4 paths of photoelectric detectors, fitting and peak-finding algorithm analysis are carried out on the collected data (the ARM processor processes the collected data in the prior art), and all physical quantities of the measured aircraft are calculated.
Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (5)
1. An aircraft measurement system based on fiber bragg gratings, comprising: the device comprises a processor, a scanning laser, an optical splitter, an optical coupler, a photoelectric detector and a fiber bragg grating sensor unit; the optical coupler is a 1 × 2 optical coupler;
the object to be measured is an aircraft, N physical quantities to be measured of the aircraft are provided, and N is an integer greater than or equal to 1;
the optical splitter is a 1 × N optical splitter; the photoelectric detector is an N-path photoelectric detector; the fiber bragg grating sensor unit comprises N fiber bragg grating sensor groups; each fiber grating sensor group corresponds to the measurement of a physical quantity;
the processor is electrically connected with the scanning laser, so that the scanning laser scans and outputs pulsed light according to a set step length;
the scanning laser is connected with the input port of the optical splitter through an optical fiber;
n output ports of the optical splitter are respectively connected with one output port of the N optical couplers through optical fibers; the input ports of the N optical couplers are respectively connected with the N fiber grating sensor groups through optical fibers; the other output ports of the N optical couplers are respectively connected with N input ports of the photoelectric detector through optical fibers, and optical signals are converted into electric signals through the photoelectric detector; and the output port of the photoelectric detector is electrically connected with the processor.
2. The fiber grating-based aerial vehicle measurement system of claim 1, further comprising an optical isolator; the scanning laser is connected with an optical isolator through an optical fiber, and the optical isolator is connected with the input port of the optical splitter through the optical fiber.
3. The fiber grating-based aircraft measurement system of claim 1 or 2, wherein the physical quantity to be measured of the aircraft is four, which are respectively: temperature, vibration, strain and air pressure;
the fiber grating sensor unit comprises a fiber grating temperature sensor group, a fiber grating vibration sensor group, a fiber grating strain sensor group and a fiber grating air pressure sensor group.
4. The fiber grating-based aircraft measurement system of claim 3, wherein a fiber grating temperature sensor is arranged at each temperature measurement point on the aircraft to be measured, and the fiber grating temperature sensors are connected in series through optical fibers to form a fiber grating temperature sensor group;
arranging a fiber bragg grating vibration sensor at each vibration measuring point on the aircraft to be measured, wherein the fiber bragg grating vibration sensors are connected in series through optical fibers to form a fiber bragg grating vibration sensor group;
arranging a fiber bragg grating strain sensor at each strain measurement point on the aircraft to be measured, wherein the fiber bragg grating strain sensors are connected in series through optical fibers to form a fiber bragg grating strain sensor group;
and arranging one fiber bragg grating air pressure sensor at each air pressure measuring point on the aircraft to be measured, wherein the fiber bragg grating air pressure sensors are connected in series through optical fibers to form a fiber bragg grating air pressure sensor group.
5. The fiber grating-based aircraft measurement system of claim 1 wherein the processing employs an ARM processor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202222010204.6U CN218524182U (en) | 2022-08-01 | 2022-08-01 | Aircraft measurement system based on fiber bragg grating |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202222010204.6U CN218524182U (en) | 2022-08-01 | 2022-08-01 | Aircraft measurement system based on fiber bragg grating |
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