CN115290212A - Rocket temperature detection system and method - Google Patents
Rocket temperature detection system and method Download PDFInfo
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- CN115290212A CN115290212A CN202210818705.9A CN202210818705A CN115290212A CN 115290212 A CN115290212 A CN 115290212A CN 202210818705 A CN202210818705 A CN 202210818705A CN 115290212 A CN115290212 A CN 115290212A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
- G01K11/32—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using changes in transmittance, scattering or luminescence in optical fibres
- G01K11/3206—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
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Abstract
The invention provides a temperature detection system and a temperature detection method for a rocket, wherein the system comprises: the system comprises a light source, an isolator, a coupler, a photoelectric detector, a comprehensive control machine and a fiber grating network; the fiber grating network consists of a plurality of fiber gratings, and the fiber grating network penetrates through the whole rocket body; the photoelectric detector is used for detecting the reflection spectrum of the reflected light obtained by the reflection of the fiber bragg grating network; the comprehensive control machine is used for processing the reflection spectrum according to a reconstruction algorithm to obtain a fiber grating reconstruction structure, and then comparing the fiber grating reconstruction structure with the original structure of the fiber grating to obtain the temperature change value and the temperature change position of the fiber grating with temperature change in the fiber grating network. The problems that in the prior art, a temperature sensor for a carrier rocket is limited in detection range, large in occupied space, complex in temperature information demodulation method and the like are solved.
Description
Technical Field
The invention relates to the technical field of rockets, in particular to a temperature detection system and method of a rocket.
Background
The rocket is one of the important tools for space exploration at present, and the temperature of each electric single-machine device and each structural component in each cabin section in the rocket determines to a certain extent whether the rocket can fly according to a normal orbit, so that temperature detection has a great influence on the safety of the whole rocket of the rocket.
The temperature of traditional rocket detects the temperature data that mainly gathers respectively according to the temperature sensor of each cabin section, and the data that will gather again is passed back to the combined control machine, and the sensor principle is mostly thermal resistance formula temperature sensor.
The detection method still has the following defects:
(1) The detection range is limited: at present, most of temperature sensors used by a carrier rocket can only measure the position of the sensor, but one cabin section of the rocket is usually provided with a certain number of sensors and cannot cover the whole cabin section;
(2) Detection device's bulky, heavy, appearance is unchangeable: the space of each cabin section of the rocket is limited, the traditional temperature detection device has a certain volume due to the fact that related electronic devices are arranged in the traditional temperature detection device, and the cabin sections are provided with temperature sensors, so that the space occupied by the cabin sections is large.
(3) The temperature information demodulation method is complex: aiming at the resistance-type temperature sensor which is widely applied at present, the temperature curve of the resistance-type temperature sensor presents nonlinearity, no analytic solution exists, demodulation of temperature information of the resistance-type temperature sensor depends on a table look-up mode more, the processing process is complex, the calculation time is increased, and the calculation efficiency is reduced.
In the prior art, the invention patent of publication No. CN110579227A discloses a time division/wavelength division multiplexing fiber grating distributed sensing system and method. The method gridds the fiber grating and utilizes the difference of reflected light time to position the detected position. However, this method uses a raster as a unit, and has low detection accuracy, and needs to compare the result of each scan with the result of the initial scan, which results in a long detection time.
The patent publication No. CN108895974B discloses a method for detecting the deformation state of a grating by establishing a structural deformation field, so as to achieve the effect of environmental monitoring. However, the method is complex and low in calculation efficiency, the method for establishing the deformation field is an interpolation method, the method is a numerical method, the precision of the method depends on the iteration times, the calculation complexity is increased, the calculation efficiency is reduced, and the numerical solution has the limitation of precision.
Disclosure of Invention
Aiming at the defects in the prior art, the embodiment of the invention provides a temperature detection system and method of a rocket, which solve the problems of limited detection range, large occupied space, complex temperature information demodulation method and the like of a temperature sensor for a carrier rocket in the prior art.
In a first aspect, in one embodiment, a rocket temperature detection system is provided, the rocket temperature detection system comprising: the system comprises a light source, an isolator, a coupler, a photoelectric detector, a comprehensive control machine and a fiber grating network;
the light source is connected with a first end of the coupler through an isolator, a second end of the coupler is connected with the grating network, a third end of the coupler is connected with the photoelectric detector, and the photoelectric detector is connected with the comprehensive controller;
the fiber grating network consists of a plurality of fiber gratings, and the fiber grating network penetrates through the whole rocket body;
the photoelectric detector is used for detecting a reflection spectrum of reflected light obtained by reflection of the fiber bragg grating network;
the integrated control machine is used for processing the reflection spectrum according to a reconstruction algorithm to obtain a fiber grating reconstruction structure, and then comparing the fiber grating reconstruction structure with an original fiber grating structure to obtain a temperature change value and a temperature change position of the fiber grating with temperature change in the fiber grating network.
In one embodiment, the light source is a broad spectrum light source;
the fiber grating adopts cascade fiber gratings with different central wavelengths, and the fiber grating is a fiber grating in a range to be measured and is a common fiber in a non-measuring range.
In one embodiment, the fiber gratings are fixed on each cabin section of the rocket through a reinforcing device, and the fiber gratings are connected with each other at the decomposition position of the rocket body through plug connectors.
In one embodiment, the isolator is used to provide unidirectional isolation between the light source and the coupler, reducing the adverse effects of the light source from reflected light or signals.
In an embodiment, the detection system further includes a data processing module respectively connected to the comprehensive controller and the photodetector, and the data processing module is configured to perform denoising processing on the reflection spectrum obtained by the photodetector.
In one embodiment, the data processing module includes an amplifying circuit, a filtering circuit, a waveform shaping circuit, a data acquisition circuit, and a data processing circuit.
In a second aspect, in an embodiment, a temperature detection method based on the temperature detection system in any one of the above embodiments is provided, the temperature detection method including:
s1: installing the fiber bragg grating network of the temperature detection system on each cabin section of the rocket body;
s2: the light source emits incident light, the incident light passes through the isolator and the coupler to reach the fiber grating, and the fiber grating is influenced by temperature change to generate refractive index change so as to change the characteristic of reflected light;
s3: the photoelectric detector detects the reflection spectrum of the reflected light obtained by the reflection of the fiber bragg grating;
s4: the comprehensive control machine processes the reflection spectrum, and obtains the temperature change value and the temperature change position of the fiber bragg grating with temperature change in the fiber bragg grating network through a reconstruction algorithm.
In one embodiment, the step S4 includes:
s41: reconstructing parameters of the fiber grating structure according to the reflection spectrum by using a reconstruction algorithm;
s42: determining a fiber bragg grating reconstruction structure according to the parameters of the fiber bragg grating structure;
s43: and comparing the fiber grating reconstruction structure with the fiber grating original structure, and further determining the temperature change value and the temperature change position of the fiber grating.
In one embodiment, the fiber grating structure is a refractive index perturbation of a fiber grating, and the parameters of the fiber grating structure include a period, a length, and an amplitude of the refractive index perturbation.
In one embodiment, the step S4 is preceded by:
and the data processing module is used for denoising the reflection spectrum.
Compared with the prior art, the invention has the following beneficial effects:
1. the fiber bragg grating network of the temperature sensing system penetrates through the whole rocket body to cover the whole rocket cabin section, so that the temperature detection of the whole rocket of the rocket can be realized, and the problem of limitation of the detection range of the traditional temperature detection sensor is solved;
2. compared with the traditional temperature detection device, the fiber bragg grating in the fiber bragg grating network has smaller volume and better scalability, can be adapted to the complex space structure in the rocket body, and solves the problem that the traditional temperature detection device is difficult to install in the rocket;
3. the invention utilizes the characteristics of the structure of the fiber grating, obtains the reconstruction structure of the fiber grating through the reconstruction algorithm, and then compares the reconstruction structure with the original structure of the fiber grating to obtain the position and the temperature change value of the fiber grating which are changed under the influence of temperature in the fiber grating network.
Drawings
Fig. 1 is an overall structural diagram of a temperature detection system according to an embodiment of the present invention.
Fig. 2 is a specific structural diagram of a temperature detection system according to an embodiment of the present invention.
Fig. 3 is an overall flowchart of a temperature detection method according to an embodiment of the present invention.
Fig. 4 is a specific flowchart of acquiring a temperature change position and a temperature change value in the temperature detection method according to the embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further described with reference to the drawings and the embodiments.
In a first aspect, in one embodiment, as shown in fig. 1 and 2, a temperature sensing system for a rocket is provided, the temperature sensing system comprising: the system comprises a light source, an isolator, a coupler, a photoelectric detector, a comprehensive control machine and a fiber grating network;
the light source is connected with a first end of the coupler through an isolator, a second end of the coupler is connected with the grating network, a third end of the coupler is connected with the photoelectric detector, and the photoelectric detector is connected with the comprehensive controller;
the fiber grating network consists of a plurality of fiber gratings, and the fiber grating network penetrates through the whole rocket body;
the photoelectric detector is used for detecting a reflection spectrum of reflected light obtained by reflection of the fiber bragg grating network;
the integrated control machine is used for processing the reflection spectrum according to a reconstruction algorithm to obtain a fiber grating reconstruction structure, and then comparing the fiber grating reconstruction structure with an original fiber grating structure to obtain a temperature change value and a temperature change position of the fiber grating with temperature change in the fiber grating network.
In the above embodiment, the fiber grating network is used for detecting the temperature of the rocket body, and compared with other temperature detection sensors, the wavelength modulation characteristic of the fiber grating can eliminate the interference caused by various light intensity fluctuations, so that the temperature detection system formed by the fiber grating has higher reliability and stability; furthermore, the self-reference characteristic of the grating fiber enables the grating fiber to be used for absolute measurement of temperature and temperature change positions;
the fiber bragg grating network of the temperature sensing system penetrates through the whole rocket body to cover the whole rocket cabin section, so that the temperature detection of the whole rocket of the rocket can be realized, and the problem of limitation of the detection range of the traditional temperature detection sensor is solved;
compared with the traditional temperature detection device, the fiber bragg grating in the fiber bragg grating network has smaller volume and better scalability, can be adapted to the complex space structure in the rocket body, and solves the problem that the traditional temperature detection device is difficult to install in the rocket;
the method has the advantages that the characteristics of the structure of the fiber grating are utilized, the reconstruction structure of the fiber grating is obtained through the reconstruction algorithm, and then the comparison is carried out with the original structure of the fiber grating, so that the position and the temperature change value of the fiber grating, which are influenced by the temperature, in the fiber grating network are obtained.
In one embodiment, the light source is a broad spectrum light source;
the fiber grating adopts cascade fiber gratings with different central wavelengths, and the fiber grating is a fiber grating in a range to be measured and a common fiber in a non-measuring range.
In the above embodiment, the wide-spectrum light source is a commonly used light source in the fiber grating sensor network, the wide-spectrum light source is a thermal light source, the spectrum width is greater than 30nm, and the wide-spectrum light source includes a light emitting diode, a super-radiation light emitting diode and an amplified spontaneous radiation light source;
in most optical detection systems, optical signals are converted into electrical signals through a photoelectric detector for further processing, and meanwhile, the noise of a light source is also converted into electrical noise through the photoelectric detector; broad spectrum light sources have two basic noise characteristics: firstly, the larger the light intensity of the light source is, the larger the noise signal of the light source is; secondly, the noise of the light source is in inverse proportion to the spectral width of the light source, namely the smaller the spectral width of the light source is, the larger the noise of the light source is; in wavelength division multiplexing, the second characteristic is important.
A plurality of cascade fiber gratings with different central wavelengths are written into the same optical fiber, so that different temperature measurement points can be distinguished, and the integrated design of the cascade fiber gratings is more flexible compared with that of a common fiber grating.
In one embodiment, the fiber gratings are fixed on each cabin section of the rocket through a reinforcing device, and the fiber gratings are connected with each other at the decomposition position of the rocket body through plug connectors.
In one embodiment, the isolator is used to provide unidirectional isolation between the light source and the coupler, reducing the adverse effects of the light source from reflected light or signals.
In an embodiment, the detection system further includes a data processing module respectively connected to the integrated controller and the photodetector, and the data processing module is configured to perform denoising processing on the reflection spectrum obtained by the photodetector.
In one embodiment, the data processing module includes an amplifying circuit, a filtering circuit, a waveform shaping circuit, a data acquisition circuit, and a data processing circuit.
In a second aspect, in an embodiment, as shown in fig. 3, a temperature detecting method based on the temperature detecting system in any one of the above embodiments is provided, where the temperature detecting method includes:
s1: installing the fiber grating network of the temperature detection system on each cabin section of the rocket body;
s2: the light source emits incident light, the incident light passes through the isolator and the coupler to reach the fiber grating, and the fiber grating is influenced by temperature change to generate refractive index change so as to change the characteristic of reflected light;
s3: the photoelectric detector detects the reflection spectrum of the reflected light obtained by the reflection of the fiber bragg grating;
s4: the comprehensive control machine processes the reflection spectrum, and obtains the temperature change value and the temperature change position of the fiber bragg grating with temperature change in the fiber bragg grating network through a reconstruction algorithm.
In one embodiment, as shown in fig. 4, the step S4 includes:
s41: reconstructing parameters of the fiber grating structure according to the reflection spectrum by using a reconstruction algorithm;
the fiber grating structure is the refractive index perturbation of the fiber grating, and the parameters of the fiber grating structure comprise the period, the length and the amplitude of the refractive index perturbation.
According to the coupled mode theory, the reflection spectrum of the fiber grating is as follows:
the effective refractive index of the fiber grating is determined by the length, amplitude and period. Where κ is the lateral coupling coefficient.
By the characteristics of the reflection spectrum, the period with the refractive index is obtained as follows:
wherein n is m And n s The refractive index of the cladding and the refractive index of the fiber core of the fiber grating;
the magnitude of the effective index is:
the effective refractive index length is:
formula (4)
S42: determining a fiber bragg grating reconstruction structure according to the parameters of the fiber bragg grating structure;
before reconstruction, the fiber grating of the fiber grating network is segmented into i1, i2 and i3 in sequence, i 8230in sequence, and the refractive index perturbation of each segment of the fiber grating can be expressed as delta n i1 (z) the structural parameter of the refractive index perturbation is expressed as Λ i1 ，L i1 ，δn 0i1 The reflection spectrum of which can be represented as R i ；
According to the formulas (1), (2) and (3), the reconstructed structural parameters are respectively Lambda i2 ，L i2 ，δn 0i2 (ii) a The refractive index perturbation Δ n (z) is determined by Λ, L, δ n 0 Determining so as to obtain the refractive index perturbation delta n after each section of the fiber grating is reconstructed i2 (z) is formula (5):
s43: and comparing the fiber grating reconstruction structure with the fiber grating original structure, and further determining the temperature change value and the temperature change position of the fiber grating.
The original structure of the grating fiber is a known quantity, and is shown as formula (6):
wherein, δ n 0 Is the amplitude of the refractive index perturbation; b is fringe visibility; q (z) is the graded envelope of the refractive index perturbation, also commonly referred to as the apodization or apodization function; Λ is the period;
is the phase shift point.
The center wavelength of the fiber grating is:
λ 0 ＝Λ(n m +n s +2δ 0 ) Formula (7)
The change amount DeltaLambda of the center wavelength when subjected to the change DeltaT of the temperature 0 Satisfy the requirements of
Δλ 0 ＝λ 0 (α + σ) Δ T formula (8)
Where α represents a thermo-optic coefficient of the fiber grating and σ represents a thermal expansion coefficient of the fiber grating.
Δ n in the formula (5) i2 Δ n in (z) and formula (6) i1 (z) are subtracted to give Δ (z). For Δ (z), where z is a value other than 0, all are temperature change values, the location where the temperature change can be determined is made.
In one embodiment, the step S4 is preceded by:
and the data processing module is used for denoising the reflection spectrum.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (10)
1. A rocket temperature sensing system, said sensing system comprising: the system comprises a light source, an isolator, a coupler, a photoelectric detector, a comprehensive control machine and a fiber grating network;
the light source is connected with a first end of the coupler through an isolator, a second end of the coupler is connected with the grating network, a third end of the coupler is connected with the photoelectric detector, and the photoelectric detector is connected with the comprehensive control machine;
the fiber grating network consists of a plurality of fiber gratings, and the fiber grating network penetrates through the whole rocket body;
the photoelectric detector is used for detecting a reflection spectrum of reflected light obtained by reflection of the fiber bragg grating network;
the integrated control machine is used for processing the reflection spectrum according to a reconstruction algorithm to obtain a fiber grating reconstruction structure, and then comparing the fiber grating reconstruction structure with an original fiber grating structure to obtain a temperature change value and a temperature change position of the fiber grating with temperature change in the fiber grating network.
2. A rocket temperature sensing system as recited in claim 1, wherein:
the light source is a wide-spectrum light source;
the fiber grating adopts cascade fiber gratings with different central wavelengths, and the fiber grating is a fiber grating in a range to be measured and a common fiber in a non-measuring range.
3. A rocket temperature sensing system as recited in claim 1, wherein:
the fiber gratings are fixed on each cabin section of the rocket through a reinforcing device, and the fiber gratings are mutually connected at the decomposition part of the rocket body through plug connectors.
4. A rocket temperature sensing system as recited in claim 1, wherein:
the isolator is used for forming one-way isolation between the light source and the coupler, and adverse effects of reflected light or signals on the light source are reduced.
5. A rocket temperature detecting system as recited in claim 1, wherein said detecting system further comprises a data processing module respectively connected to said integrated control machine and said photodetector, said data processing module is adapted to de-noise the reflection spectrum obtained by said photodetector.
6. A rocket temperature sensing system as recited in claim 5, wherein said data processing module comprises amplification circuitry, filtering circuitry, waveform shaping circuitry, data acquisition circuitry, and data processing circuitry.
7. A temperature detection method based on the temperature detection system of the rocket according to claim 1, wherein the detection method comprises:
s1: installing the fiber bragg grating network of the temperature detection system on each cabin section of the rocket body;
s2: the light source emits incident light, the incident light passes through the isolator and the coupler to reach the fiber grating, and the fiber grating is influenced by temperature change to generate refractive index change so as to change the characteristic of reflected light;
s3: the photoelectric detector detects the reflection spectrum of the reflected light obtained by the reflection of the fiber bragg grating;
s4: the comprehensive control machine processes the reflection spectrum, and obtains the temperature change value and the temperature change position of the fiber bragg grating with temperature change in the fiber bragg grating network through a reconstruction algorithm.
8. The temperature detecting method according to claim 7, wherein the step S4 includes:
s41: reconstructing parameters of the fiber grating structure according to the reflection spectrum by using a reconstruction algorithm;
s42: determining a fiber bragg grating reconstruction structure according to the parameters of the fiber bragg grating structure;
s43: and comparing the fiber grating reconstruction structure with the fiber grating original structure to further determine the temperature change value and the temperature change position of the fiber grating.
9. The method according to claim 8, wherein the fiber grating structure is a refractive index perturbation of the fiber grating, and the parameters of the fiber grating structure include a period, a length, and an amplitude of the refractive index perturbation.
10. The temperature detecting method according to claim 8, wherein the step S4 is preceded by:
and the data processing module is used for denoising the reflection spectrum.
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