Method and system for compressing spectral data volume of aircraft

Abstract

The invention discloses a method and system for compressing the spectral data volume of an aircraft, and the method comprises the steps: receiving incident spectral data; performing spectral conversion on the incident spectral data to obtain a spectral response value; establishing a mapping relation between the spectral response value and the incident spectral data; according to the mapping relation between the spectral response value and the incident spectral data, the corresponding incident spectral data are solved according to the spectral response value obtained through actual detection. According to the invention, the problem that the spectral data demand on the aircraft is not matched with the data channel capacity in the prior art is solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of spectral data collection on aircraft, and in particular to a method and system for compressing the amount of spectral data of an aircraft. Background Art

[0002] Spectral detection technology can reflect the structural composition information of the object being measured, so it has important application value in the fields of chemical sensing and environmental analysis. Spectral detection is achieved by detecting and analyzing the incident light through a spectrometer. Traditional spectrometers use spatial spectroscopy (dispersion principle) or temporal spectroscopy (Michelson interference spectroscopy) to detect the light intensity at each wavelength on the spectral curve. This direct sampling method determines that the accuracy of the spectral data depends on the number of sampling wavelengths of the spectrum. The larger the number of sampling wavelengths, the higher the detection accuracy of the spectrum, but this also means a larger amount of spectral data.

[0003] It is a mature scientific research method to carry a spectrometer on an aircraft to realize remote sensing detection of hydrology, hills, and forests. Usually, the spectral data collected by the aircraft can be wirelessly transmitted through the telemetry system or stored in the aircraft's memory through a wired method, and then the memory is recovered for post-analysis. Regardless of which solution is used, the channel capacity for data transmission or storage is limited. However, with the improvement of scientific research requirements for spectral detection accuracy, the increasing amount of spectral data is no longer matched with the channel capacity that can be provided on the aircraft. Therefore, in order to solve the problem of large amount of spectral data collected on aircraft, it is urgent to develop new methods for spectral data collection on aircraft. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a method and system for compressing the amount of aircraft spectral data, and to solve the problem in the prior art that the amount of spectral data required on the aircraft does not match the data channel capacity.

[0005] The object of the present invention is achieved through the following technical scheme: a method for compressing the amount of aircraft spectral data, comprising: receiving incident spectral data; spectrally converting the incident spectral data to obtain spectral response values; establishing a mapping relationship between the spectral response values ​​and the incident spectral data; and solving the corresponding incident spectral data according to the spectral response values ​​actually detected through the mapping relationship between the spectral response values ​​and the incident spectral data.

[0006] In the above method for compressing the amount of aircraft spectral data, the incident spectral data is spectrally converted by a reconstruction spectrometer to obtain a spectral response value.

[0007] In the above method for compressing the amount of aircraft spectral data, the incident spectral data is:

[0008]

[0009] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n The light intensity value, n is the total number of wavelengths.

[0010] In the above method for compressing the amount of aircraft spectral data, the filter curve array of the reconstruction spectrometer is:

[0011]

[0012] Among them, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under the condition, i=1, 2...m, j=1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0013] In the above method for compressing the amount of aircraft spectral data, the spectral response value is obtained by the following formula:

[0014]

[0015] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n Light intensity value, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under i is the spectral response value under the i-th filter, i = 1, 2...m, j = 1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0016] A system for compressing the amount of aircraft spectral data includes: a first module for receiving incident spectral data; a second module for performing spectral conversion on the incident spectral data to obtain spectral response values; a third module for establishing a mapping relationship between the spectral response values ​​and the incident spectral data; and a fourth module for solving the corresponding incident spectral data according to the spectral response values ​​actually detected through the mapping relationship between the spectral response values ​​and the incident spectral data.

[0017] In the above-mentioned system for compressing the amount of aircraft spectral data, incident spectral data is spectrally converted by a reconstruction spectrometer to obtain a spectral response value.

[0018] In the above system for compressing the amount of aircraft spectral data, the incident spectral data is:

[0019]

[0020] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n The light intensity value, n is the total number of wavelengths.

[0021] In the above-mentioned system for compressing the amount of aircraft spectral data, the filter curve array of the reconstruction spectrometer is:

[0022]

[0023] Among them, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under the condition, i=1, 2...m, j=1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0024] In the above system for compressing the aircraft spectral data volume, the spectral response value is obtained by the following formula:

[0025]

[0026] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n Light intensity value, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under i is the spectral response value under the i-th filter, i = 1, 2...m, j = 1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] The present invention can achieve 2 times or even greater spectral data compression on an aircraft without sacrificing spectral resolution, solving the problem of mismatch between spectral data demand and data channel capacity on an aircraft in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0030] Figure 1It is a schematic diagram of the principle of realizing spectral data compression on an aircraft by utilizing the response value of a spectrometer provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0031] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0032] Figure 1 FIG. 1 is a schematic diagram of the principle of using the spectrometer response value to realize spectral data compression on an aircraft according to an embodiment of the present invention. Figure 1 As shown, the method includes:

[0033] receiving incident spectral data;

[0034] The incident spectral data is spectrally transformed to obtain a spectral response value; specifically, the incident spectral data is spectrally transformed through a reconstruction spectrometer to obtain a spectral response value;

[0035] Establishing a mapping relationship between the spectral response value and the incident spectral data;

[0036] Through the mapping relationship between the spectral response value and the incident spectral data, the corresponding incident spectral data is solved according to the spectral response value actually detected.

[0037] The incident spectrum data is:

[0038]

[0039] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n The light intensity value, n is the total number of wavelengths.

[0040] The filter curve array of the reconstruction spectrometer is:

[0041]

[0042] Among them, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under the condition, i=1, 2...m, j=1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0043] The spectral response value is obtained by the following formula:

[0044]

[0045] Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n Light intensity value, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under i is the spectral response value under the i-th filter, i = 1, 2...m, j = 1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

[0046] The principle of computational spectroscopy is to use a filter array and use the following formula to convert the incident spectrum into the response value obtained after the action of different filters.

[0047]

[0048] Among them, each row of the matrix T is the transmission spectrum function of a filter, the number of wavelengths is n, the total number of filters is m, the vector x is the incident spectrum, and each value of the vector I represents the light intensity response value obtained by each detector. From the matrix knowledge, it can be known that under the premise that the filter transmission matrix (T) is known, when the corresponding response value (I) of each filter is measured, the spectral information of the incident light can be obtained by inverse solution (x=T -1 I). This process is called spectrum reconstruction. Therefore, only the response value vector information needs to be obtained on the aircraft, and the original incident spectrum information can be obtained through spectrum reconstruction afterwards.

[0049] Because different incident spectra will act on the same filter array, the one-to-one correspondence between different incident spectra and response vectors can be trained in advance, thereby shortening the length of the response value vector, that is, compressing the data collected on the aircraft. Ultimately, it is possible to obtain more accurate spectral data by inverting with only a small number of filters.

[0050] For example, for the spectral data of 405-700nm, assuming that a light intensity data is taken every 5nm, then this spectral curve is in the form of a 60*1 vector. According to the traditional spectral data transmission method, it will be necessary to transmit 60*1 data. After using the spectrometer based on the principle of computational spectroscopy on the aircraft, only a certain number of filter array designs (for example, 30 filters) are required. Combined with the prior filter array training and learning, the spectral data with 60*1 can be obtained after the fact. Therefore, this method can achieve 2 times or even greater spectral data compression under the condition of the same spectral sampling frequency.

[0051] The present embodiment also provides a system for compressing the amount of aircraft spectral data, the system comprising: a first module for receiving incident spectral data; a second module for performing spectral conversion on the incident spectral data to obtain spectral response values; a third module for establishing a mapping relationship between the spectral response values ​​and the incident spectral data; and a fourth module for obtaining corresponding incident spectral data according to the spectral response values ​​actually detected through the mapping relationship between the spectral response values ​​and the incident spectral data.

[0052] This embodiment can achieve 2 times or even greater spectral data compression on an aircraft without sacrificing spectral resolution, thereby solving the problem of mismatch between spectral data demand and data channel capacity on an aircraft in the prior art.

[0053] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A method for compressing the amount of aircraft spectral data, characterized in that include: receiving incident spectral data; The incident spectral data is spectrally transformed to obtain a spectral response value; Establishing a mapping relationship between the spectral response value and the incident spectral data; Through the mapping relationship between the spectral response value and the incident spectral data, the corresponding incident spectral data is solved according to the spectral response value actually detected.

2. The method for compressing aircraft spectral data according to claim 1, characterized in that: The incident spectral data is spectrally transformed through a reconstruction spectrometer to obtain a spectral response value.

3. The method for compressing aircraft spectral data according to claim 1, characterized in that: The incident spectrum data is: Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n The light intensity value, n is the total number of wavelengths.

4. The method for compressing aircraft spectral data according to claim 2, characterized in that: The filter curve array of the reconstruction spectrometer is: Among them, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under the condition, i=1, 2...m, j=1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

5. The method for compressing aircraft spectral data according to claim 1, characterized in that: The spectral response value is obtained by the following formula: Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n Light intensity value, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under i is the spectral response value under the i-th filter, i = 1, 2...m, j = 1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

6. A system for compressing the amount of aircraft spectral data, characterized in that include: A first module is used to receive incident spectral data; The second module is used to perform spectral conversion on the incident spectral data to obtain a spectral response value; The third module is used to establish a mapping relationship between the spectral response value and the incident spectral data; The fourth module is used to obtain corresponding incident spectral data according to the spectral response values ​​actually detected through the mapping relationship between the spectral response values ​​and the incident spectral data.

7. The system for compressing aircraft spectral data according to claim 6, characterized in that: The incident spectral data is spectrally transformed through a reconstruction spectrometer to obtain a spectral response value.

8. The system for compressing aircraft spectral data according to claim 6, characterized in that: The incident spectrum data is: Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n The light intensity value, n is the total number of wavelengths.

9. The system for compressing aircraft spectral data according to claim 7, characterized in that: The filter curve array of the reconstruction spectrometer is: Among them, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under the condition, i=1, 2...m, j=1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

10. The system for compressing aircraft spectral data according to claim 6, characterized in that: The spectral response value is obtained by the following formula: Among them, x(λ1) is the light intensity value with wavelength λ1, x(λ2) is the light intensity value with wavelength λ2, and x(λ n ) is the wavelength λ n Light intensity value, T i (λ j ) is the value of the ith filter at wavelength λ j The transmittance under i is the spectral response value under the i-th filter, i = 1, 2...m, j = 1, 2...n, m is the total number of filters, and n is the total number of wavelengths.

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