A thermoelectric joint test method for radome in high-speed flight environment

Abstract

The present invention discloses a thermoelectric joint test method for radomes facing a high-speed flight environment. The radome is heated by a heating system, and when the radome reaches a predetermined temperature value, the heating of the radome is stopped. The heat preservation system keeps the radome at the predetermined temperature value, and a thermoelectric joint test is carried out in an existing anechoic chamber. The temperature data of the radome during the test process are recorded in real time, and the temperature data of the radome during the thermoelectric joint test process are reconstructed to obtain a reconstructed temperature field of the radome, laying a foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance under service environments.

Description

Technical Field

[0001] The present invention belongs to the technical field of combined thermoelectric testing of radomes, and particularly relates to a method for combined thermoelectric testing of radomes for high-speed flight environments. Background Art

[0002] When a missile-borne radome flies at hypersonic speed, it faces the problem of aerodynamic heating. The intense friction between the outside of the radome and the air causes the surface temperature of the radome to rise sharply. Most radomes are made of inorganic materials, and the dielectric constant and loss tangent of these materials are affected by temperature changes. The change of the dielectric properties of the materials ultimately affects the electrical performance of the radome. Therefore, the electrical performance of the radome must be tested and evaluated before it is put into service.

[0003] Traditional evaluation of the electrical performance of radomes mainly uses a radome electrical performance test system to conduct tests at room temperature. However, during actual service, due to aerodynamic heating caused by speed increase, the surface temperature of the radome will increase significantly, and the local temperature may exceed a thousand degrees. The electrical performance test under room temperature conditions often cannot truly reflect its service performance. Therefore, it is necessary to simulate the real working environment of the radome for evaluation, that is, the high-temperature electrical performance evaluation of the radome.

[0004] The evaluation of the electrical performance of radomes in high-temperature environments is mainly to add thermal tests on the basis of traditional radome electrical performance tests. However, due to the limitations of microwave anechoic chambers, there is little research on the combined thermoelectric testing of radomes. The public patent CN112557798A provides a phased array antenna-radome electrical performance test device and test method. In this invention, the test device includes a transmitting signal source, a transmitting antenna, a test tooling, a turntable, a turntable control system, a phased array antenna, and a wave control machine. The transmitting signal source emits a beam through the transmitting antenna. The phased array antenna and the tested radome are installed on the test tooling. First, the radome is heated at high temperature, and after it cools down to room temperature, the electrical performance test is carried out, and the evaluation is carried out by comparing the electrical performance of the radome before and after high temperature. However, this method separates the electrical test and the thermal test, and cannot truly reflect the dynamic influence mechanism of temperature factors on electrical performance in the service environment; the public patent CN114065473A provides a method for comprehensive surface radar performance analysis based on force-thermo-electric coupling. This invention includes thermal analysis, thermo-electric coupling analysis, force-thermal coupling analysis, and force-thermo-electric coupling analysis. The radome is subjected to thermal-electric coupling simulation through simulation software. However, the simulation requires high-performance computing resources and there is still a certain objective gap with the actual situation. There may be a situation where the simulation results are qualified but unqualified in the actual flight state. Summary of the Invention

[0005] In order to solve the above problems existing in the prior art, the present invention provides a method for combined thermoelectric testing of radomes for high-speed flight environments.

[0006] The technical problem to be solved by the present invention is achieved by the following method, including the following steps:

[0007] Heat the radome through a heating system; stop heating the radome when it reaches a predetermined temperature value; insulate the radome that has reached the predetermined temperature value through an insulation system, and conduct a combined thermoelectric test on the insulated radome; record the temperature data of the radome in real time during the combined thermoelectric test through a first temperature measurement structure, and reconstruct the temperature data to obtain a reconstructed temperature field of the radome.

[0008] Furthermore, the heating system includes a heating sleeve, a console for controlling the heating sleeve, and a second temperature measurement structure; the second temperature measurement structure includes a demodulator for real-time measurement and analysis of the signals of fiber Bragg grating temperature sensors, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

[0009] Furthermore, the heating sleeve includes a lining layer, a heating layer, an insulating layer, and an outer layer.

[0010] Furthermore, the lining layer is a quartz cloth, the heating layer is a fiberglass cloth uniformly provided with heating wires, the insulating layer is a heat-insulating nano composite insulating blanket, and the outer layer is a composite aluminum foil cloth.

[0011] Furthermore, the insulation system includes an insulation sleeve and a first temperature measurement structure.

[0012] Furthermore, the insulation sleeve includes an aerogel inner layer and a quartz fiber outer layer.

[0013] Furthermore, the first temperature measurement structure includes a demodulator for real-time measurement and analysis of the signals of fiber Bragg grating temperature sensors, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

[0014] Furthermore, several fiber Bragg grating temperature sensors are divided into two groups and are uniformly arranged above and below the inner wall of the radome respectively, and the spacing distance of the group of fiber Bragg grating temperature sensors arranged above the inner wall of the radome is less than the spacing distance of the group of fiber Bragg grating temperature sensors arranged below the inner wall of the radome.

[0015] Furthermore, a heat insulation cap for blocking internal heat radiation and heat conduction is provided inside the radome.

[0016] Furthermore, reconstructing the temperature data to obtain a reconstructed temperature field of the radome further includes:

[0017] Select the temperature data of the radome at several moments during the combined thermoelectric test. Through principal component analysis (PCA), the temperature data is separated in space and time to obtain discrete spatial modes and low-order time coefficients. Cubic spline interpolation (CS) is performed on the discrete spatial modes to obtain continuous spatial basis functions. The low-order time coefficients are denoised by a Kalman filter (KF) to obtain optimal time coefficients. The reconstructed radome temperature field is obtained based on the continuous spatial basis functions and the optimal time coefficients.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0019] A combined thermoelectric test method for a radome facing a high-speed flight environment provided by the present invention. On the one hand, through the structural design of heating the radome with a heating sleeve and insulating the radome with a thermal insulation sleeve, and at the same time adopting dynamic monitoring of real-time temperature measurement by fiber Bragg grating temperature sensors, the high-temperature electrical performance test of the radome can be directly carried out in the existing anechoic chamber. On the other hand, the present invention proposes a method for reconstructing the radome temperature field, accurately reconstructing the complete radome temperature field through partial discrete temperature measurement points, laying a foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance in the service environment.

[0020] The following will further elaborate on the present invention in conjunction with the accompanying drawings and embodiments. Brief Description of the Drawings

[0021] Figure 1 is a combined thermoelectric test method for a radome facing a high-speed flight environment provided by the present invention;

[0022] Figure 2 is a schematic diagram of the heating system provided by an embodiment of the present invention;

[0023] Figure 3 is a schematic diagram of the arrangement of fiber Bragg grating temperature sensors provided by an embodiment of the present invention;

[0024] Figure 4 is a schematic cross-sectional view of the heating sleeve sleeved on the radome provided by an embodiment of the present invention;

[0025] Figure 5 is a schematic diagram of the arrangement interval of fiber Bragg grating temperature sensors provided by an embodiment of the present invention;

[0026] Figure 6 is a schematic diagram of the combined thermoelectric test of the radome provided by an embodiment of the present invention;

[0027] Figure 7 is a schematic diagram of the thermal insulation system provided by an embodiment of the present invention;

[0028] Figure 8 is a schematic cross-sectional view of the thermal insulation sleeve sleeved on the radome provided by an embodiment of the present invention;

[0029] Figure 9 It is the flow chart of the algorithm for reconstructing the temperature field of the radome provided by the present invention;

[0030] Figure 10 It is the temperature rise curve of the temperature measurement points during the heating process provided by the embodiment of the present invention;

[0031] Figure 11 It is the temperature drop curve of the temperature measurement points with and without the heat preservation sleeve provided by the embodiment of the present invention;

[0032] Figure 12(a) is the schematic diagram of the position of the temperature measurement points in the radome provided by the embodiment of the present invention;

[0033] Figure 12(b) is the schematic diagram of the position of the temperature measurement points in the space coordinate system provided by the embodiment of the present invention;

[0034] Figure 13(a) is the cloud map of the first-order continuous spatial basis function obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0035] Figure 13(b) is the cloud map of the second-order continuous spatial basis function obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0036] Figure 13(c) is the cloud map of the third-order continuous spatial basis function obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0037] Figure 13(d) is the cloud map of the fourth-order continuous spatial basis function obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0038] Figure 13(e) is the cloud map of the fifth-order continuous spatial basis function obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0039] Figure 14(a) is the cloud map of the reconstructed temperature field of the radome at the 5th minute provided by the embodiment of the present invention;

[0040] Figure 14(b) is the cloud map of the reconstructed temperature field of the radome at the 10th minute provided by the embodiment of the present invention;

[0041] Figure 14(c) is the cloud map of the reconstructed temperature field of the radome at the 20th minute provided by the embodiment of the present invention;

[0042] Figure 14(d) is the cloud map of the reconstructed temperature field of the radome at the 36th minute provided by the embodiment of the present invention;

[0043] Figure 15 It is the verification position reconstruction - measured comparison chart provided by the embodiment of the present invention;

[0044] Figure 16 It is the MAE and RMSE of the reconstructed temperature at the verification position provided by the embodiment of the present invention. Detailed implementation manners

[0045] In order to further elaborate on the technical means and effects adopted by the present invention to achieve the intended invention purpose, the following will combine the accompanying drawings and specific implementation manners to detail the solution according to the present invention.

[0046] The foregoing and other technical contents, features and effects of the present invention can be clearly presented in the following detailed description in conjunction with the accompanying drawings. Through the description of the specific implementation manners, a more in-depth and specific understanding of the technical means and effects adopted by the present invention to achieve the intended purpose can be obtained. However, the attached drawings are only for reference and explanation, and are not used to limit the technical solution of the present invention.

[0047] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variant are intended to cover non-exclusive inclusion, so that an article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of another identical element in the article or device including the said element.

[0048] As Figure 1 shown, it is a thermoelectric combined test method for radome facing high-speed flight environment provided by an embodiment of the present invention:

[0049] Arrange a heating system in an existing microwave anechoic chamber, sleuth a heating sleeve in the heating system on the outer surface of the radome, load a heat insulation cap at the bottom of the inner wall of the radome, and control the heating of the radome by the heating sleeve through the console in the heating system.

[0050] As Figure 2 shown, the heating system includes a heating sleeve, a console for controlling the heating sleeve and a second temperature measurement structure. Among them, the second temperature measurement structure includes a demodulator for real-time measuring and analyzing the signals of fiber Bragg grating temperature sensors, a computer and several fiber Bragg grating temperature sensors connected in sequence; as Figure 3 shown, several fiber Bragg grating temperature sensors are arranged in a spiral shape on the inner wall of the radome through high-temperature resistant tapes. Preferably, the high-temperature resistant tapes are polyimide tapes or quartz fiber tapes.

[0051] The heating jacket includes a lining layer, a heating layer, a heat-insulating layer, and an outer layer. The lining layer is made of quartz cloth, the heating layer is a fiberglass cloth with heating wires evenly arranged to provide uniform heating for the heating jacket, the heat-insulating layer is a heat-insulating nano composite thermal blanket, and the outer layer is a composite aluminum foil cloth; the control console is connected to the heating jacket to control the temperature of the heating jacket; the heat-insulating cap that blocks internal thermal radiation and heat conduction is adhered to the bottom of the inner wall of the radome through high-temperature resistant glue, as Figure 4 shown, which is a schematic cross-sectional view of the heating jacket sleeved on the radome.

[0052] The temperature change of the radome is measured in real time by the fiber Bragg grating temperature sensors arranged spirally on the inner wall of the radome. When the temperature of the radome reaches the predetermined temperature value, the control console controls the heating jacket to stop heating the radome; preferably, the predetermined temperature value is 350 °C.

[0053] A number of fiber Bragg grating temperature sensors are divided into two groups and are evenly arranged above and below the inner wall of the radome respectively, as Figure 5 shown. Considering that the circumference of the root of the radome is large and the circumference of the head is small, in order to comprehensively monitor the wall temperature of the radome, the grating areas are divided into two groups, and the interval distance of the group of fiber Bragg grating temperature sensors arranged above the inner wall of the radome is less than the interval distance of the group of fiber Bragg grating temperature sensors arranged below the inner wall of the radome;

[0054] Preferably, the demodulator for real-time dynamically monitoring the wall temperature of the radome by real-time decoding the central wavelength of the grating area selects MOI si155, and its bandwidth is 160 nm; in this embodiment, 20 fiber Bragg grating temperature sensors are set according to the inner wall shape of the radome and the bandwidth of the demodulator. The grating interval between the fiber Bragg grating sensors arranged in the lower part of the inner wall of the radome in the first group is 200 mm, the grating interval between the fiber Bragg grating sensors arranged in the upper part of the inner wall of the radome in the second group is 50 mm, the interval between the first group and the second group of grating areas is 200 mm, and the grating area length of the fiber Bragg grating temperature sensors is all 10 mm.

[0055] After the radome is heated, remove the heating jacket and quickly put on the heat-insulating jacket, as Figure 6 shown. Install the radome with the heat-insulating jacket on the turntable in the existing microwave anechoic chamber, and keep the radome at the predetermined temperature value through the heat-insulating jacket in the heat-insulating system, and conduct thermoelectric combined tests on the heat-insulated radome in the microwave anechoic chamber.

[0056] As Figure 7 shown, the heat-insulating system includes a heat-insulating jacket and a first temperature measurement structure. Among them, the first temperature measurement structure includes a demodulator for real-time measuring and analyzing the signals of fiber Bragg grating sensors, a computer, and a number of fiber Bragg grating temperature sensors connected in sequence.

[0057] The thermal insulation cover includes an aerogel inner layer and a quartz fiber outer layer. The aerogel used in the inner layer has a dielectric constant of 1.01 and a loss tangent of 0.005. The outer layer is wrapped with quartz fiber, and the thermal insulation cover has the same shape as the radome. When the thermal insulation cover is sleeved on the surface of the radome, the inner layer of the thermal insulation cover is closely fitted with the outer layer of the radome. As Figure 8 shown, it is a schematic cross-sectional view of the thermal insulation cover sleeved on the radome.

[0058] The temperature data of the radome during the combined thermal and electrical test is measured in real time by the fiber Bragg grating temperature sensors in the first temperature measurement structure. The demodulator decodes the central wavelength of the grating area in real time to dynamically monitor the temperature of the radome in real time. The computer records the temperature data of the radome during the combined thermal and electrical test in real time, and reconstructs the temperature data to obtain the reconstructed temperature field of the radome.

[0059] When reconstructing the temperature data to obtain the reconstructed temperature field of the radome, each fiber Bragg grating temperature sensor is used as a temperature measurement point. As Figure 9 shown, the temperature data of the radome obtained at some temperature measurement points at several moments during the combined thermal and electrical test is selected. The principal component analysis (PCA) is used to separate the temperature data in space and time to obtain discrete spatial modes and low-order time coefficients. The cubic spline interpolation (CS) is performed on the discrete spatial modes to obtain continuous spatial basis functions. The Kalman filter (KF) is used to denoise the low-order time coefficients to obtain the optimal time coefficients. The reconstructed temperature field of the radome is obtained according to the continuous spatial basis functions and the optimal time coefficients.

[0060] Since the temperature field distribution of the radome is closely related to time and space, the temperature field of the radome is reconstructed by the method of separating space and time. Then the temperature field of the radome at any moment is expressed as:

[0061]

[0062] In the formula, s is the spatial coordinate of the grid point, t is the time, is the spatial basis function related to the model, and α i (t) is the time mode coefficient related to time.

[0063] The above formula is expanded into an approximate finite-term form, that is, the temperature field of the radome in the actual working environment is expressed as:

[0064]

[0065] In the formula, n represents the number of spatial basis functions whose proportion of the energy containing spatial information is greater than 99%.

[0066] To obtain the dominant spatial basis functions the following optimization objective is formed:

[0067]

[0068] Where, is the L2 norm of T(s,t), is the definition of its set average, L is the length of the set, L 2 (Ω) represents the space of square integrable functions defined on the set Ω, st(·) indicates that the contents in the brackets are constrained, and the orthogonal constraint condition Ensures that the spatial basis functions associated with the model uniqueness.

[0069] The corresponding Lagrangian constraint Γ is:

[0070]

[0071] Among them, λ i represents the Lagrange multiplier.

[0072] The temperatures measured at some temperature measurement points can be expressed as the following matrix:

[0073]

[0074] Where, T (i) represents the i-th temperature vector.

[0075] Then the above Lagrangian constraints are equivalent to:

[0076]

[0077] right Taking the derivative, we can get:

[0078]

[0079] Arranged:

[0080]

[0081] Will Sorted in descending order, the energy proportion contained in the first n modes can be expressed as:

[0082]

[0083] When the energy contained in the first n modes accounts for more than 99%, the infinite-dimensional system can be approximated by the first n modes. At this time, the temperature field of the radome can be expressed as:

[0084]

[0085] Principal component analysis selection T T The first n characteristic roots of T λ1,λ2,…,λ nThe corresponding unit eigenvector As the projection direction, when reducing the original data to n dimensions, only need to find T T The eigenvectors corresponding to the n largest eigenvalues of T form the projection matrix, and then use Dimensionality reduction can be achieved, discrete spatial modes and corresponding low-order time coefficients can be obtained. By performing cubic spline interpolation on the discrete spatial modes, continuous spatial basis functions can be obtained.

[0086] Since there is noise in the sensor measurement values and the reconstruction error is large under the influence of noise, a Kalman filter is introduced to denoise the low-order time coefficients after spatio-temporal separation. Then the time coefficients in the real working environment can be expressed as:

[0087]

[0088] Where represents the time coefficient, represents the optimal time coefficient, P - (t) represents the prior covariance matrix, K(t) represents the Kalman filter gain, P(t) represents the state covariance matrix, A represents the state transition matrix, H represents the observation matrix, z i represents the observed value at the current moment, Q represents the system noise covariance matrix, and R represents the measurement noise covariance matrix.

[0089] The reconstructed temperature field can be calculated according to and as follows:

[0090]

[0091] The accuracy of the reconstructed temperature field is measured by the mean absolute error (MAE) and root mean square error (RMSE) of the temperature at the verification positions. Specifically:

[0092]

[0093] In the formula, is the reconstructed temperature field, T i (s,t) is the test state temperature field, and m is the number of grids.

[0094] Before the thermoelectric joint test of the radome, a "heating - heat preservation - temperature measurement" thermal test is first carried out to ensure the feasibility of the "heat preservation - dynamic monitoring" scheme. The console sets the heating temperature to 400 °C, and the radome is heated with a heating jacket. After 37 minutes of heating, the overall temperature of the radome reaches above 350 °C, and at this time, the temperature of some temperature measurement points reaches 400 °C. The temperature rise curve of the temperature measurement points during the heating process is as Figure 10 shown.

[0095] By comparing the temperature drop of the radome under two conditions: with a heat preservation cover (condition one) and without a heat preservation cover (condition two), the heat preservation effect of the "heat preservation cover" structure is analyzed. The time for the electrical performance test of the radome is 35 minutes. Therefore, compare the temperature drop of condition one and condition two within 35 minutes. At the same time, since there are 20 temperature measurement points, 5 temperature measurement points are randomly selected for comparison. The temperature drop curve is as Figure 11 shown. After 36 minutes in condition one, the wall temperature of the radome can still reach about 300 °C, with a temperature drop of 25.11%; after 36 minutes in condition two, the wall temperature of the radome is only about 75 °C, with a temperature drop of 81.5%. The heat preservation effect of the radome with a heat preservation cover - heat insulation cap is significantly better than that without a heat preservation cover - heat insulation cap. The heat preservation effect of the present invention is obvious and can effectively meet the requirements of the thermoelectric joint test of the radome.

[0096] Preferably, a total of 20 fiber Bragg grating temperature sensors are arranged on the inner wall of the radome in the present invention as 20 temperature measurement points. 15 of the temperature measurement points are selected as reconstruction points in the present invention to reconstruct the temperature field of the radome with the temperature data at 36 moments, and the remaining 5 temperature measurement points are used as verification points to verify the accuracy of the reconstructed temperature field. The positions of the temperature measurement points in the radome and their positions in the space coordinate system are as Figure 12(a) and 12(b) shown, where blue represents the reconstruction points and the corresponding reconstruction positions, and red represents the verification points and the corresponding verification positions.

[0097] When the spatial information energy cumulative contribution rate is selected as 0.99, 5 spatial modes are obtained. As shown in Fig. 13, the first - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method can be obtained. Specifically, Fig. 13(a) is the first - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method provided by the embodiment of the present invention;

[0098] Fig. 13(b) is the second - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method provided by the embodiment of the present invention; Fig. 13(c) is the third - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method provided by the embodiment of the present invention; Fig. 13(d) is the fourth - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method provided by the embodiment of the present invention; Fig. 13(e) is the fifth - order continuous spatial basis function cloud map obtained by using the cubic spline interpolation method provided by the embodiment of the present invention.

[0099] As shown in Fig. 14, they are the temperature field reconstruction results of the radome at different times. Specifically, Fig. 14(a) is the reconstructed temperature field nephogram of the radome at the 5th minute provided by the embodiment of the present invention; Fig. 14(b) is the reconstructed temperature field nephogram of the radome at the 10th minute provided by the embodiment of the present invention; Fig. 14(c) is the reconstructed temperature field nephogram of the radome at the 20th minute provided by the embodiment of the present invention; Fig. 14(d) is the reconstructed temperature field nephogram of the radome at the 36th minute provided by the embodiment of the present invention.

[0100] As Figure 15 shown, it is a comparison chart of the reconstructed results and the measured results at the positions of 5 selected verification points and the verification point positions. It can be seen that the reconstructed results of the present invention are very close to the measured results.

[0101] The mean absolute error and root mean square error of the verification positions are shown in Table 1. It can be seen from Table 1 that the reconstruction error is within 3.5°C. As Figure 16 shown, they are the MAE and RMSE of the reconstructed temperature field at the verification point positions, which verifies the effectiveness of the present method in the reconstruction of the radome temperature field. It can reconstruct the temperature field of the radome during the thermoelectric test through a small amount of actual measurement data, providing key support for exploring the dynamic influence mechanism of temperature factors on electrical performance in the service environment.

[0102] Table 1 MAE and RMSE of the reconstructed temperature at the verification positions

[0103] Verification Point 1 Verification Point 2 Verification Point 3 Verification Point 4 Verification Point 5 MAE / ℃ 3.1101 1.5041 2.2826 1.7697 0.8248 RMSE / ℃ 3.4737 1.6069 2.7307 2.2746 0.9551

[0104] A thermoelectric joint test method for a radome facing a high-speed flight environment provided by the present invention, on the one hand, through the structural design of a heating sleeve to heat the radome, a heat preservation sleeve to keep the radome warm and a heat insulation cap to block the thermal radiation and heat conduction from the inside of the radome, and at the same time, the dynamic monitoring of real-time temperature measurement by fiber Bragg grating temperature sensors, so that the high-temperature electrical performance test of the radome can be directly carried out in the existing darkroom. On the other hand, the present invention proposes a method for reconstructing the temperature field of the radome, which can accurately reconstruct the complete temperature field of the radome through partial discrete temperature measurement points, laying a foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance in the service environment.

[0105] The above content is a further detailed description of the present invention in combination with specific preferred embodiments. It cannot be determined that the specific implementation of the present invention is only limited to these descriptions. For those of ordinary skill in the technical field to which the present invention pertains, without departing from the concept of the present invention, several simple deductions or substitutions can be made, which should all be regarded as belonging to the protection scope of the present invention.

Claims

1. A combined thermoelectric test method for a radome in a high-speed flight environment, characterized in that: The following steps are involved: heating the radome through a heating system; and stopping heating the radome when the radome reaches a predetermined temperature value; The antenna cover that reaches a predetermined temperature value is insulated by the insulation system, and a thermoelectric combined test is performed on the insulated antenna cover; the temperature data of the antenna cover during the thermoelectric combined test is recorded in real time by the first temperature measurement structure, and the temperature data is reconstructed to obtain a reconstructed antenna cover temperature field.

2. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 1, characterized in that: The heating system includes a heating jacket, a control console for controlling the heating jacket, and a second temperature measurement structure; the second temperature measurement structure includes a demodulator, a computer, and several fiber Bragg grating temperature sensors connected in sequence for real-time measurement and analysis of fiber Bragg grating temperature sensor signals.

3. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 2, characterized in that: The heating jacket comprises an inner lining layer, a heating layer, a heat-insulating layer and an outer layer.

4. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 3, characterized in that: The inner lining layer is quartz cloth, the heating layer is glass fiber cloth evenly provided with heating wires, the thermal insulation layer is a heat-insulating nano-composite thermal insulation blanket, and the outer layer is composite aluminum foil cloth.

5. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 1, characterized in that: The thermal insulation system includes a thermal insulation sleeve and the first temperature measurement structure.

6. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 5, characterized in that: The thermal insulation sleeve comprises an aerogel inner layer and a quartz fiber outer layer.

7. A combined thermoelectric test method for a radome in a high-speed flight environment according to claim 1 or 5, characterized in that: The first temperature measurement structure includes a demodulator for real-time measurement and analysis of fiber Bragg grating temperature sensor signals, a computer, and a plurality of fiber Bragg grating temperature sensors, which are connected in sequence.

8. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 7, characterized in that: The fiber grating temperature sensors are divided into two groups and are evenly arranged above and below the inner wall of the antenna cover respectively. The spacing distance of the fiber grating temperature sensors of the group arranged above the inner wall of the antenna cover is smaller than the spacing distance of the fiber grating temperature sensors of the group arranged below the inner wall of the antenna cover.

9. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 1, characterized in that: The interior of the antenna cover is provided with a heat insulating cap for blocking heat radiation and heat conduction from the interior.

10. The method for thermoelectric combined testing of a radome in a high-speed flight environment according to claim 1, characterized in that: Reconstructing the temperature data to obtain a reconstructed radome temperature field also includes: The temperature data of the radome at several moments during the combined thermoelectric test were selected, and the temperature data were separated in time and space by principal component analysis to obtain discrete spatial modes and low-order time coefficients. The discrete spatial modes were interpolated by cubic spline to obtain continuous spatial basis functions. The low-order time coefficients were denoised by Kalman filter to obtain the optimal time coefficients. The reconstructed radome temperature field was obtained based on the continuous spatial basis functions and the optimal time coefficients.

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