Thermal and electric combined test method for radome oriented to high-speed flight environment

Abstract

Disclosed is a thermal and electric combined test method for a radome oriented to a high-speed flight environment. The method comprises: heating a radome via a heating system; when the radome reaches a predetermined temperature value, stopping heating the radome; a thermal insulation system maintaining the temperature of the radome which has reached the predetermined temperature value, and performing a thermal and electric combined test in an existing anechoic chamber; and recording temperature data of the radome during the test process in real time, and reconstructing the temperature data of the radome during the thermal and electric combined test to obtain a reconstructed radome temperature field, thereby laying a foundation for exploring a dynamic influence mechanism of temperature factors on electrical performance in a service environment.

Description

A Thermoelectric Combined Test Method for Radomes for High-Speed ​​Flight Environments Technical Field

[0001] This invention belongs to the field of thermoelectric combined testing technology for radomes, and specifically relates to a thermoelectric combined testing method for radomes oriented towards high-speed flight environments. Background Technology

[0002] When a missile-borne radome flies at hypersonic speeds, it faces the problem of aerodynamic heating. The intense friction between the radome's exterior and the air causes the surface temperature of the radome to rise sharply. Since most radomes are made of inorganic materials, the dielectric constant and loss tangent of these materials are affected by temperature changes. The changes in the dielectric properties of the materials ultimately affect the electrical performance of the radome. Therefore, the electrical performance of the radome must be tested and evaluated before it enters service.

[0003] Traditional radome electrical performance evaluation mainly uses radome electrical performance testing systems to conduct tests at room temperature. However, during actual service, due to aerodynamic heating caused by increased speed, the surface temperature of the radome will rise significantly, and the local temperature may exceed 1,000 degrees Celsius. Electrical performance tests at room temperature often cannot truly reflect its service performance. Therefore, it is necessary to simulate the actual working environment of the radome for evaluation, i.e., high-temperature electrical performance evaluation of the radome.

[0004] The evaluation of the electrical performance of radomes under high-temperature environments mainly involves adding thermal testing to the traditional electrical performance testing of radomes. However, due to the limitations of microwave anechoic chambers, there are very few studies on the combined thermo-electrical testing of radomes. Patent CN112557798A discloses a phased array antenna-radome electrical performance testing device and method. The testing device includes a transmitting signal source, a transmitting antenna, a testing fixture, a turntable, a turntable control system, a phased array antenna, and a beam control unit. The transmitting signal source transmits a beam through the transmitting antenna. The phased array antenna and the radome under test are mounted on the testing fixture. The radome is first heated to a high temperature, and after cooling to room temperature, its electrical performance is tested. The electrical performance of the radome before and after the high temperature is compared for evaluation. However, this method separates electrical and thermal testing, failing to truly reflect the dynamic influence mechanism of temperature factors on electrical performance under service conditions. Patent CN114065473A discloses a surface radar integrated performance analysis method based on force-thermal-electric coupling. This invention includes thermal analysis, thermo-electric coupling analysis, force-thermal coupling analysis, and force-thermal-electric coupling analysis. The radome is simulated using thermal-electric coupling simulation software. However, the simulation requires high-performance computing resources and still has certain objective differences from reality, potentially resulting in simulation results that are acceptable but unacceptable under actual flight conditions.

[0005] Summary of the Invention

[0006] To address the aforementioned problems in the prior art, this invention provides a combined thermoelectric testing method for radomes designed for high-speed flight environments.

[0007] The technical problem to be solved by this invention is achieved through the following method, including the following steps:

[0008] The radome is heated by a heating system; heating is stopped when the radome reaches a predetermined temperature; the radome is kept at the predetermined temperature by a heat preservation system, and a thermoelectric combined test is performed on the heat-preserved radome; the temperature data of the radome during the thermoelectric combined test is recorded in real time by a first temperature measuring structure, and the temperature data is reconstructed to obtain the reconstructed temperature field of the radome.

[0009] Furthermore, the heating system includes a heating jacket, a control console for controlling the heating jacket, and a second temperature measuring structure; the second temperature measuring structure includes a demodulator for real-time measurement and analysis of fiber Bragg grating temperature sensor signals, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

[0010] Furthermore, the heating jacket includes an inner lining, a heating layer, an insulation layer, and an outer layer.

[0011] Furthermore, the inner lining layer is quartz cloth, the heating layer is fiberglass cloth with heating wires evenly distributed, the insulation layer is a heat-insulating nanocomposite insulation blanket, and the outer layer is composite aluminum foil cloth.

[0012] Furthermore, the insulation system includes an insulation jacket and a first temperature measuring structure.

[0013] Furthermore, the insulation jacket includes an aerogel inner layer and a quartz fiber outer layer.

[0014] Furthermore, the first temperature measurement structure includes a demodulator for real-time measurement and analysis of fiber Bragg grating temperature sensor signals, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

[0015] Furthermore, several fiber Bragg grating temperature sensors are divided into two groups and evenly arranged above and below the inner wall of the radome, respectively. The spacing between the group of fiber Bragg grating temperature sensors arranged above the inner wall of the radome is smaller than the spacing between the group of fiber Bragg grating temperature sensors arranged below the inner wall of the radome.

[0016] Furthermore, a heat-insulating cap is installed inside the radome to block heat radiation and heat conduction from the inside.

[0017] Furthermore, the reconstructed radome temperature field obtained by reconstructing the temperature data also includes:

[0018] Temperature data of the radome at several moments during the thermoelectric combined test were selected. Principal component analysis (PCA) was used to separate the temperature data into discrete spatial modes and low-order time coefficients. Cubic spline interpolation (CS) was performed on the discrete spatial modes to obtain continuous spatial basis functions. Kalman filter (KF) was used to reduce noise in the low-order time coefficients 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.

[0019] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0020] The present invention provides a thermoelectric combined testing method for radomes in high-speed flight environments. On the one hand, it employs a structural design that heats the radome with a heating jacket and insulates it with a thermal insulation jacket, while using a fiber optic grating temperature sensor for real-time temperature monitoring. This allows for direct testing of the radome's high-temperature electrical performance in existing anechoic chambers. On the other hand, the present invention proposes a radome temperature field reconstruction method that accurately reconstructs the complete radome temperature field through partially discrete temperature measurement points, laying the foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance under service conditions.

[0021] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0022] Figure 1 illustrates a thermoelectric combined test method for radomes in high-speed flight environments provided by this invention.

[0023] Figure 2 is a schematic diagram of the heating system provided in an embodiment of the present invention;

[0024] Figure 3 is a schematic diagram of the fiber optic grating temperature sensor arrangement provided in an embodiment of the present invention;

[0025] Figure 4 is a cross-sectional schematic diagram of the heating sleeve provided in an embodiment of the present invention being fitted onto the antenna radome;

[0026] Figure 5 is a schematic diagram of the fiber optic grating temperature sensor arrangement interval provided in an embodiment of the present invention;

[0027] Figure 6 is a schematic diagram of the combined thermoelectric test of the radome provided in an embodiment of the present invention;

[0028] Figure 7 is a schematic diagram of the heat preservation system provided in an embodiment of the present invention;

[0029] Figure 8 is a cross-sectional schematic diagram of the heat insulation sleeve provided in an embodiment of the present invention being fitted onto the radome;

[0030] Figure 9 is a flowchart of the radome temperature field reconstruction algorithm provided by the present invention;

[0031] Figure 10 is a temperature rise curve of the temperature measuring point during the heating process provided in the embodiment of the present invention;

[0032] Figure 11 shows the cooling curves of the temperature measuring points with and without insulation sleeves provided in the embodiments of the present invention.

[0033] Figure 12(a) is a schematic diagram of the position of the temperature measuring point inside the radome provided in an embodiment of the present invention;

[0034] Figure 12(b) is a schematic diagram of the position of the temperature measuring point in the spatial coordinate system provided in the embodiment of the present invention;

[0035] Figure 13(a) is a cloud map of first-order continuous spatial basis functions obtained by cubic spline interpolation according to an embodiment of the present invention;

[0036] Figure 13(b) is a cloud map of second-order continuous spatial basis functions obtained by cubic spline interpolation according to an embodiment of the present invention;

[0037] Figure 13(c) is a cloud map of third-order continuous spatial basis functions obtained by cubic spline interpolation according to an embodiment of the present invention;

[0038] Figure 13(d) is a cloud map of fourth-order continuous spatial basis functions obtained by cubic spline interpolation according to an embodiment of the present invention;

[0039] Figure 13(e) is a cloud map of fifth-order continuous spatial basis functions obtained by cubic spline interpolation according to an embodiment of the present invention;

[0040] Figure 14(a) is a reconstruction temperature field cloud map of the radome at the 5th minute according to an embodiment of the present invention;

[0041] Figure 14(b) is a reconstruction temperature field cloud map of the radome provided in the embodiment of the present invention at the 10th minute;

[0042] Figure 14(c) is a reconstruction temperature field cloud map of the radome provided in the embodiment of the present invention at the 20th minute;

[0043] Figure 14(d) is a reconstruction temperature field cloud map of the radome at the 36th minute according to the embodiment of the present invention;

[0044] Figure 15 is a comparison diagram of verification location reconstruction and actual measurement provided by the embodiment of the present invention;

[0045] Figure 16 shows the MAE and RMSE of the verification location reconstruction temperature provided in an embodiment of the present invention. Detailed Implementation

[0046] To further illustrate the technical means and effects adopted by the present invention to achieve the intended purpose, the following detailed description of the solution according to the present invention is provided in conjunction with the accompanying drawings and specific embodiments.

[0047] The foregoing and other technical contents, features, and effects of the present invention will be clearly presented in the following detailed description of specific embodiments in conjunction with the accompanying drawings. Through the description of the specific embodiments, a more in-depth and concrete understanding can be gained of the technical means and effects adopted by the present invention to achieve its intended purpose. However, the accompanying drawings are for reference and illustration only and are not intended to limit the technical solutions of the present invention.

[0048] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations are intended to cover non-exclusive inclusion, such that an article or apparatus comprising a list of elements includes not only those elements but also other elements not expressly listed. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the article or apparatus that includes said element.

[0049] Figure 1 shows a thermoelectric combined testing method for radomes in high-speed flight environments provided by an embodiment of the present invention:

[0050] A heating system is installed in the existing microwave anechoic chamber. A heating sleeve is placed on the outer surface of the radome, and a heat insulation cap is installed on the bottom of the inner wall of the radome. The heating sleeve is controlled to heat the radome through a control console in the heating system.

[0051] As shown in Figure 2, the heating system includes a heating jacket, a control console for controlling the heating jacket, and a second temperature measuring structure. The second temperature measuring structure includes a demodulator for real-time measurement and analysis of fiber optic temperature sensor signals, a computer, and several fiber optic temperature sensors connected in sequence. As shown in Figure 3, several fiber optic temperature sensors are spirally arranged on the inner wall of the radome using high-temperature resistant tape. Preferably, the high-temperature resistant tape is polyimide tape or quartz fiber tape.

[0052] The heating jacket includes an inner lining, a heating layer, an insulation layer, and an outer layer. The inner lining is made of quartz cloth, the heating layer is made of fiberglass cloth with heating wires evenly distributed to provide uniform heating for the heating jacket, the insulation layer is a heat-insulating nanocomposite insulation blanket, and the outer layer is made of composite aluminum foil cloth. The control console is connected to the heating jacket to control the temperature of the heating jacket. The heat insulation cap, which blocks heat radiation and heat conduction from the inside, is bonded to the bottom of the inner wall of the radome with high-temperature resistant adhesive. As shown in Figure 4, it is a cross-sectional schematic diagram of the heating jacket fitted onto the radome.

[0053] The temperature change of the radome is measured in real time by a fiber optic grating temperature sensor arranged in a spiral shape on the inner wall of the radome. When the temperature of the radome reaches a predetermined temperature value, the control console controls the heating jacket to stop heating the radome. Preferably, the predetermined temperature value is 350°C.

[0054] Several fiber Bragg grating temperature sensors are divided into two groups and evenly arranged above and below the inner wall of the radome, as shown in Figure 5. 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 temperature of the radome wall, the grating is divided into two groups, and the spacing between the fiber Bragg grating temperature sensors arranged above the inner wall of the radome is smaller than the spacing between the fiber Bragg grating temperature sensors arranged below the inner wall of the radome.

[0055] Preferably, the demodulator used to dynamically monitor the radome wall temperature in real time by decoding the center wavelength of the grating region is an MOI si155 with a bandwidth of 160nm. In this embodiment, 20 fiber optic temperature sensors are set according to the shape of the inner wall of the radome and the bandwidth of the demodulator. The first group of fiber optic temperature sensors is set at a grating region spacing of 200mm between the fiber optic temperature sensors located on the lower part of the inner wall of the radome, and the second group of fiber optic temperature sensors is set at a grating region spacing of 50mm between the fiber optic temperature sensors located on the upper part of the inner wall of the radome. The spacing between the first and second groups of grating regions is 200mm, and the grating region length of each fiber optic temperature sensor is 10mm.

[0056] After the radome is heated, remove the heating sleeve and quickly put on the insulation sleeve, as shown in Figure 6. Install the radome with the insulation sleeve on the turntable in the existing microwave anechoic chamber. The insulation sleeve in the insulation system keeps the radome at the predetermined temperature value. Then, perform a thermoelectric combined test on the insulated radome in the microwave anechoic chamber.

[0057] As shown in Figure 7, the insulation system includes an insulation jacket and a first temperature measuring structure. The first temperature measuring structure includes a demodulator for real-time measurement and analysis of fiber Bragg grating sensor signals, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

[0058] The insulation sleeve consists of 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. The insulation sleeve has the same shape as the radome. When it is put on the surface of the radome, the inner layer of the insulation sleeve and the outer layer of the radome fit tightly together, as shown in Figure 8, which is a cross-sectional schematic diagram of the insulation sleeve being put on the radome.

[0059] The temperature data of the radome is measured in real time by the fiber optic grating temperature sensor in the first temperature measurement structure during the thermoelectric combined test. The demodulator decodes the center wavelength of the grating region in real time to dynamically monitor the temperature of the radome. The computer records the temperature data of the radome in real time during the thermoelectric combined test and reconstructs the temperature data to obtain the reconstructed temperature field of the radome.

[0060] When reconstructing the temperature data to obtain the reconstructed radome temperature field, each fiber grating temperature sensor is used as a temperature measurement point, as shown in Figure 9. Temperature data of the radome obtained from some temperature measurement points at several moments during the thermoelectric combined test are selected. Principal component analysis (PCA) is used to separate the temperature data in time and space 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. Kalman filter (KF) is used to reduce noise of low-order time coefficients to obtain optimal time coefficients. The reconstructed radome temperature field is obtained based on the continuous spatial basis functions and optimal time coefficients.

[0061] Since the temperature field distribution of the radome is closely related to time and space, a spatiotemporal separation method is used to reconstruct the radome temperature field. Therefore, the radome temperature field at any given time can be expressed as:

[0062] In the formula, s represents the spatial coordinates of the grid point, and t represents time. For the spatial basis functions related to the model, α i (t) represents the time-related time pattern coefficients.

[0063] Expanding the above equation into an approximate finite term form, the radome temperature field under real-world operating conditions can be expressed as:

[0064] In the formula, n represents the number of spatial basis functions that contain more than 99% of spatial information energy.

[0065] To obtain the dominant spatial basis functions The following optimization objectives are set:

[0066] In the formula, It is the L2 norm of T(s,t). It is the definition of the set average, where L is the length of the set. 2 (Ω) denotes the space of square-integrable functions defined on the set Ω, and st(·) indicates that the contents within the parentheses are constrained, specifically by orthogonal constraints. The spatial basis functions associated with the model are guaranteed. The uniqueness of.

[0067] The corresponding Lagrangian constraint Γ is:

[0068] Where, λ i It represents the Lagrange multiplier.

[0069] The temperatures measured at some of the temperature measurement points can be represented by the following matrix:

[0070] In the formula, T (i) This represents the i-th temperature vector.

[0071] The above Lagrange constraint is equivalent to:

[0072] right Taking the derivative, we get:

[0073] Summarized as follows:

[0074] Will Arranged in descending order, the energy percentage of the first n modes can be expressed as:

[0075] When the energy content of the first n modes is greater than 99%, the infinite-dimensional system can be approximated using the first n modes. In this case, the radome temperature field can be expressed as:

[0076] Principal component analysis selected T T The first n characteristic roots of T are λ1, λ2, ..., λ n The corresponding unit eigenvector As the projection direction, when reducing the original data to n dimensions, it is only necessary to find T. T The eigenvectors corresponding to the n largest eigenvalues ​​of T form a projection matrix, and then... Dimensionality reduction can be achieved, and 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.

[0077] Since sensor measurements inherently contain noise, and the reconstruction error is significant under the influence of noise, a Kalman filter is introduced to reduce the noise of the low-order time coefficients after spatiotemporal separation. Therefore, the time coefficients in a real-world working environment can be expressed as:

[0078] in, Indicates the time coefficient. P represents the optimal time coefficient. - (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, and z i Let Q represent the observed value at the current moment, Q represent the system noise covariance matrix, and R represent the measurement noise covariance matrix.

[0079] The reconstructed temperature field can be based on and The calculation yielded the following:

[0080] The accuracy of the reconstructed temperature field is measured using the mean absolute error (MAE) and root mean square error (RMSE) of the temperature at the verification location. Specifically:

[0081] In the formula, To reconstruct the temperature field, T i (s,t) represents the temperature field under test conditions, and m represents the number of grid cells.

[0082] Before conducting the thermoelectric combined test of the radome, the present invention first conducts a "heating-insulation-temperature measurement" thermal test to ensure the feasibility of the "insulation-dynamic monitoring" scheme. The control console is set to a heating temperature of 400℃, and the radome is heated with a heating jacket. After heating for 37 minutes, the overall temperature of the radome reaches above 350℃. At this time, the temperature of some temperature measurement points reaches 400℃. The temperature rise curve of the temperature measurement points during the heating process is shown in Figure 10.

[0083] By comparing the cooling of the radome under two conditions—with and without a thermal insulation cover (condition 1) and condition 2—the insulation effect of the thermal insulation cover structure was analyzed. The electrical performance test of the radome lasted 35 minutes, so the cooling performance under condition 1 and condition 2 was compared within 35 minutes. Since there were 20 temperature measurement points, 5 points were randomly selected for comparison. The cooling curves are shown in Figure 11. Under condition 1, the radome wall temperature still reached approximately 300℃ after 36 minutes, a cooling rate of 25.11%. Under condition 2, the radome wall temperature was only about 75℃ after 36 minutes, a cooling rate of 81.5%. The thermal insulation effect of the radome with the thermal insulation cover-heat insulation cap is significantly better than that without it. This invention demonstrates a significant insulation effect and can effectively meet the requirements for combined thermoelectric testing of the radome.

[0084] Preferably, the present invention sets a total of 20 fiber optic temperature sensors as 20 temperature measurement points on the inner wall of the radome. The present invention selects 15 of these temperature measurement points as reconstruction points to reconstruct the temperature field of the radome at 36 time points, and uses the remaining 5 temperature measurement points as verification points to verify the accuracy of the reconstructed temperature field. The positions of the temperature measurement points inside the radome and their positions in the spatial coordinate system are shown in Figures 12(a) and 12(b), where blue represents the reconstruction point and its corresponding reconstruction position, and red represents the verification point and its corresponding verification position.

[0085] Five spatial modes were obtained when the cumulative contribution rate of spatial information energy was set to 0.99, as shown in Figure 13. The first five continuous spatial basis functions can be obtained using cubic spline interpolation. Specifically, Figure 13(a) is a cloud map of the first-order continuous spatial basis functions obtained using cubic spline interpolation according to an embodiment of the present invention; Figure 13(b) is a cloud map of the second-order continuous spatial basis functions obtained using cubic spline interpolation according to an embodiment of the present invention; Figure 13(c) is a cloud map of the third-order continuous spatial basis functions obtained using cubic spline interpolation according to an embodiment of the present invention; Figure 13(d) is a cloud map of the fourth-order continuous spatial basis functions obtained using cubic spline interpolation according to an embodiment of the present invention; and Figure 13(e) is a cloud map of the fifth-order continuous spatial basis functions obtained using cubic spline interpolation according to an embodiment of the present invention.

[0086] Figure 14 shows the temperature field reconstruction results of the radome at different times. Specifically, Figure 14(a) is the reconstructed temperature field cloud map of the radome at the 5th minute provided in the embodiment of the present invention; Figure 14(b) is the reconstructed temperature field cloud map of the radome at the 10th minute provided in the embodiment of the present invention; Figure 14(c) is the reconstructed temperature field cloud map of the radome at the 20th minute provided in the embodiment of the present invention; and Figure 14(d) is the reconstructed temperature field cloud map of the radome at the 36th minute provided in the embodiment of the present invention.

[0087] Figure 15 shows a comparison between the selected five verification point locations and the reconstruction results of the verification point locations and the measured results. It can be seen that the reconstruction results of the present invention are very close to the measured results.

[0088] The mean absolute error and root mean square error of the verification location are shown in Table 1. As can be seen from Table 1, the reconstruction error is within 3.5℃. Figure 16 shows the MAE and RMSE of the reconstructed temperature field at the verification point, which verifies the effectiveness of this method in reconstructing the temperature field of the radome. It can reconstruct the temperature field of the radome during thermoelectric testing using a small amount of actual measurement data, providing key support for exploring the dynamic influence mechanism of temperature factors on electrical performance under service environment.

[0089] Table 1. MAE and RMSE of verification location reconstruction temperature

[0090] The present invention provides a thermoelectric combined testing method for radomes in high-speed flight environments. On the one hand, it employs a heating jacket to heat the radome, an insulation jacket to insulate the radome, and a heat-insulating cap to block heat radiation and heat conduction from inside the radome. Simultaneously, it utilizes a fiber optic grating temperature sensor for real-time temperature monitoring, enabling direct high-temperature electrical performance testing of the radome within an existing anechoic chamber. On the other hand, the present invention proposes a radome temperature field reconstruction method, which accurately reconstructs the complete radome temperature field through partially discrete temperature measurement points, laying the foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance under service conditions.

[0091] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

Claims

1. A combined thermoelectric testing method for radomes designed for high-speed flight environments, characterized in that, Includes the following steps: The radome is heated by a heating system; heating of the radome stops when it reaches a predetermined temperature value. The radome is kept at a predetermined temperature by an insulation system, and a thermoelectric combined test is performed on the insulated radome. The temperature data of the radome during the thermoelectric combined test is recorded in real time by a first temperature measuring structure, and the temperature data is reconstructed to obtain the reconstructed temperature field of the radome.

2. The method for combined thermoelectric testing of radomes for high-speed flight environments 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 measuring structure; the second temperature measuring structure includes a demodulator for real-time measurement and analysis of fiber Bragg grating temperature sensor signals, a computer, and several fiber Bragg grating temperature sensors connected in sequence.

3. A thermoelectric combined testing method for radomes in high-speed flight environments as described in claim 2, characterized in that: The heating jacket includes an inner lining, a heating layer, an insulation layer, and an outer layer.

4. A thermoelectric combined testing method for radomes in high-speed flight environments as described in claim 3, characterized in that, The inner lining layer is quartz cloth, the heating layer is fiberglass cloth with heating wires evenly distributed, the heat insulation layer is a heat-insulating nanocomposite heat insulation blanket, and the outer layer is composite aluminum foil cloth.

5. The method for combined thermoelectric testing of radomes for high-speed flight environments according to claim 1, characterized in that, The insulation system includes an insulation sleeve and the first temperature measuring structure.

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

7. A thermoelectric combined testing method for radomes in high-speed flight environments 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 several fiber Bragg grating temperature sensors connected in sequence.

8. The method for combined thermoelectric testing of radomes for high-speed flight environments according to claim 7, characterized in that, The plurality 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. The spacing between the group of fiber Bragg grating temperature sensors arranged above the inner wall of the radome is smaller than the spacing between the group of fiber Bragg grating temperature sensors arranged below the inner wall of the radome.

9. The thermoelectric combined testing method for radomes in high-speed flight environments according to claim 1, characterized in that, The radome is equipped with a heat-insulating cap that blocks heat radiation and heat conduction from the inside.

10. The thermoelectric combined testing method for radomes in high-speed flight environments according to claim 1, characterized in that, The temperature data is reconstructed to obtain the reconstructed radome temperature field, which also includes: Temperature data of the radome at several moments during the thermoelectric combined test were selected. The temperature data were spatiotemporally separated by principal component analysis to obtain discrete spatial modes and low-order time coefficients. Cubic spline interpolation was performed on the discrete spatial modes 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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