High-speed flight environment-oriented antenna housing heat and power combined test method

Abstract

The invention discloses a high-speed flight environment-oriented antenna housing thermoelectric joint test method, which comprises the following steps of: heating an antenna housing through a heating system, stopping heating the antenna housing after the antenna housing reaches a preset temperature value, carrying out heat preservation on the antenna housing reaching the preset temperature value through a heat preservation system, and carrying out thermoelectric joint test in an existing darkroom. The temperature data of the radome in the test process are recorded in real time, the temperature data of the radome in the thermoelectric joint test process are reconstructed to obtain the reconstructed radome temperature field, and a foundation is laid for exploring the dynamic influence mechanism of the temperature factor on the electrical performance in the service environment.

Description

Technical Field

[0001] The invention belongs to the technical field of thermoelectric combined testing of radomes, and in particular relates to a thermoelectric combined testing method 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. The radome is mostly made of inorganic materials. The dielectric constant and loss tangent of these materials are affected by temperature changes. Changes in the dielectric properties of the materials ultimately affect the electrical properties of the radome. Therefore, the electrical properties of the radome must be tested and evaluated before it is put into service.

[0003] Traditionally, the electrical performance evaluation of the radome is mainly carried out at room temperature using a radome electrical performance test system. However, in actual service, due to the aerodynamic heating caused by the increase in speed, the surface temperature of the radome will increase significantly, and the local temperature may exceed one thousand degrees. The electrical performance test under room temperature often cannot truly reflect its service performance. Therefore, it is necessary to simulate the actual 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 the radome in a high temperature environment mainly involves adding thermal testing on the basis of traditional radome electrical performance testing. However, due to the limitations of microwave anechoic chambers, there are few studies on the combined thermal and electrical testing of radomes. Patent publication CN112557798A provides a phased array antenna-radome electrical performance test device and test method. In the invention, the test device includes a transmitting signal source, a transmitting antenna, a test fixture, a turntable, a turntable control system, a phased array antenna and a beam controller. The transmitting signal source transmits a beam through the transmitting antenna. The phased array antenna and the tested radome are installed on the test fixture. The radome is first heated at high temperature, and then the electrical performance test is performed after it is cooled to room temperature. The electrical performance of the radome is evaluated by comparing the electrical performance 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 under the service environment; Patent publication CN114065473A provides a surface radar comprehensive performance analysis method based on force-thermal-electric coupling. The invention includes thermal analysis, thermoelectric coupling analysis, force-thermal coupling analysis, and force-thermal-electric coupling analysis. The radome is thermally-electrically coupled simulated by simulation software, but the simulation requires high-performance computing resources and there is still a certain objective gap with the actual situation. It may happen that the simulation results are qualified but unqualified under 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 combined thermal and electrical testing method for a radome in a high-speed flight environment.

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

[0007] The antenna cover is heated by a heating system; the heating of the antenna cover is stopped when the antenna cover reaches a predetermined temperature value; the antenna cover that has reached the predetermined temperature value is insulated by a thermal 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 a first temperature measuring structure, and the temperature data is reconstructed to obtain a reconstructed temperature field of the antenna cover.

[0008] Furthermore, 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 grating temperature sensors connected in sequence for real-time measurement and analysis of fiber grating temperature sensor signals.

[0009] Furthermore, the heating jacket comprises an inner lining layer, a heating layer, a thermal insulation layer and an outer layer.

[0010] Furthermore, 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.

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

[0012] Furthermore, the thermal insulation sleeve comprises an inner layer of aerogel and an outer layer of quartz fiber.

[0013] Furthermore, the first temperature measurement structure includes a demodulator, a computer and a plurality of fiber Bragg grating temperature sensors which are connected in sequence and measure and analyze the fiber Bragg grating temperature sensor signals in real time.

[0014] Furthermore, a plurality of 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 group of fiber grating temperature sensors arranged above the inner wall of the antenna cover is smaller than the spacing distance of the group of fiber grating temperature sensors arranged below the inner wall of the antenna cover.

[0015] Furthermore, a heat insulating cap is provided inside the antenna cover to block heat radiation and heat conduction from the inside.

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

[0017] The temperature data of the radome at several moments during the combined heat and power test were selected, and the temperature data were separated in time and space by principal component analysis (PCA) to obtain discrete spatial modes and low-order time coefficients. The discrete spatial modes were interpolated by cubic spline (CS) to obtain continuous spatial basis functions. The low-order time coefficients were denoised by the Kalman filter (KF) to obtain the optimal time coefficient. The reconstructed radome temperature field was obtained according to the continuous spatial basis functions and the optimal time coefficients.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The present invention provides a combined thermoelectric test method for a radome in a high-speed flight environment. On the one hand, a heating sleeve is used to heat the radome and an insulation sleeve is used to insulate the radome. At the same time, a fiber grating temperature sensor is used for real-time temperature measurement and dynamic monitoring. Thus, the high-temperature electrical performance test of the radome can be directly performed in an existing darkroom. On the other hand, the present invention proposes a radome temperature field reconstruction method. The complete radome temperature field is accurately reconstructed through partially discrete temperature measurement points, laying a foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance under a service environment.

[0020] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The invention provides a combined thermal and electrical testing method for a radome in a high-speed flight environment;

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

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

[0024] Figure 4 is a cross-sectional schematic diagram of a heating sleeve provided in an embodiment of the present invention being mounted on a radome;

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

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

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

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

[0029] Fig. 9 It is a flow chart of the radome temperature field reconstruction algorithm provided by the present invention;

[0030] Fig.10 is a temperature rise curve of a temperature measuring point during a heating process provided by an embodiment of the present invention;

[0031] Fig.11 The temperature drop curves of the temperature measuring points with and without the insulation cover provided by the embodiments of the present invention;

[0032] FIG. 12( a ) is a schematic diagram of the positions of temperature measurement points in the antenna cover according to an embodiment of the present invention;

[0033] FIG12( b ) is a schematic diagram of the positions of the temperature measurement points in the spatial coordinate system provided by an embodiment of the present invention;

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

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

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

[0037] FIG. 13( d ) is a cloud diagram of a fourth-order continuous spatial basis function obtained by using a cubic spline interpolation method provided in an embodiment of the present invention;

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

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

[0040] FIG14( b ) is a cloud diagram of the reconstructed temperature field of the radome at the 10th minute provided by an embodiment of the present invention;

[0041] FIG14( c ) is a cloud diagram of the reconstructed temperature field of the radome at the 20th minute provided by an embodiment of the present invention;

[0042] FIG14( d ) is a cloud diagram of the reconstructed temperature field of the radome at the 36th minute provided by an embodiment of the present invention;

[0043] Fig.15 It is a verification position reconstruction-actual measurement comparison diagram provided by an embodiment of the present invention;

[0044] Fig.16 These are the MAE and RMSE of the reconstructed temperature of the verification position provided by the embodiment of the present invention. DETAILED DESCRIPTION

[0045] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined invention purpose, the scheme according to the present invention is described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0046] The above and other technical contents, features and effects of the present invention are clearly presented in the following detailed description of the specific implementation modes in conjunction with the accompanying drawings. Through the description of the specific implementation modes, the technical means and effects adopted by the present invention to achieve the predetermined purpose can be more deeply and specifically understood. However, the attached drawings are only for reference and explanation purposes and are not used to limit the technical solutions of the present invention.

[0047] It should be noted that, in this article, relational terms such as first and second, etc. 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 "include", "comprise" or any other variants are intended to cover non-exclusive inclusion, so that an article or device including a series of elements includes not only those elements, but also other elements that are not explicitly listed. In the absence of more restrictions, the elements defined by the statement "including one..." do not exclude the existence of other identical elements in the article or device including the elements.

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

[0049] A heating system is arranged in an existing microwave darkroom, a heating sleeve in the heating system is mounted on the outer surface of the antenna cover, a heat insulation cap is loaded on the bottom of the inner wall of the antenna cover, and the heating sleeve is controlled by a control console in the heating system to heat the antenna cover.

[0050] like Figure 2 As shown, the heating system includes a heating jacket, a control console for controlling the heating jacket, and a second temperature measurement structure, wherein the second temperature measurement structure includes a demodulator, a computer, and a plurality of fiber Bragg grating temperature sensors connected in sequence for real-time measurement and analysis of fiber Bragg grating temperature sensor signals; Figure 3 As shown, a plurality of fiber grating temperature sensors are spirally arranged on the inner wall of the antenna cover through a high temperature resistant tape. Preferably, the high temperature resistant tape is a polyimide tape or a quartz fiber tape.

[0051] The heating sleeve includes an inner lining layer, a heating layer, an insulation layer and an outer layer, wherein the inner lining layer is quartz cloth, the heating layer is glass fiber cloth with heating wires evenly arranged, which provides uniform heating for the heating sleeve, the insulation layer is a heat-insulating nano-composite insulation blanket, and the outer layer is a composite aluminum foil cloth; the control console is connected to the heating sleeve to control the temperature of the heating sleeve; the insulation cap that blocks the heat radiation and heat conduction from the inside is bonded to the bottom of the inner wall of the antenna cover by high-temperature resistant glue, such as Figure 4 The figure shows a cross-sectional schematic diagram of a heating sleeve being mounted on a radome.

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

[0053] Several fiber Bragg grating temperature sensors are divided into two groups and are evenly arranged above and below the inner wall of the radome. Figure 5 As 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 temperature of the radome wall, the grating area is divided into two groups, and the spacing distance of a group of fiber Bragg grating temperature sensors arranged above the inner wall of the radome is smaller than the spacing distance of a group of fiber Bragg grating temperature sensors arranged below the inner wall of the radome;

[0054] Preferably, the demodulator for real-time dynamic monitoring of the wall temperature of the antenna cover by real-time decoding of the grating center wavelength selects MOI si155, whose bandwidth is 160nm; in this embodiment, 20 fiber grating temperature sensors are arranged according to the shape of the inner wall of the antenna cover and the bandwidth of the demodulator, wherein the grating interval between the fiber grating sensors of the first group arranged at the lower part of the inner wall of the antenna cover is 200mm, and the grating interval between the fiber grating sensors of the second group arranged at the upper part of the inner wall of the antenna cover is 50mm, the interval between the first group and the second group of gratings is 200mm, and the grating length of the fiber grating temperature sensor is 10mm.

[0055] After the antenna cover is heated, remove the heating cover and quickly put on the insulation cover. Figure 6 As shown, the antenna cover with the insulation sleeve is installed on a turntable in an existing microwave darkroom, the antenna cover reaching a predetermined temperature value is insulated by the insulation sleeve in the insulation system, and a thermoelectric combined test is performed on the insulated antenna cover in the microwave darkroom.

[0056] like Figure 7 As shown, the heat preservation system includes a heat preservation sleeve and a first temperature measurement structure, wherein the first temperature measurement structure includes a demodulator, a computer and a plurality of fiber grating temperature sensors connected in sequence for real-time measurement and analysis of fiber grating sensor signals.

[0057] The insulation sleeve includes an inner layer of aerogel and an outer layer of quartz fiber. The dielectric constant of the inner layer of aerogel is 1.01, and the loss tangent is 0.005. The outer layer is wrapped with quartz fiber. The insulation sleeve has the same shape as the radome. When the insulation sleeve is put on the surface of the radome, the inner layer of the insulation sleeve fits tightly with the outer layer of the radome. Figure 8 The figure shows a cross-sectional schematic diagram of a thermal insulation sleeve being mounted on a radome.

[0058] The fiber grating temperature sensor in the first temperature measurement structure measures the temperature data of the antenna cover in real time during the thermoelectric combined test. The demodulator decodes the central wavelength of the grating area in real time to dynamically monitor the temperature of the antenna cover in real time. The computer records the temperature data of the antenna cover in real time during the thermoelectric combined test, and reconstructs the temperature data to obtain a reconstructed antenna cover temperature field.

[0059] When reconstructing the temperature data to obtain the reconstructed radome temperature field, each fiber Bragg grating temperature sensor is used as a temperature measurement point, such as Fig. 9 As shown in the figure, the temperature data of the radome obtained from some temperature measurement points at several moments during the combined heat and power test are selected, and the temperature data are separated in time and space by principal component analysis (PCA) to obtain discrete spatial modes and low-order time coefficients. The discrete spatial modes are interpolated by cubic spline (CS) to obtain continuous spatial basis functions. The low-order time coefficients are denoised by the Kalman filter (KF) to obtain the optimal time coefficient. The reconstructed radome temperature field 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 time and space separation. The temperature field of the radome at any time is expressed as:

[0061]

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

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

[0064]

[0065] Where n represents the number of spatial basis functions that contain more than 99% of the spatial information energy.

[0066] To obtain the dominant spatial basis function The following optimization objectives are formed:

[0067]

[0068] In the formula, is the L2 norm of T(s,t), is the definition of the 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 The spatial basis functions associated with the model are guaranteed uniqueness.

[0069] The corresponding Lagrangian constraint Γ is:

[0070]

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

[0072] The temperature 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 get:

[0078]

[0079] Arranged:

[0080]

[0081] Will Sorting 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 to select T T The first n characteristic roots of T λ1,λ2,…,λ nThe corresponding unit eigenvector As the projection direction, that is, when the original data is reduced to n dimensions, we only need to find T T The eigenvectors corresponding to the largest n eigenvalues ​​of T form a projection matrix, and then use 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.

[0086] Since the sensor measurement value has noise, and the reconstruction error is large under the influence of noise, the Kalman filter is introduced to reduce the noise of the low-order time coefficient after time-space separation. The time coefficient in the real working environment can be expressed as:

[0087]

[0088] in, 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 transfer matrix, H represents the observation matrix, z i represents the observation 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 based on and Calculate and get:

[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 position. Specifically:

[0092]

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

[0094] Before the thermoelectric combined test of the antenna cover, the present invention first performs a "heating-insulation-temperature measurement" thermal test to ensure the feasibility of the "insulation-dynamic monitoring" scheme. The console sets the heating temperature to 400°C and uses a heating jacket to heat the antenna cover. After heating for 37 minutes, the overall temperature of the antenna cover reaches above 350°C. 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 follows: Fig.10 shown.

[0095] By comparing the cooling conditions of the antenna cover under two working conditions, with a thermal insulation cover (working condition 1) and without a thermal insulation cover (working condition 2), the thermal insulation effect of the "thermal insulation cover" structure is analyzed. The electrical performance test time of the antenna cover is 35 minutes, so the cooling conditions of working condition 1 and working condition 2 within 35 minutes are compared. At the same time, since there are 20 temperature measurement points, 5 temperature measurement points are randomly selected for comparison. The cooling curve is shown in Fig.11 As shown, after 36 minutes in working condition 1, the wall temperature of the radome can still reach about 300°C, a temperature drop of 25.11%; after 36 minutes in working condition 2, the wall temperature of the radome is only about 75°C, a temperature drop of 81.5%. The thermal insulation effect of the radome with the thermal insulation cover-insulation cap is significantly better than that without the thermal insulation cover-insulation cap. The thermal insulation effect of the present invention is obvious and can effectively meet the requirements of the thermal power combined test of the radome.

[0096] Preferably, the present invention sets a total of 20 fiber Bragg grating temperature sensors as 20 temperature measuring points on the inner wall of the antenna cover. The present invention selects 15 of the temperature measuring points as reconstruction points to reconstruct the temperature field of the antenna cover using temperature data at 36 moments, and the remaining 5 temperature measuring points are used as verification points to verify the accuracy of the reconstructed temperature field. The positions of the temperature measuring points in the antenna cover and in the spatial coordinate system are as follows: Figure 12(a) and 12(b) As shown, blue represents reconstruction points and the reconstruction positions corresponding to the reconstruction points, and red represents verification points and the verification positions corresponding to the verification points.

[0097] When the cumulative contribution rate of spatial information energy is selected as 0.99, 5 spatial modes are obtained, as shown in FIG13 . The first five order continuous spatial basis functions can be obtained by using the cubic spline interpolation method. Specifically, FIG13 (a) is a cloud diagram of the first order continuous spatial basis function obtained by using the cubic spline interpolation method provided in an embodiment of the present invention;

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

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

[0100] like Fig.15 As shown, there are five selected verification point positions and a comparison diagram of the reconstruction results of the verification point positions and the measured results. It can be seen that the reconstruction 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 position are shown in Table 1. It can be seen from Table 1 that the reconstruction error is within 3.5°C. Fig.16 The figure shows the MAE and RMSE of the reconstructed temperature field at the verification point position, 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 with 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.

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

[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] The present invention provides a combined thermoelectric test method for a radome in a high-speed flight environment. On the one hand, the radome is heated by a heating sleeve, the radome is insulated by an insulation sleeve, and the heat radiation and heat conduction from the inside of the radome are blocked by a heat insulation cap. At the same time, a fiber grating temperature sensor is used for real-time temperature measurement and dynamic monitoring, so that the high-temperature electrical performance test of the radome can be directly performed in an existing darkroom. 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 a foundation for exploring the dynamic influence mechanism of temperature factors on electrical performance under a service environment.

[0105] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A combined thermal and electrical test method for a radome in a high-speed flight environment, characterized in that: The following steps are involved: The radome is heated by a heating system; when the radome reaches a predetermined temperature value, the heating of the radome is stopped; 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 comprises a heating jacket, a control console for controlling the heating jacket and a second temperature measurement structure; the second temperature measurement structure comprises a demodulator, a computer and a plurality of fiber grating temperature sensors connected in sequence for real-time measurement and analysis of fiber grating temperature sensor signals.

3. The method for testing the thermal power 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 testing the thermal power 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 testing the thermal power 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 measuring structure.

6. The method for testing the thermal power 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 method for testing the thermal power combination of a radome in a high-speed flight environment according to claim 1 or 5, characterized in that: The first temperature measurement structure comprises a demodulator, a computer and a plurality of fiber grating temperature sensors which are connected in sequence and are used for real-time measurement and analysis of fiber grating temperature sensor signals.

8. The method for testing the thermal power 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 group of fiber grating temperature sensors arranged above the inner wall of the antenna cover is smaller than the spacing distance of the group of fiber grating temperature sensors arranged below the inner wall of the antenna cover.

9. The method for testing the thermal power 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 testing the thermal power 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 heat and power 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 the Kalman filter to obtain the optimal time coefficient. The reconstructed radome temperature field was obtained according to the continuous spatial basis functions and the optimal time coefficients.

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