A thermal vacuum experiment method for a spaceborne active phased array antenna

Abstract

The application discloses a kind of spaceborne active phased array antenna thermal vacuum experiment method, belong to communication antenna technical field;Specific steps are as follows, under the premise that the internal structure of active phased array antenna and T / R component are not reformed, only remove the passive transmitting antenna array at the outermost side of active phased array antenna, install matching load, so that single machine full load works without transmitting wireless signal, and excess heat consumption is exported or radiated by designing specific heat conduction mode.Load.

Description

Technical Field

[0001] This invention relates to the field of communication antenna technology, and in particular to a thermal vacuum experimental method for a spaceborne active phased array antenna. Background Technology

[0002] Thermal vacuum testing of spaceborne equipment is typically a mandatory test before individual unit delivery and is an effective way to expose problems with the unit. Thermal vacuum testing must be conducted inside a thermal vacuum chamber. Because the interior of the thermal vacuum chamber is sealed and made entirely of metal, transmitting signals inside the chamber can easily damage the equipment; therefore, signal transmission is generally strictly prohibited inside the thermal vacuum chamber.

[0003] However, spaceborne active phased array antennas differ from traditional passive antennas. During hot vacuum testing, they require individual unit power-on and signal transmission to simulate operational conditions, which contradicts the prohibition on antenna signal transmission within a hot vacuum chamber. If the unit is only powered on without transmitting signals during the test, the heat dissipation during the test will be less than the actual heat dissipation under operating conditions, making it impossible to effectively verify the unit.

[0004] To address this issue, current solutions include placing a microwave-absorbing heat sink inside a hot vacuum tank and modifying the T / R assembly or installing a load. However, both methods have their limitations.

[0005] The method of installing microwave absorbing heat sinks is expensive, has a long processing cycle, requires custom manufacturing, and since microwave absorbing heat sinks are generally made of non-metallic materials, there is also a risk of contaminating the thermal vacuum tank.

[0006] Modifying the T / R component and installing a load would complicate the operation process. In addition, converting the transmitted signal into heat generated by the load would introduce additional heat generation from the load, resulting in poor accuracy of the test results. Summary of the Invention

[0007] To address the problems existing in the above-mentioned background technology, this invention proposes a thermal vacuum experimental method for spaceborne active phased array antennas.

[0008] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0009] A thermal vacuum experimental method for a spaceborne active phased array antenna specifically includes the following steps.

[0010] Step 1: Remove the outermost passive transmitting antenna array of the spaceborne active phased array antenna while preserving the internal structure of the active phased array antenna and the T / R assembly.

[0011] Step 2: Install a matching load on the T / R component port;

[0012] Step 3: Set a heat-conducting structure on the matching load to promptly export and radiate the heat generated by the transmitted signal.

[0013] Step 4: Place the phased array antenna, connected to the thermal conductive fixture, into the hot vacuum chamber.

[0014] Step 5: Use one of the T / R components as a detection component and output the transmitted signal to the spectrum analyzer outside the hot vacuum tank via a wired connection.

[0015] Step 6: First, perform phase calibration on the monitoring components to ensure that the output power of each channel is maximized in the combiner;

[0016] Step 7: Adjust the signal source output power value to reach state P-1 at the design frequency point, and record the corresponding spectrum analyzer readings at the design frequency point. The readings at room temperature, high temperature, and low temperature are recorded as P1, P2, and P3, respectively. Compare the detected transmission power values ​​at the corresponding frequency points at room temperature, high temperature, and low temperature, and calculate the difference between power P2 and P1, and between P3 and P1, respectively, to obtain P2-1 and P3-1. Record the larger value between P2-1 and P3-1 as the fluctuation value of high and low temperature power.

[0017] Furthermore, in step 1, the passive transmitting antenna array to be removed refers to the transmitting element of the antenna; the form of the transmitting element includes, but is not limited to, array antenna elements and microstrip antenna elements.

[0018] Furthermore, in step 2, the installed matching load is selected with an appropriate resistance value based on the magnitude of the radiated power, and its port type should be compatible with the port type of the T / R component.

[0019] Furthermore, in step 3, a thermal pad is placed or thermal grease is applied between the thermally conductive structure and the matching load.

[0020] Furthermore, in step 5, the output end of the detection component is connected to a combiner, the combinedr's connector is connected to a coaxial cable, and the other end of the coaxial cable is connected to the hot vacuum tank adapter flange to output the transmitted signal to the spectrum analyzer outside the hot vacuum tank.

[0021] Furthermore, the hot vacuum chamber can be replaced with a sealed temperature chamber for thermal cycling tests.

[0022] The beneficial effects of the above-mentioned technical solution adopted by the present invention are as follows:

[0023] a) Without altering the internal structure of the active phased array antenna or the T / R assembly, only the outermost passive transmitting antenna array of the spaceborne active phased array antenna needs to be removed, making the operation simple.

[0024] B) To ensure the accuracy of the test, the additional heat introduced by installing the matching load is promptly discharged or radiated away by setting up a heat-conducting structure.

[0025] c) The technical solution adopted in this invention has a low cost and is suitable for promotion. It can be extended to other spaceborne active phased array antenna thermal tests, such as in the closed temperature chamber of thermal cycling tests.

[0026] d) This method does not require equipment such as microwave absorbing heat sinks, saving costs and reducing test preparation time. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the thermal vacuum test of the spaceborne active phased array antenna of the present invention;

[0028] Figure 2 This is a schematic diagram of the present invention after the transmitting antenna array has been removed and a matching load has been installed;

[0029] Figure 3 This is a schematic diagram of the power fluctuation monitoring of the spaceborne active phased array antenna of the present invention. Detailed Implementation

[0030] The present invention will now be further described in conjunction with the accompanying drawings and specific embodiments.

[0031] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings of the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] A thermal vacuum experimental method for a spaceborne active phased array antenna specifically includes the following steps.

[0033] Step 1: Remove the outermost passive transmitting antenna array of the spaceborne active phased array antenna while preserving the internal structure of the active phased array antenna and the T / R assembly.

[0034] Step 2: Install a matching load on the T / R component port;

[0035] Step 3: Set a heat-conducting structure on the matching load to promptly export and radiate the heat generated by the transmitted signal.

[0036] Step 4: Place the phased array antenna, connected to the thermal conductive fixture, into the hot vacuum chamber.

[0037] Step 5: Use one of the T / R components as a detection component and output the transmitted signal to the spectrum analyzer outside the hot vacuum tank via a wired connection.

[0038] Step 6: First, perform phase calibration on the monitoring components to ensure that the output power of each channel is maximized in the combiner;

[0039] Step 7: Adjust the signal source output power value to reach state P-1 at the design frequency point, and record the corresponding spectrum analyzer readings at the design frequency point. The readings at room temperature, high temperature, and low temperature are recorded as P1, P2, and P3, respectively. Compare the detected transmission power values ​​at the corresponding frequency points at room temperature, high temperature, and low temperature, and calculate the difference between power P2 and P1, and between P3 and P1, respectively, to obtain P2-1 and P3-1. Record the larger value between P2-1 and P3-1 as the fluctuation value of high and low temperature power.

[0040] Furthermore, in step 1, the passive transmitting antenna array to be removed refers to the transmitting element of the antenna; the form of the transmitting element includes, but is not limited to, array antenna elements and microstrip antenna elements.

[0041] Furthermore, in step 2, the installed matching load is selected with an appropriate resistance value based on the magnitude of the radiated power, and its port type should be compatible with the port type of the T / R component.

[0042] Furthermore, in step 3, a thermal pad is placed or thermal grease is applied between the thermally conductive structure and the matching load.

[0043] Furthermore, in step 5, the output end of the detection component is connected to a combiner, the combinedr's connector is connected to a coaxial cable, and the other end of the coaxial cable is connected to the hot vacuum tank adapter flange to output the transmitted signal to the spectrum analyzer outside the hot vacuum tank.

[0044] Furthermore, the hot vacuum chamber can be replaced with a sealed temperature chamber for thermal cycling tests.

[0045] The following is a more specific example:

[0046] This embodiment describes a thermal vacuum test method for a spaceborne active phased array antenna. A schematic diagram of the thermal vacuum test is shown below. Figures 1 to 3 The following describes this embodiment in detail through a thermal vacuum test of a satellite-borne active phased array antenna, specifically including the following steps;

[0047] Step 1: A certain satellite-borne active phased array antenna has a passive transmitting antenna array in the form of a dipole antenna. Without modifying the internal structure of the active phased array antenna and the T / R assembly, only the passive transmitting antenna array is removed.

[0048] Step 2: Install matching loads on the component port. The onboard active phased array antenna component port adopts the SMP interface form. Select the corresponding SMP matching load and install it on the component port in a plug-in manner.

[0049] Step 3, set up a heat-conducting structure on the matching load, such as Figure 2As shown, the solution used in this experiment is to install a heat-dissipating bent copper plate on the upper end of the SMP matching load, and install a thermal pad between the two to conduct excess heat to the bottom heat sink in a timely manner. In other experiments, the amount of heat to be radiated can also be calculated as needed, and a radiation plate with a specific surface emissivity and area can be designed to radiate the "extra" heat to the vacuum tank heat sink through the radiation plate;

[0050] Step 4: Use one component as a monitoring component. Connect its output end to a combiner. Connect the combiner's connector to a coaxial cable. Through the hot vacuum tank adapter flange, the output is connected to a spectrum analyzer outside the hot vacuum tank.

[0051] Step 5: The monitoring components need to be phase calibrated to ensure that the output power of each channel is maximized in the combiner (i.e., simulating the actual antenna array calibration state).

[0052] Step Six: During the experiment, adjust the signal source output power value to reach state P-1 at the designed frequency point, and record the corresponding spectrum analyzer readings at the designed frequency point; compare the normal temperature, high temperature, and low temperature transmit power detection values ​​at the corresponding frequency points, select the maximum and minimum transmit power detection values ​​at the corresponding frequency points, and check for high and low temperature power fluctuations. A power fluctuation monitoring diagram is shown below. Figure 3 As shown.

[0053] Through the above methods, the test of the spaceborne active phased array antenna at full power consumption in a thermal vacuum environment was completed, while power fluctuations were monitored.

Claims

1. A method for thermal vacuum experiment of a space-borne active phased array antenna, characterized in that, Specifically comprising the following steps, Step 1, under the premise of reserving the internal structure of the active phased array antenna and the T / R module, dismounting the outermost passive transmitting antenna array of the satellite-borne active phased array antenna; Step 2, mounting a matching load on the port of the T / R module; Step 3, setting a heat conduction structure on the matching load to timely export and radiate the heat generated by the load converted from the transmitting signal; Step 4, placing the phased array antenna connected with the heat conduction tool into a hot vacuum tank; Step 5, taking one of the T / R modules as a detection module, and outputting the transmitting signal to a spectrum analyzer outside the hot vacuum tank through wired connection; Step 6, firstly, performing phase calibration on the detection module to ensure that the power of each path is maximally superimposed in the combiner; Step 7, adjusting the output power value of the signal source to reach the P-1 state at the design frequency point, and recording the spectrum analyzer reading at the design frequency point, wherein the normal temperature, high temperature and low temperature readings are recorded as P1, P2 and P3 respectively, the power P2 and P1, and the power P3 and P1 are respectively subtracted to obtain P2-1 and P3-1, and the larger value of P2-1 and P3-1 is recorded as the fluctuation value of the high and low temperature power.

2. The thermal vacuum experiment method of a spaceborne active phased array antenna according to claim 1, characterized in that, In step 1, the dismounted passive transmitting antenna array refers to the transmitting unit of the antenna; the form of the transmitting unit includes but is not limited to the array antenna unit and the microstrip antenna unit.

3. The thermal vacuum experiment method of claim 1, wherein, In step 2, the matching load is selected according to the radiation power size, and the port form thereof should be adapted to the port form of the T / R module.

4. The thermal vacuum experiment method for a spaceborne active phased array antenna according to claim 1, characterized in that, In step 3, the heat conduction structure and the matching load are provided with a heat conduction pad or a heat conduction silicone grease.

5. The thermal vacuum experiment method for a spaceborne active phased array antenna according to claim 1, characterized in that, In step 5, the output end of the detection module is connected with the combiner, the combined end of the combiner is connected with a coaxial cable, the other end of the coaxial cable is connected with a flange through a hot vacuum tank adapter, and the transmitting signal is output to the spectrum analyzer outside the hot vacuum tank.

6. The thermal vacuum experiment method of a spaceborne active phased array antenna according to claim 1, wherein, The hot vacuum tank can be replaced with a sealed temperature chamber for thermal cycling test.

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