Decoupling vacuum thermal test method for super-large array radar satellite

Abstract

The application provides a kind of super large array surface radar satellite decoupling vacuum thermal test method, satellite and radar antenna are arranged in a vacuum tank, radar antenna is detached from satellite and placed side by side on one side of satellite, infrared simulation device is respectively arranged around satellite to simulate external heat flow, wave absorption device is arranged on antenna array surface to absorb microwave and simulate external heat flow, the power level of infrared simulation device is adjusted according to the thermal radiation level of satellite surface, the power level of wave absorption device is adjusted according to the microwave emission power and thermal radiation level of antenna array surface, and vacuum thermal test is carried out on satellite and antenna.The application can avoid vacuum thermal test of satellite and radar antenna respectively because of too large antenna array surface, and can carry out microwave wireless emission state test of whole satellite, avoid high risk operation caused by antenna hanging and unfolding in tank after decoupling of antenna and satellite, greatly reduce the tank period of test state establishment and withdrawal and other links, and improve the efficiency of model development.

Description

Technical Field

[0001] This invention belongs to the field of vacuum thermal testing technology for radar satellites, specifically, it relates to a decoupling vacuum thermal testing method for ultra-large array radar satellites. Background Technology

[0002] Currently, radar satellites improve performance by expanding their antenna arrays, characterized by T / R modules evenly arranged on the antenna array. The antenna consists of multiple sub-unit boards with identical or similar configurations, often resulting in ultra-large arrays with apertures reaching several meters or even tens of meters, some exceeding the effective size of current vacuum tanks.

[0003] In current vacuum thermal tests of radar satellites, the satellite platform is typically placed in a seated position within a vacuum chamber, with the radar antennas on both sides suspended and horizontally supported by deployment fixtures. However, when the radar antenna array exceeds the effective dimensions of the vacuum chamber, internal deployment is impossible. This necessitates disassembling the radar antenna and conducting multiple tests, significantly impacting the satellite's development process and cycle. Furthermore, it makes it impossible to verify the amplitude and phase consistency of synchronous testing of the satellite and radar antennas, hindering the achievement of the radar satellite's vacuum thermal test objectives.

[0004] To solve the above problems, it is necessary to study a vacuum thermal testing method that is simple to design, safe to operate, and highly efficient in development.

[0005] According to research, Chinese patent document CN117109958A discloses a method for vacuum thermal testing of ultra-large aperture antennas with the entire satellite. It proposes to conduct vacuum thermal testing by folding the antennas and arranging them on both sides of the satellite. The premise is that the satellite is not conducting wireless microwave transmission / reception tests in a vacuum container. This method has no practical guiding significance for vacuum thermal testing of ultra-large array radar satellites in microwave wireless transmission mode, and no relevant practical applications have been found.

[0006] Furthermore, while the vacuum thermal testing methods for conventional-sized radar satellites are relatively mature, as the antennas of newer models become increasingly larger, those skilled in the art can easily conceive of increasing the size of the vacuum chamber, based on the technical inspiration from patent document CN117109958A.

[0007] Unlike patent document CN117109958A, the inventive concept of this invention is not to increase the size of the vacuum tank, but to make full use of the existing size of the vacuum tank, to achieve the optimal test method under limited vacuum tank conditions, and to conduct wireless microwave transmission / reception tests, meeting the vacuum thermal test requirements of radar satellite microwave wireless transmission state, so that the thermal test assessment can be fully carried out. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method for decoupling vacuum thermal testing of ultra-large array radar satellites.

[0009] According to the present invention, a decoupling vacuum thermal test method for a super-large array radar satellite includes: vertically installing a satellite 2 in a vacuum tank 1, and installing an infrared simulation device 10 around the satellite 2 to simulate external heat flow; Two back-to-back antenna subassemblies 3 of the antenna of satellite 2 are placed side by side on one side of satellite 2, and a microwave absorbing device 9 is set on the array surface of the antenna subassembly 3 to absorb microwaves and simulate external heat flow. The power level of the infrared simulation device 10 is adjusted according to the thermal radiation level on the surface of satellite 2, and the power level of the absorbing device 9 is adjusted according to the microwave transmission power and thermal radiation level of antenna sub-assembly 3. After adjustment, a vacuum thermal test is conducted on the satellite and antenna.

[0010] Preferably, the antenna of satellite 2 includes two antenna sub-assemblies 3 placed back-to-back on one side of satellite 2 and a sub-unit board 4 installed on the top of satellite. The back-to-back antenna sub-assemblies 3 are mainly composed of multiple sub-unit boards. Among them, multiple sub-unit boards belonging to the same antenna sub-assembly 3 are spliced ​​together in sequence and arranged vertically on one side of satellite 2.

[0011] Preferably, the antenna sub-assembly 3 is connected to the single unit inside the satellite cabin via a high-low frequency adapter cable, and the satellite top sub-unit plate 4 is transported and parked with the satellite. The multiple sub-unit plates are parked, transported and put into the tank for testing using antenna support fixtures.

[0012] Preferably, the back of the antenna sub-assembly 3 is covered with a multi-layer heat insulation assembly.

[0013] Preferably, the relative distance between the antenna sub-assemblies 3 and the effective size of the vacuum tank and the size of the wave-absorbing device are increased.

[0014] Preferably, the antenna is in the same test state as in the on-orbit state and is capable of wireless microwave transmission and reception.

[0015] Preferably, the infrared simulation device includes an infrared heating cage and an infrared lamp array.

[0016] According to the present invention, a vacuum thermal test device for decoupling ultra-large array radar satellites includes: a vacuum tank 1, an infrared simulation device 10, an antenna fixing device, and a wave-absorbing device 9. Satellite 2 can be vertically installed in vacuum tank 1, and infrared simulation device 10 can be installed around satellite 2 to simulate external heat flow; The antenna fixing device allows two back-to-back antenna sub-assemblies 3 of the antenna of satellite 2 to be placed side by side on one side of satellite 2. The microwave absorbing device 9 can be set on the array surface of the antenna sub-assembly 3 to absorb microwaves and simulate external heat flow. The power level of the infrared simulation device 10 is adjusted according to the thermal radiation level on the surface of satellite 2, and the power level of the absorbing device 9 is adjusted according to the microwave transmission power and thermal radiation level of antenna sub-assembly 3. After adjustment, a vacuum thermal test is conducted on the satellite and antenna.

[0017] Preferably, the back of the antenna sub-assembly 3 is covered with a multi-layer heat insulation assembly.

[0018] Preferably, the antenna of satellite 2 includes two antenna sub-assemblies 3 placed back-to-back on one side of satellite 2 and a sub-unit board 4 installed on the top of satellite. The back-to-back antenna sub-assemblies 3 are mainly composed of multiple sub-unit boards. Among them, multiple sub-unit boards belonging to the same antenna sub-assembly 3 are spliced ​​together sequentially and arranged vertically on one side of satellite 2; Antenna sub-assembly 3 is connected to the single unit inside the satellite cabin via high- and low-frequency adapter cables. The satellite top sub-unit board 4 is transported and parked with the satellite. The multiple sub-unit boards are parked, transported and put into the tank for testing using antenna support fixtures. The relative distance of the antenna sub-assembly 3 is widened by combining the effective size of the vacuum tank and the size of the wave-absorbing device. The antenna is in the same test state as in-orbit state and is capable of wireless microwave transmission and reception.

[0019] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention avoids the need to conduct separate vacuum thermal tests on satellite and radar antennas due to excessively large antenna arrays, and can perform whole-satellite microwave wireless transmission status tests.

[0020] 2. By decoupling the antenna from the satellite, this invention avoids the extremely high-risk operation of suspending and deploying the antenna inside the container, significantly reduces the container occupation period for test status establishment and dismantling, and improves the efficiency of model development.

[0021] 3. This invention provides a new approach to solving the problem of excessively large radar satellite antennas and insufficient effective space inside the vacuum container for antenna suspension and deployment in vacuum thermal testing. It meets the design requirements of simple design, safe operation, high development efficiency, good reliability, and flexible design. Attached Figure Description

[0022] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram showing the placement of the satellite and antenna in a vacuum chamber during the vacuum thermal test of this invention.

[0023] The diagram shows: Detailed Implementation

[0024] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0025] This invention provides a method for decoupling vacuum thermal testing of ultra-large array radar satellites, referring to... Figure 1 As shown, the process includes: vertically mounting satellite 2 in a vacuum chamber 1, and installing an infrared simulation device 10 around satellite 2 to simulate external heat flow. Two back-to-back antenna subassemblies 3 are placed side-by-side on one side of the satellite, and a microwave absorbing device 9 is installed on the array surface of the antenna subassemblies 3 to absorb microwaves and simulate external heat flow. The power level of the infrared simulation device 10 is adjusted according to the thermal radiation level of the satellite 2 surface, and the power level of the absorbing device 9 is adjusted according to the microwave transmission power and thermal radiation level of the antenna subassemblies 3. After adjustment, a vacuum thermal test is conducted on the satellite and antennas.

[0026] The antenna of Satellite 2 includes two antenna sub-assemblies 3 placed back-to-back on one side of Satellite 2 and a sub-unit plate 4 installed on the top of the satellite. The back-to-back antenna sub-assemblies 3 are mainly composed of multiple sub-unit plates, such as the first sub-unit plate 5, the second sub-unit plate 6, the third sub-unit plate 7, and the fourth sub-unit plate 8, which are spliced ​​together in sequence and arranged vertically on one side of Satellite 2. The antenna sub-assemblies 3 are connected to the single unit inside the satellite cabin through high- and low-frequency conversion cables. Except for the sub-unit plate 4 on the top of the satellite, which is transported and parked with the satellite, the other sub-unit plates, such as the first sub-unit plate 5, the second sub-unit plate 6, the third sub-unit plate 7, and the fourth sub-unit plate 8, are parked, transported, and put into the tank for testing using antenna support fixtures.

[0027] The back of the antenna sub-assembly 3 is covered with a multi-layer heat insulation component.

[0028] The relative distance between the antenna sub-assemblies 3 needs to be maximized by combining the effective size of the vacuum tank and the size of the absorbing device. On the one hand, this ensures that there is sufficient operating space between the antenna sub-assemblies 3, and on the other hand, it enhances the radiation heat dissipation of the vacuum tank by the sub-unit board.

[0029] The present invention also provides a vacuum thermal test device for decoupling ultra-large array radar satellites, which is applicable to the vacuum thermal test method for decoupling ultra-large array radar satellites, including: a vacuum tank 1, an infrared simulation device 10, an antenna fixing device, and a wave absorbing device 9; Satellite 2 can be vertically installed in vacuum tank 1, and infrared simulation device 10 can be installed around satellite 2 to simulate external heat flow; The antenna fixing device allows two back-to-back antenna sub-assemblies 3 of the antenna of satellite 2 to be placed side by side on one side of satellite 2. The microwave absorbing device 9 can be set on the array surface of the antenna sub-assembly 3 to absorb microwaves and simulate external heat flow. The power level of the infrared simulation device 10 is adjusted according to the thermal radiation level on the surface of satellite 2, and the power level of the absorbing device 9 is adjusted according to the microwave transmission power and thermal radiation level of antenna sub-assembly 3. After adjustment, a vacuum thermal test is conducted on the satellite and antenna.

[0030] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0031] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for decoupling vacuum thermal testing of ultra-large array radar satellites, characterized in that, include: The satellite (2) is vertically installed in the vacuum tank (1), and an infrared simulation device (10) is installed around the satellite (2) to simulate external heat flow; Two back-to-back antenna subassemblies (3) of the satellite (2) are placed side by side on one side of the satellite (2), and a microwave absorbing device (9) is set on the array surface of the antenna subassembly (3) to absorb microwaves and simulate external heat flow. Adjust the power level of the infrared simulation device (10) according to the thermal radiation level of the satellite (2) surface, and adjust the power level of the absorbing device (9) according to the microwave transmission power and thermal radiation level of the antenna sub-assembly (3). After adjustment, conduct a vacuum thermal test on the satellite and antenna. The back of the antenna sub-assembly (3) is covered with a multi-layer heat insulation component.

2. The method for decoupling vacuum thermal testing of ultra-large array radar satellites according to claim 1, characterized in that, The antenna of the satellite (2) includes two antenna sub-assemblies (3) placed back-to-back on one side of the satellite (2) and a sub-unit board (4) installed on the top of the satellite. The back-to-back antenna sub-assemblies (3) are mainly composed of multiple sub-unit boards (4). Among them, multiple sub-unit boards (4) belonging to the same antenna sub-assembly (3) are spliced ​​together in sequence and arranged vertically on one side of the satellite (2).

3. The method for decoupling vacuum thermal testing of ultra-large array radar satellites according to claim 1, characterized in that, The antenna sub-assembly (3) is connected to the single unit inside the satellite cabin via a high-low frequency adapter cable. The satellite top sub-unit board (4) is transported and parked with the satellite. Multiple sub-unit boards (4) are parked, transported, and put into the tank for testing using antenna support fixtures.

4. The method for decoupling vacuum thermal testing of ultra-large array radar satellites according to claim 1, characterized in that, The relative distance of the antenna sub-assembly (3) is combined with the effective size of the vacuum tank and the size of the wave-absorbing device to widen.

5. The method for decoupling vacuum thermal testing of ultra-large array radar satellites according to claim 1, characterized in that, The antenna is in the same test state as in-orbit state and is capable of wireless microwave transmission and reception.

6. The method for decoupling vacuum thermal testing of ultra-large array radar satellites according to claim 1, characterized in that, The infrared simulation device includes an infrared heating cage and an infrared lamp array.

7. A vacuum thermal test device for decoupling ultra-large array radar satellites, characterized in that, The ultra-large array radar satellite decoupling vacuum thermal test method according to any one of claims 1 to 6 includes: a vacuum tank (1), an infrared simulation device (10), an antenna fixing device, and a wave absorbing device (9). The satellite (2) can be vertically installed in the vacuum tank 1, and the infrared simulation device (10) can be installed around the satellite (2) to simulate external heat flow; The antenna fixing device can be used to place two back-to-back antenna sub-assemblies (3) of the antenna of the satellite (2) side by side on one side of the satellite (2), and the wave absorbing device (9) can be set on the array surface of the antenna sub-assembly (3) to absorb microwaves and simulate external heat flow. Adjust the power level of the infrared simulation device (10) according to the thermal radiation level of the satellite (2) surface, and adjust the power level of the absorbing device (9) according to the microwave transmission power and thermal radiation level of the antenna sub-assembly (3). After adjustment, conduct a vacuum thermal test on the satellite and antenna.

8. The ultra-large array radar satellite decoupling vacuum thermal test device according to claim 7, characterized in that, The back of the antenna sub-assembly (3) is covered with a multi-layer heat insulation component.

9. The ultra-large array radar satellite decoupling vacuum thermal test device according to claim 7, characterized in that, The antenna of the satellite (2) includes two antenna sub-assemblies (3) placed back-to-back on one side of the satellite (2) and a sub-unit board (4) installed on the top of the satellite. The back-to-back antenna sub-assemblies (3) are mainly composed of multiple sub-unit boards (4). Among them, multiple sub-unit boards (4) belonging to the same antenna sub-assembly (3) are spliced ​​together in sequence and arranged vertically on one side of the satellite (2); The antenna sub-assembly (3) is connected to the single unit inside the satellite cabin via a high-low frequency adapter cable. The satellite top sub-unit board (4) is transported and parked with the satellite. Multiple sub-unit boards (4) are parked, transported, and put into the tank for testing using antenna support fixtures. The relative distance of the antenna sub-assembly (3) is widened by combining the effective size of the vacuum tank and the size of the wave-absorbing device. The antenna is in the same test state as in-orbit state and is capable of wireless microwave transmission and reception.

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