Satellite antenna high frequency cable temperature consistency control device structure

Abstract

The application provides a satellite-borne antenna high-frequency cable temperature consistency control device structure and belongs to the field of thermal control design of space vehicles. The application aims at the problems of the large number and long length of high-frequency cables of a satellite-borne super-large aperture antenna, the uncertainty of temperature distribution of the high-frequency cables through different parts of the antenna and the star body, solves the high-frequency cable temperature consistency control problem through reasonable cable layout, overall covering of a multilayer thermal insulation component and other measures, guarantees the electrical performance of the antenna, simultaneously adapts to the temperature requirements under different external heat flow conditions, and has the characteristics of less resource occupation, high adaptability, good reliability and flexible design.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft thermal control, in particular to a structure of a high-frequency cable temperature consistency control device for a spaceborne antenna, and more particularly to a structure of a high-frequency cable temperature consistency control device for a spaceborne super-large aperture antenna, wherein the super-large aperture refers to an antenna with a size greater than 50 meters in the length direction. BACKGROUND

[0002] At present, one of the development directions of radar antennas is to expand the aperture to pursue performance, and the characteristic is that the equipment group is uniformly arranged on the antenna, which generates heat during short-time operation and has no heat consumption when not working, and the temperature oscillation is large. Without effective thermal control measures, the temperature of the equipment during operation will rise sharply, which will lead to the direct failure of the equipment, and the temperature of the high-frequency cable will also be out of control. In addition, a large-aperture radar antenna is often composed of different sub-boards ZB, which has the characteristic of "low temperature on both sides and high temperature in the middle". The high-frequency cables drawn from different sub-boards ZB have initial temperature differences, and due to the requirement of cable equal length, effective arrangement devices are needed to ensure that their electrical and thermal performances meet the requirements.

[0003] For radar antennas, the conventional thermal control design device is designed for the heat dissipation requirement of the equipment, a heat dissipation surface is provided on the ground, and common devices are covered with polyimide germanium film or aluminum alloy bright anodic oxidation, the surface of the antenna is covered with multiple thermal insulation components, and heat pipes, heat-conducting fillers and heaters are used to control the equipment group. With the increase of the aperture of the antenna, the required power and weight will also increase by several times, and there is no extra resource for high-frequency cable thermal control, which needs to be controlled by using existing means of antenna thermal control. The electrical performance often requires good temperature consistency between different high-frequency cables, and in the case of limited resources, appropriate devices need to be taken to ensure it.

[0004] At present, the main temperature control methods for high-frequency cables of radar antennas are: 1) directly exposed on the back of the antenna without taking any measures, due to the uncertainty of the surface absorption ratio and the change of the orbital heat flow, the cable temperature oscillates sharply, and even reaches-90℃-90℃; 2) according to the heat dissipation of the high-frequency cable, the surface of the high-frequency cable is plated with F46 silver or covered with multiple thermal insulation components, which can appropriately reduce the temperature oscillation, but still cannot meet the electrical performance requirements.

[0005] After searching the prior art:

[0006] Patent document CN109004335A discloses a thermal control design device for a large-aperture antenna suitable for Mars exploration, mainly relates to the independent thermal design of the antenna main reflecting surface and the antenna mechanism, the antenna is a passive antenna, and does not involve high-frequency cable temperature control, i.e. there is no such requirement.

[0007] Patent document CN107462779A discloses a test method for a microwave imaging satellite inter-board cable phase error measurement device, mainly relates to inter-board cable phase error measurement, does not use a new thermal control technology for temperature control, resulting in the cable being exposed to the space environment, the temperature exceeding limit risk is great, and the antenna electrical performance and imaging quality will be adversely affected.

[0008] Patent document CN112298619A discloses an SAR antenna inter-board cable ultra-stable temperature control device, focuses on explaining that the cable is entirely covered in a multi-layer thermal insulation assembly, and is expanded and contracted together with the antenna, so that it is not affected by the space external heat flow. The patent document is applicable to the case where the antenna aperture is small, and does not use any control device for the temperature consistency between the cables.

[0009] Patent document CN114537716A discloses a dot matrix temperature consistency control method and system, uses a pre-buried phase change heat pipe or phase change plate, and lays high thermal conductivity graphene, lays thermal conductive silicone grease, etc. to keep the starting temperature of each module of the antenna at the same temperature level. There is no practical guidance for temperature consistency control of high-frequency cables suspended in the air.

[0010] Patent document CN107742771A discloses a satellite-borne antenna deployment arm device capable of realizing built-in wiring of radio frequency cables, realizes the internal wiring function of the antenna radio frequency cable, is conducive to the wiring of the extravehicular cable, reduces the weight of the product, and is conducive to the integrated thermal control design of the deployment arm and the radio frequency cable. The patent document does not provide an actual method for thermal control design, and has no related discussion on temperature consistency. SUMMARY

[0011] In view of the defects in the prior art, the purpose of the present application is to provide a satellite-borne antenna high-frequency cable temperature consistency control device structure.

[0012] According to the satellite-borne antenna high-frequency cable temperature consistency control device structure provided by the present application, the satellite-borne antenna high-frequency cable temperature consistency control device structure comprises:

[0013] A polyimide germanium film against the ground coating the satellite-borne super-large aperture antenna;

[0014] A multi-layer thermal insulation assembly against the sky coating the satellite-borne super-large aperture antenna;

[0015] High-frequency cables corresponding to each block of the satellite-borne super-large aperture antenna, wherein the high-frequency cables are entirely covered in the multi-layer thermal insulation assembly, and each high-frequency cable has an equal length, extends to the midpoint of the satellite-borne super-large aperture antenna in the length direction across the block, and finally converges into a cluster before entering the star body.

[0016] Preferably, the high-frequency cables themselves have no active thermal control measures.

[0017] Preferably, the spaceborne super-large aperture antenna has 2n sub-panels, and the high-frequency cables between the sub-panels and corresponding high-frequency cables are symmetrically distributed left and right;

[0018] The first sub-panel and the 2n sub-panel are outermost sub-panels, and the n sub-panel and the n+1 sub-panel are middle sub-panels;

[0019] The high-frequency cables of the outermost sub-panels are wired across the edges of the spaceborne super-large aperture antenna, avoiding the high-power device group on the spaceborne super-large aperture antenna;

[0020] The high-frequency cables of the 2nd to 2n-1 sub-panels are wound on the spaceborne super-large aperture antenna in different lengths, and after ensuring that the remaining cables are equal in length, they are merged into the main path

[0021] Preferably, the closer the high-frequency cables of the 2nd to 2n-1 sub-panels are to the middle sub-panels, the longer the winding on the spaceborne super-large aperture antenna.

[0022] Preferably, the high-frequency cables of the 2nd to 2n-1 sub-panels are arranged around each sub-panel, and through different winding turns, the remaining lengths of each cable are ensured to be equal when merged into the main path.

[0023] Preferably, the high-frequency cables are bound to the edges of each sub-panel using a clamp, and one clamp is arranged every 300-500 mm.

[0024] Preferably, the high-frequency cables have a turning radius of 400-600 mm when crossing the sub-panels.

[0025] Preferably, one or more thermistors are arranged on the high-frequency cables.

[0026] Preferably, the high-power device group is centrally installed on the array surface of the spaceborne super-large aperture antenna.

[0027] Preferably, the spaceborne super-large aperture antenna is also included.

[0028] Compared with the prior art, the present application has the following beneficial effects:

[0029] 1. The present application is particularly suitable for temperature consistency control of high-frequency cables of a spaceborne super-large aperture antenna under complex conditions of external heat flow and internal power consumption, and can meet the temperature consistency requirements of the high-frequency cables of the spaceborne super-large aperture antenna under different spatial environments and internal power consumption conditions.

[0030] 2. By using the present application, not only good thermal control effect is achieved, but also the entire device has high reliability and strong adaptability, and the entire device product relies on the thermal control measures of the antenna itself, and there is no problem of system start, termination and failure.

[0031] 3. The high-frequency cable in the application has no active thermal control measure, and through reasonable wiring arrangement, the temperature distribution characteristics of different positions of the antenna are used to obtain the beneficial effects of high reliability and good temperature control effect. BRIEF DESCRIPTION OF DRAWINGS

[0032] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments thereof, read in conjunction with the accompanying drawings:

[0033] Figure 1 The structure comparison schematic view between the plan view and the side view of the satellite-borne super-large aperture antenna high-frequency cable temperature consistency control device of one embodiment of the application.

[0034] Figure 2 The average temperature difference curve of the high-frequency cable thermal resistance of the sub-plate ZB1 and the sub-plate ZB8 of one embodiment of the application.

[0035] As shown in the drawings:

[0036] DETAILED DESCRIPTION

[0037] The application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that, for those skilled in the art, without departing from the concept of the application, a number of changes and improvements can be made. These all belong to the protection scope of the application.

[0038] For the satellite-borne super-large aperture antenna high-frequency cable, the number is large, the length is long, and the temperature distribution is uncertain after passing through different parts of the antenna and the star body. The application solves the problem of high-frequency cable temperature consistency control by reasonable cable layout, overall wrapping of multi-layer thermal insulation components and other measures, and guarantees the antenna electrical performance. The application solves the problem of satellite-borne super-large aperture antenna high-frequency cable temperature consistency control, and at the same time, adapts to the temperature demand under different external heat flow conditions, has the characteristics of less resource occupation, high adaptability, good reliability and flexible design.

[0039] The application provides a temperature consistency control device for a high-frequency cable of a spaceborne super-large aperture antenna, which comprises: a high-power device cluster installed on an array surface of the spaceborne super-large aperture antenna; a polyimide germanium film coated on a ground surface of the spaceborne super-large aperture antenna; a multilayer thermal insulation assembly coated on a sky surface of the spaceborne super-large aperture antenna; 16 sub-panels of the spaceborne super-large aperture antenna, which are symmetrically distributed on the left and right sides; one high-frequency cable on each sub-panel; a plurality of thermistors arranged at typical positions on the high-frequency cable; and the high-frequency cables being equal in length, the outermost sub-panel ZB1 crossing 7 sub-panels, the next outermost sub-panel ZB2 crossing 6 sub-panels, and the like, and finally converging into a cluster before entering a star body. The high-frequency cable itself has no active thermal control measure, and through reasonable arrangement of the high-frequency cable, the temperature distribution characteristics of different positions of the antenna are used, so that the high-frequency cable has high reliability and good temperature control effect.

[0040] The application will be specifically described below.

[0041] The spaceborne super-large aperture antenna has a length of more than 50 meters and a width of 2 meters, the 16 high-frequency cables are equal in length and have a length of 30 meters, and the temperature of the high-frequency cables at different positions is greatly different, which affects the electrical performance of the antenna. In this regard, the high-frequency cable of the sub-panel ZB1 is arranged along the edge of the antenna to avoid the high-power device cluster on the antenna, so as to prevent the occurrence of severe temperature fluctuations due to the start of the high-power device. Starting from the sub-panel ZB2, the high-frequency cable is wound on the antenna in different degrees, the remaining cables are equal in length, and then the cables are converged into a main path. The closer to the middle sub-panel ZB8, the longer the winding length on the antenna, and the cables are arranged around each sub-panel ZB as much as possible, and the number of winding turns is different to ensure that the remaining lengths of the cables are equal when the cables are converged into the main path.

[0042] As shown in Figure 1 , the high-frequency cable is entirely coated in the multilayer thermal insulation assembly on the back of the spaceborne super-large aperture antenna, so as to ensure that the cable temperature of the high-frequency cable does not fluctuate severely due to the complex external heat flow changes of the orbit. A plurality of thermistors are arranged at typical positions on the high-frequency cable for measuring the temperature. The high-frequency cable is bound to the edge of each sub-panel by a clamp, and one clamp is arranged every 300mm-500mm to ensure that the long-size high-frequency cable meets the mechanical conditions of the antenna. When the high-frequency cable crosses the sub-panels ZB of the antenna, the turning radius is 400mm-600mm, so as to ensure that the antenna folding and unfolding are not affected.

[0043] The application will be more specifically described below in combination with Figure 1 . In Figure 1For the convenience of illustration, only the left half of the symmetrical antenna is shown, and the right half adopts the same device structure. The high-frequency cable of the sub-plate ZB1 is wired along the edge of the space-borne super-large aperture antenna, avoids the high-power equipment group on the space-borne super-large aperture antenna, prevents the occurrence of severe temperature fluctuation due to the start of the high-power equipment, and is wired on the space-borne super-large aperture antenna in different degrees from the sub-plate ZB2. After ensuring that the remaining cables are equal in length, the cables are merged into the main path. The closer to the middle sub-plate ZB8, the longer the wiring on the space-borne super-large aperture antenna, and the cables are arranged as much as possible around each sub-plate, and the remaining lengths of each cable are ensured to be equal when merging into the main path through different winding numbers.

[0044] There are high-frequency cables on each of the sub-plates ZB1 to ZB8, and each cable has a length of 30 meters. There are 15 temperature measuring points for each cable, and each cable has 15 temperature measuring points. The temperature control problem of the high-power equipment group is solved, and the beneficial effects of high reliability and good temperature control effect are achieved.

[0045] Based on the above temperature control device, the temperature of the high-frequency cable of the space-borne super-large aperture antenna is tested and verified. The test simulates the out-of-orbit heat flow by combining the heater, the infrared cage and the wave-absorbing heat sink, and the antenna works according to the actual working mode.

[0046] The closer to the sub-plate ZB8, the higher the overall temperature in the sub-plates ZB1 to ZB8. Therefore, among the eight corresponding high-frequency cables, the temperature difference between the sub-plate ZB1 and the sub-plate ZB8 is the largest. By comparing the temperature difference, the temperature consistency of the eight high-frequency cables can be known. Figure 2 The average temperature difference curve of the high-frequency cable thermistors of the sub-plate ZB1 and the sub-plate ZB8 can be seen from the above test results. The average temperature difference of the high-frequency cables of the eight sub-plates is less than or equal to 3.5 DEG C. In the case that the antenna aperture is much larger than the conventional size, the temperature consistency is still good. The use requirements are met, and the antenna work is guaranteed.

[0047] It is proved by the above embodiment that the temperature consistency control device of the high-frequency cable of the space-borne super-large aperture antenna is stable, has the characteristics of good effect, good adaptability and convenient implementation of thermal control measures.

[0048] In summary, the temperature consistency control problem of the high-frequency cable of the space-borne super-large aperture antenna is solved, and the device can adapt to various orbits and working modes. According to the characteristics of the long length and high temperature consistency requirement of the high-frequency cable of the super-large aperture antenna, the high-frequency cable is wired on the antenna plate according to the temperature field characteristics of the antenna sub-plate, and the temperature consistency control is realized. With the development of space-borne radar technology, the antenna aperture area is increasing, and the temperature consistency control of the high-frequency cable of the same type of antenna can be designed by referring to the device.

[0049] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0050] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other in the case of no conflict.

Claims

1. A structure for a temperature uniformity control device for a spaceborne antenna high-frequency cable, characterized in that, include: A ground-facing polyimide germanium-coated film covering a spaceborne ultra-large aperture antenna; A multi-layered heat insulation component covering the surface of a spaceborne ultra-large aperture antenna; The high-frequency cables correspond one-to-one with each sub-board of the spaceborne ultra-large aperture antenna. The high-frequency cables are completely covered in multi-layer heat insulation components, and each high-frequency cable is of equal length. They extend across the sub-board to the midpoint of the length direction of the spaceborne ultra-large aperture antenna and finally converge into a bundle before entering the satellite. The spaceborne ultra-large aperture antenna consists of 2n sub-boards, and the sub-boards and corresponding high-frequency cables are symmetrically distributed from left to right. The first and 2nth sub-boards are the outermost sub-boards, and the nth and (n+1)th sub-boards are the middle sub-boards; The high-frequency cable of the outermost sub-plate runs across the edge of the spaceborne ultra-large aperture antenna, avoiding the high-power equipment group on the spaceborne ultra-large aperture antenna. The high-frequency cables of the second to the 2n-1th sub-boards are wound to varying degrees on the spaceborne ultra-large aperture antenna to ensure that the remaining cables are of equal length before merging into the main path. The closer the high-frequency cable of the second to the 2n-1th sub-board is to the middle sub-board, the longer the cable will be wound on the spaceborne ultra-large aperture antenna. The high-frequency cables of the second to the (2n-1)th sub-boards are arranged around each sub-board, and different numbers of windings are used to ensure that the remaining length of each cable is equal when it merges into the main path.

2. The structure of the spaceborne antenna high-frequency cable temperature uniformity control device according to claim 1, characterized in that, High-frequency cables themselves lack active thermal control measures.

3. The structure of the spaceborne antenna high-frequency cable temperature uniformity control device according to claim 1, characterized in that, High-frequency cables are secured to the edges of each sub-board using clamps, with one clamp placed every 300mm to 500mm.

4. The structure of the spaceborne antenna high-frequency cable temperature uniformity control device according to claim 1, characterized in that, When high-frequency cables cross sub-boards, the turning radius is 400mm to 600mm.

5. The structure of the spaceborne antenna high-frequency cable temperature uniformity control device according to claim 1, characterized in that, One or more thermistors are installed on the high-frequency cable.

6. The structure of the spaceborne antenna high-frequency cable temperature uniformity control device according to claim 1, characterized in that, High-power equipment clusters are installed on the array surface of the spaceborne ultra-large aperture antenna.

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