Phased array feed source device for antenna

Abstract

The invention relates to a phased array feed source device for an antenna, belongs to the technical field of radar antennas, and solves the technical problem of insufficient heat dissipation performance of a feed source device. The antenna comprises a horn radiation unit, a T / R assembly and a heat conduction table, the cross section of the heat conduction table is of an n-shaped axial symmetry structure, one end of the T / R assembly is fixed to the heat conduction table, and the other end of the T / R assembly is connected with the horn radiation unit through a connector. Through the arrangement of the heat conduction table, the T / R assembly is arranged in the heat conduction table, the heat radiation area is increased, the heat dissipation efficiency is improved, the horn radiation unit is also arranged on the heat conduction table and has a good supporting effect, after heat dissipation is conducted through the heat conduction table, the situation that the working efficiency of the horn radiation unit is reduced due to insufficient heat dissipation is avoided, and the overall weight of the structure can also be reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of radar antennas, and particularly to a phased array feed device for an antenna. Background Art

[0002] In the antenna feed structure of a synthetic aperture radar (SAR), poor heat dissipation of the T / R (Transmitter / Receiver) module can indirectly affect the performance of the radiation unit through thermal effects. Specifically, the T / R module, as the core component of an active phased array antenna, integrates temperature-sensitive devices such as high-power amplifiers and phase shifters. When the temperature of the module rises due to poor heat dissipation, the electrical performance of these devices will drift. For example, the phase accuracy of the phase shifter decreases, and the gain of the power amplifier fluctuates, which in turn causes deviations in the amplitude and phase of the excitation signal received by the radiation unit. Such deviations will directly change the radiation pattern characteristics of the radiation unit, such as beam pointing deviation, gain reduction or sidelobe level increase, ultimately resulting in a decrease in the overall radiation efficiency of the antenna, a deterioration in beam scanning accuracy, and even possible deformation of the array surface structure due to the accumulation of thermal stress, further破坏 the spatial phase consistency of the radiation unit and seriously affecting the detection performance and reliability of the SAR antenna.

[0003] Therefore, there is an urgent need for a phased array feed device with good heat dissipation effect to ensure the stable operation of the radiation unit of the antenna. Summary of the Invention

[0004] In view of the above technical problems existing in the prior art, the present invention proposes the following technical solutions: A phased array feed device for an antenna, comprising a horn radiation unit, a T / R module, and a heat conducting platform. The cross-section of the heat conducting platform has an axisymmetric structure in the shape of a "U", and includes a plurality of heat conducting platform units arranged side by side. The phased array feed device is fixedly connected to the upper deck of the satellite payload compartment through the bottom surface of the heat conducting platform unit; One end of the T / R module is fixed on the heat conducting platform, and the other end is connected to the horn radiation unit through a connector. A high-frequency circuit board for a calibration power distribution network is provided below the T / R module; Furthermore, the horn radiation unit includes multiple groups of single-polarization horn antenna units. Each group of single-polarization horn antenna units includes a plurality of single-polarization horn antennas connected in sequence. The horn structures of adjacent single-polarization horn antennas share a side wall.

[0005] It should be noted that in the translation of the text in item , the part "进一步破坏" in Chinese is an incorrect expression in the original text. It is guessed that it may be "进一步破坏", and the translation is given accordingly. If there is an error, please correct it according to the correct content.Furthermore, the heat conduction table unit is provided with a cavity, in which a T / R component and a phase change module are fixedly arranged. Specifically, the heat conduction table unit includes a heat conduction skeleton and a "C" - shaped sealing plate covering the heat conduction skeleton. The heat conduction skeleton includes a heat conduction top plate and two symmetrical "L" - shaped heat conduction side walls. The top of the heat conduction top plate is flush with the top of the heat conduction side walls. The heat conduction top plate is arranged in the middle of the two heat conduction side walls. The heat conduction top plate, the sealing plate and the heat conduction side walls enclose two cavities, and the T / R component and the phase change module are respectively and fixedly arranged in the two cavities.

[0006] Furthermore, the thickness of the heat conduction top plate is less than the thickness of the heat conduction side walls.

[0007] Furthermore, the top of the heat conduction top plate is used to place the horn radiation unit, and the phased array feeder device is fixedly connected to the upper deck plate of the satellite's payload compartment through the bottom surface of the heat conduction side wall.

[0008] Furthermore, the phase change module is octadecane phase change material, which is used to absorb the heat generated when the T / R component works.

[0009] Furthermore, the number of the heat conduction table units is 12. There are 2 T / R components arranged in the cavity of each heat conduction table unit, and there are 24 T / R components in total.

[0010] Furthermore, there are 12 groups of single - polarization horn antenna units in total. Each group of single - polarization horn antenna units is connected to the 2 T / R components fixed on each heat conduction table unit.

[0011] Furthermore, each group of single - polarization horn antenna units includes 8 single - polarization horn antennas. The T / R component is a 4 - channel T / R component, and each T / R component is connected to 4 single - polarization horn antennas.

[0012] Furthermore, both the T / R component and the single - polarization horn antenna have feeding interfaces, and the feeding interfaces are SMP interfaces. The T / R component and the single - polarization horn antenna are connected by blind plugging through the SMP interfaces.

[0013] Furthermore, the material of the heat conduction table is aluminum alloy. [[ID=]]

[0014] The present invention has at least one of the following beneficial effects: (1) By setting up a heat conduction platform with a "Ji" - shaped axisymmetric structure and placing the T / R component inside the heat conduction platform, on the one hand, it can increase the area of heat radiation and improve the heat dissipation efficiency. On the other hand, the horn radiation unit is also set on the heat conduction platform. The heat conduction platform has a good supporting effect on the horn radiation unit, and after heat dissipation through the heat conduction platform, the horn radiation unit will not have its working efficiency reduced due to insufficient heat dissipation. In addition, the horn structures share a side wall, which can also reduce the overall weight of the structure; (2) The bottom surface of the heat conduction side wall is firmly connected to the upper cabin plate of the satellite's payload cabin. Through the connection between the bottom surface of the heat conduction side wall and the cabin plate, heat conduction between the bottom surface of the heat conduction platform and the cabin plate can be achieved. Combining with the surface heat radiation of the heat conduction side wall, it enriches the heat dissipation form and improves the heat dissipation effect, further ensuring...

[0015] In the present invention, the above - mentioned technical solutions can also be combined with each other to achieve more preferred combination schemes. Other features and advantages of the present invention will be elaborated in the subsequent content. Moreover, some advantages can be made obvious from the description or understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the content specifically pointed out in the text and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings are only used for the purpose of showing specific embodiments and are not considered as limitations to the present invention. Throughout the drawings, the same reference signs represent the same components; Figure 1 is a schematic structural diagram of the feed device in Embodiment 1; Figure 2 is a front view of the feed device in Embodiment 1; Figure 3 is a top view of the heat conduction platform unit (taking 2 as an example) in Embodiment 1; Figure 4 is an overall temperature distribution diagram of the heat conduction platform in Embodiment 1; Figure 5 is a temperature distribution diagram of the T / R component in Embodiment 1; Figure 6 is a single - track temperature change curve diagram of the T / R component in Embodiment 1; Figure 7 is a schematic structural diagram of the horn radiation unit in Embodiment 2; Figure 8 is a standing - wave simulation result diagram of the horn radiation unit in Embodiment 2; Figure 9 is a simulation result diagram of the range - direction pattern of the horn radiation unit in Embodiment 2; Figure 10 is a simulation result diagram of the azimuth - direction pattern of the horn radiation unit in Embodiment 2; Figure 11 It is the working principle diagram of the T / R component in Embodiment 3; Figure 12 It is the structural schematic diagram of the T / R component in Embodiment 3; Figure 13 It is the integrated power supply wave control principle diagram in Embodiment 3; Figure 14 It is the structural schematic diagram of the integrated power supply wave control in Embodiment 3; In the figure: 100 - heat conduction table, 110 - heat conduction table unit, 120 - heat conduction skeleton, 130 - sealing plate, 121 - heat conduction top plate, 122 - heat conduction side wall, 140 - phase change module, 150 - cavity, 200 - T / R component, 300 - horn radiation unit, 310 - single - polarization horn antenna unit, 311 - single - polarization horn antenna. Specific implementation manners

[0017] Next, the preferred embodiments of the present invention will be specifically described with reference to the accompanying drawings. Among them, the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principle of the present invention, rather than to limit the scope of the present invention.

[0018] Embodiment 1: Refer to Figure 1 , Figure 2 As shown, the present invention provides a phased - array feeder device for an antenna, including a horn radiation unit 300, a T / R component 200, and a heat conduction table 100. The cross - section of the heat conduction table 100 is an axisymmetric structure in the shape of a "U", including a plurality of heat conduction table units 110 arranged side by side. The phased - array feeder device is fixedly connected to the upper cabin plate of the satellite's payload cabin through the bottom surface of the heat conduction table unit 110. One end of the T / R component 200 is fixed on the heat conduction table 100, and the other end is connected to the horn radiation unit 300. Since the working environment of the SAR antenna feeder is a space - borne vacuum environment without air convection, heat dissipation can only be carried out through heat conduction or heat radiation. Therefore, by setting the heat conduction table 100 with an axisymmetric structure in the shape of a "U", the T / R component is arranged inside the heat conduction table. On the one hand, the heat radiation area can be increased to improve the heat dissipation efficiency. On the other hand, the horn radiation unit is also arranged on the heat conduction table. The heat conduction table has a good supporting effect on the horn radiation unit, and after heat dissipation through the heat conduction table, the horn radiation unit will not have its working efficiency reduced due to insufficient heat dissipation.

[0019] Refer to Figure 2 , Figure 3Furthermore, the heat conduction platform unit 110 includes a heat conduction frame 120 and a U-shaped sealing plate 130 covering the heat conduction frame 120. The heat conduction frame 120 includes a heat conduction top plate 121 and two symmetrical L-shaped heat conduction sidewalls 122. The top of the heat conduction top plate 121 is flush with the top of the heat conduction sidewalls 122. The heat conduction top plate 121 is located in the middle of the two heat conduction sidewalls. The thickness of the heat conduction top plate 121 is less than the thickness of the heat conduction sidewalls 122. The heat conduction top plate 121, the sealing plate 130 and the heat conduction sidewalls 122 form two cavities 150. The T / R assembly 200 and the phase change module 140 are fixedly installed in the two cavities 150 respectively.

[0020] The phase change module 140, which is installed in the cavity 150 formed between the heat-conducting sidewall 122, the heat-conducting top plate 120, and the sealing plate 130, can directly absorb the heat emitted by the T / R component 200 and dissipate heat through phase change. On the other hand, the sidewall of the heat-conducting frame 120 increases the area of ​​heat radiation, which comprehensively improves the heat conduction effect of the heat-conducting platform 100 and ensures the operating temperature of the T / R component 200.

[0021] Furthermore, the top of the heat-conducting top plate 121 is used to place the horn radiation unit 300, and the phased array feed device is fastened to the upper compartment plate of the satellite's payload bay through the bottom surface of the heat-conducting side wall 122.

[0022] By connecting the bottom surface of the heat-conducting sidewall 22 to the compartment plate, heat conduction between the bottom surface of the heat-conducting platform and the compartment plate can be realized. Combined with the surface heat radiation of the heat-conducting sidewall, the heat dissipation methods are enriched and the heat dissipation effect is improved.

[0023] Furthermore, the phase change module 140 is made of octadecane phase change material, which is used to absorb the heat generated when the T / R component 200 is in operation.

[0024] Octadecylane has a melting point of 28.2℃, which is compatible with the operating temperature of the T / R module in the feed at around 45℃, thus ensuring the heat dissipation effect of the T / R module.

[0025] Furthermore, the heat conduction stage 100 is made of aluminum alloy.

[0026] The high thermal conductivity of aluminum alloy materials can further and quickly dissipate the working heat of the T / R components, ensuring the operating temperature.

[0027] Furthermore, a high-frequency circuit board for scaling the power distribution network is disposed below the T / R component 200.

[0028] The present invention performs a thermal analysis on the structure of the heat-conducting stage. The process and results of the thermal analysis are as follows: Thermal analysis was performed on the structure of the heat conduction stage consisting of 12 heat conduction stage units 110. The heat conduction stage 100 is used to install and fix 24 T / R components. The entire heat conduction stage is made of aluminum alloy. The phase change module uses octadecane phase change material to absorb and store the heat generated by the T / R components during operation.

[0029] 1) Thermal design input conditions: a) Heat consumption and operating time: The heat consumption of each T / R module is 60W; b) Temperature range of the external TR assembly; Operating temperature range: -20℃ to +50℃; Storage temperature range: -30℃ to +60℃; c) Temperature range of external feed radiation unit: Operating temperature range: -50℃ to +60℃; Storage temperature range: -50℃ to +60℃; d) Temperature gradient: All feed sources: ≤12℃; T / R module interior: ≤7℃; e) Heat Dissipation Conditions and Interface: The SAR antenna feed operates in a vacuum environment on-board, with no air convection. There are two heat dissipation methods: heat conduction from the bottom surface of the heat-conducting platform and heat radiation from the surface of the heat-conducting platform. The thermal interface between the phased array feed and the satellite platform is located on the bottom surface of the heat-conducting platform.

[0030] 2) Material properties of the heat conduction stage The heat-conducting stage uses a 7075 aluminum alloy body with a thermal conductivity of 130 W / m•K, a density of 2.81 g / cm³, and a specific heat of 960 J / kg•K. The phase change material is octadecane, with a melting point of 28.2℃, a density of 0.748 g / cm³ (at 70℃), a specific heat of 1950 L / kg•K, and a latent heat of phase change of 243 kJ / kg.

[0031] 3) Thermal simulation process and results a) Simplification of thermal analysis model The thermal environment of a satellite is quite complex, with numerous heat-generating devices. While in orbit, the satellite is exposed to varying amounts of sunlight at different locations, and is also affected by factors such as sunlight reflected from Earth and infrared radiation from the Earth. The thermal environment affects the satellite body and its various modules in a complex manner. To simplify calculations, the following simplifications were made in the thermal analysis: the contact surfaces between the modules and the heat-conducting platform have good thermal conductivity, allowing heat to be transferred away quickly; the thermal characteristics of each device are independent and do not affect the feed source, which can be considered independently; the feed source is in a weightless state; the feed source operates in a "vacuum" state, and air convection is negligible.

[0032] b) Thermal analysis model building A model was established based on the composition, thermal design method, and heat distribution of the feed source. The contact surface temperature between the bottom of the heat-conducting platform and the cabin plate was 25°C. The TR component and the heat-conducting frame 120 were installed in good contact. The thermal network analysis model was solved using the thermal analysis software UG_NX, with 21,684 network nodes.

[0033] c) Thermal analysis results See Figures 4-6 The thermal analysis results show that after 3 minutes of operation, the highest shell temperature of the T / R component is 44.8℃, with a temperature uniformity of 1.6℃, meeting the temperature requirements. The thermal analysis calculations demonstrate that the thermal design of the SAR antenna feed is reasonable and feasible, and the shell temperature of the TR component meets the temperature specifications.

[0034] Example 2: Based on Example 1, see Figure 2 , Figure 3 , Figure 7 The horn radiating unit 300 includes multiple sets of single-polarized horn antenna units 310. Each set of single-polarized horn antenna units 310 includes multiple single-polarized horn antennas 311 connected in sequence. The horn structures of adjacent single-polarized horn antennas 311 share a sidewall.

[0035] Because the horn structure shares a single sidewall, the overall weight of the structure can be significantly reduced. Simultaneously, the reduced number and number of connecting components improves the overall mechanical stability and vibration resistance. More importantly, the weight reduction can directly lower transmission costs or increase the payload ratio. Furthermore, the modular design with a shared sidewall can support rapid expansion of the antenna array while maintaining structural compactness, adapting to the needs of arrays of different sizes.

[0036] Furthermore, the number of heat conduction stage units 110 is specifically 12, and two T / R components 200 are installed in the cavity 130 of the heat conduction stage unit 110, for a total of 24 T / R components 200.

[0037] There are 12 groups of single-polarized horn antenna units 310. Each group of single-polarized horn antenna units 310 is connected to two T / R components 200 fixed on each heat conduction stage unit 110.

[0038] Each group of single-polarized horn antenna units 310 includes 8 single-polarized horn antennas 311. The T / R assembly 200 has 4 channels, and each T / R assembly 200 is connected to 4 single-polarized horn antennas 311.

[0039] Both the T / R assembly 200 and the single-polarized horn antenna 311 have a power supply interface, which is an SMP (SubMiniature version P connector) interface. The T / R assembly 200 and the single-polarized horn antenna 311 are connected by blind insertion through the SMP interface.

[0040] The blind plugging feature of the SMP interface enables rapid alignment between the TR components and the antenna, reducing manual debugging time and being suitable for automated assembly lines.

[0041] At this time, the total number of antenna radiation units of the feed device, equipped with only 4-channel TR components. The TR components and the radiation units are interconnected through SMP blind plugging. The TR components are fixed on a "C-shaped" heat conduction platform by themselves, and the overall heat conduction platform is further fastened to the upper deck of the payload compartment.

[0042] Taking the arrangement direction of the heat conduction platform unit 110 as the distance direction of the horn radiation unit 300, and taking the horizontal direction of the plane where the "C-shaped" cross-section of the heat conduction platform unit 110 is located as the azimuth direction of the horn radiation unit 300.

[0043] The standing wave of the horn radiation unit 300 and the primary radiation patterns in the distance direction and azimuth direction are respectively simulated and tested. The simulation results are shown in Figures 8-10 . According to the simulation results, in the frequency range of 9.0 - 10.2 GHz, the horn standing wave < 1.36, the beam width in the distance direction of the horn is 62.8 degrees, and the beam width in the azimuth direction is 85.4 degrees, meeting the designed usage requirements.

[0044] Embodiment 3: Based on Embodiment 1 or Embodiment 2, further, referring to Figure 11 , the present invention also proposes a specific design of the T / R component. Specifically, the four-channel delay T / R component includes transmitting and receiving channels, and is composed of a load-state transceiver switch, a transceiver digital phase shifter, a receiving digital attenuator, a 5-bit delay chip (8λ / 4λ / 2λ / 1λ / 0.5λ), a low-noise amplifier, a driver amplifier, a power amplifier, a bidirectional amplifier, a limiter, a circulator, a power modulator, a drive control circuit, etc. The peak transmitting power of each channel is 50 W, the component efficiency ≥ 40%, the receiving gain is 28 dB, and the noise figure ≤ 3 dB.

[0045] During transmission, high-power amplification of the transmission signal is completed, and during reception, low-noise amplification of the reception signal is completed. The transceiver conversion is completed under the control of the TR signal. The transceiver phase shift, receiving gain, transceiver delay, and the load-state mode of each T / R channel are all controlled by an integrated power wave control.

[0046] The control drive circuit converts the serial control code input by the wave controller into parallel code and stores it in a register. Driven by the drive circuit, the output controls the transmit digitally controlled phase shifter, receive digitally controlled phase shifter, receive digitally controlled attenuator, transmit delay, receive delay, transmit / receive switch status, and load status of the T / R component. Transmit and receive share the same digital phase shifter and delay chip, while transmit and receive control codes are separate, and switching control is completed under the control of the TR signal.

[0047] The TR component's external structure diagram is as follows: Figure 12 As shown, X1G~X4G are SMP transceiver interfaces that plug into the speaker, X5G is the SMP calibration signal interface, X6G is the SMA (SubMiniature version A connector) transceiver port, and X1 is the low-frequency input interface.

[0048] The schematic diagram and structural diagram of the integrated power supply wave control unit are as follows: Figure 13 , Figure 14 As shown. Each integrated power wave controller corresponds to four 4-channel TR components, which can meet the power consumption requirement of up to 500W.

[0049] The integrated power beam controller receives channel control data from a highly integrated central electronic device, parses it, and forwards it to the 4-channel TR component. Simultaneously, it reports collected telemetry information to the system. The antenna distributor provides a 42V high-voltage primary bus to the integrated power beam controller.

[0050] The four-channel delay T / R component technology proposed in this invention achieves high-precision beam control, low-noise reception (noise figure ≤3dB), and high-power transmission (50W per channel) by integrating a 5-bit delay chip (maximum 8λ delay), a digital phase shifter / attenuator, and an integrated power beam control unit. Combined with SMP / SMA standardized interfaces and blind-mating design, it significantly improves system integration efficiency and electromagnetic compatibility. Its integrated "power + beam control" architecture and efficient thermal management with heat dissipation platform ensure high reliability and environmental adaptability. The solution also has multi-channel expansion potential and frequency band / polarization adaptation flexibility.

[0051] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A phased array feed device for an antenna, comprising a horn radiation unit (300), a T / R component (200), and a heat conducting platform (100), characterized in that: The cross-section of the heat conducting platform (100) is an axisymmetric structure in the shape of "ji", and includes a plurality of heat conducting platform units (110) arranged side by side. The phased array feed device is fixedly connected to the upper cabin plate of the payload cabin of the satellite through the bottom surface of the heat conducting platform unit (110); One end of the T / R component (200) is fixed on the heat conducting platform (100), and the other end is connected to the horn radiation unit (300).

2. The phased array feed device for an antenna as described in claim 1, characterized in that: The horn radiation unit (300) includes multiple groups of single-polarization horn antenna units (310). Each group of single-polarization horn antenna units (310) includes a plurality of single-polarization horn antennas (311) connected in sequence. The horn structures of adjacent single-polarization horn antennas (311) share a side wall.

3. A phased array feed device for an antenna as described in claim 2, characterized in that: The heat conducting platform unit (110) is provided with a cavity (150), and a T / R component (200) and a phase change module (140) are fixedly arranged in the cavity (150).

4. A phased array feed device for an antenna as described in claim 3, characterized in that: The phase change module (140) is an octadecane phase change material for absorbing the heat generated when the T / R component (200) works.

5. A phased array feed device for an antenna as described in claim 3 or 4, characterized in that: The number of the heat conducting platform units (110) is 12, and 2 T / R components (200) are arranged in the cavity (130) of the heat conducting platform unit (110).

6. A phased array feed device for an antenna as described in claim 5, characterized in that: There are 12 groups of the single-polarization horn antenna units (310) in total, and each group of single-polarization horn antenna units (310) is connected to 2 T / R components (200) fixed on each heat conducting platform unit (110).

7. A phased array feed device for an antenna as described in claim 6, characterized in that: Each group of single-polarization horn antenna units (310) includes 8 single-polarization horn antennas (311). The T / R component (200) is 4-channel, and each T / R component (200) is connected to 4 single-polarization horn antennas (311).

8. A phased array feed device for an antenna as described in claim 7, characterized in that: Both the T / R component (200) and the single-polarization horn antenna (311) have feeding interfaces, and the feeding interfaces are SMP interfaces. The T / R component (200) and the single-polarization horn antenna (311) are connected by blind plugging through the SMP interfaces.

9. A phased array feed device for an antenna as described in any one of claims 1-4, characterized in that: The material of the heat conducting platform (100) is aluminum alloy.

10. A phased array feed device for an antenna as described in any one of claims 1-4, characterized in that: A high-frequency circuit board for a calibration power distribution network is arranged below the T / R component (200).

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