Satellite-borne communication integrated board and communication satellite

Abstract

The application provides a satellite-borne communication integrated board and a communication satellite, and relates to the technical field of communication satellites. The satellite-borne communication integrated board comprises a structural support frame, a phased array antenna assembly, a solar wing photovoltaic assembly and a main control board. The structural support frame comprises a plurality of reinforcing ribs, and a first fixing area and a second fixing area are formed by the reinforcing ribs. The first fixing area is a hollow area, and a plurality of through holes are formed in the second fixing area by the reinforcing ribs. The first surface of the phased array antenna assembly is provided with an antenna array surface, and the second surface of the phased array antenna assembly is fixed to the reinforcing ribs of the structural support frame. The first surface of the solar wing photovoltaic assembly is provided with a power generation unit, and the second surface of the solar wing photovoltaic assembly is fixed to the reinforcing ribs of the structural support frame. The main control board is fixed to the orthographic projection area of the first fixing area on the second surface of the solar wing photovoltaic assembly, and the main control board is connected with a plurality of transceiver assemblies. The application realizes the communication between the satellite and the ground station, and achieves the effects of reducing the volume and weight.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of communication antenna, in particular to a satellite-borne communication integrated board and a communication satellite. BACKGROUND

[0002] At present, among the commercial low-orbit satellites launched in recent years, the proportion of communication satellites is more than 50%, and satellite communication technology has received more attention. Satellite communication technology is supported by many communication payloads, such as phased array communication antennas and parabolic antennas. The communication antenna is the core part of the satellite-borne communication integrated board and is the key factor to determine the signal transmission quality. Using a large-area antenna can improve the gain of signal reception and transmission, thereby improving the communication quality. When the communication antenna is used, the satellite solar wing needs to power the communication function of the large-area antenna.

[0003] However, the satellite solar wing and the communication antenna in the prior art are separately arranged on the satellite, which results in large volume and weight, the need for more control signals and power supply lines, and the increase of the weight and size of the entire satellite, thereby increasing the satellite development cost. SUMMARY

[0004] Therefore, the purpose of the present application is to provide a satellite-borne communication integrated board and a communication satellite to overcome at least one of the above-mentioned defects.

[0005] In a first aspect, the embodiments of the present application provide a satellite-borne communication integrated board, which comprises: a structure support frame, the structure support frame comprises a plurality of reinforcing ribs, and a first fixed area and a second fixed area are formed by the plurality of reinforcing ribs, the first fixed area is a hollow area, and a plurality of through holes are formed in the second fixed area by the reinforcing ribs; a phased array antenna assembly, an antenna array surface is arranged on a first surface of the phased array antenna assembly, the antenna array surface is formed by a plurality of antenna sub-arrays arranged in a phased array form, a second surface of the phased array antenna assembly is fixed to the reinforcing ribs of the structure support frame, a plurality of transceiver assemblies are arranged on the second surface of the phased array antenna assembly, a predetermined number of transceiver assemblies are connected to a corresponding antenna sub-array, and the plurality of transceiver assemblies are embedded into the plurality of through holes; a solar wing photovoltaic assembly, a power generation unit is arranged on a first surface of the solar wing photovoltaic assembly, and a second surface of the solar wing photovoltaic assembly is fixed to the reinforcing ribs of the structure support frame; a main control board, the main control board is fixed to a normal projection area of the first fixed area on the second surface of the solar wing photovoltaic assembly, and the main control board is connected to the plurality of transceiver assemblies.

[0006] In an alternative embodiment of the present application, the phased array antenna assembly comprises a first fixed plate and a plurality of antenna sub-assemblies, each antenna sub-assembly comprising an antenna sub-array, a digital plate and the predetermined number of transceiver assemblies, wherein the plurality of antenna sub-arrays are fixed on a first surface of the first fixed plate in a phased array form, a first surface of each digital plate is fixed within a footprint of a corresponding one of the antenna sub-arrays on a second surface of the first fixed plate, and the predetermined number of transceiver assemblies are formed into groups, each group being arranged on a second surface of a corresponding one of the digital plates, and the predetermined number of transceiver assemblies in each group are arranged in an array form on the second surface of the corresponding digital plate.

[0007] In an alternative embodiment of the present application, each digital plate is connected to the master control plate, such that the master control plate is configured to convert digital signals and analog signals between the ground station and the satellite.

[0008] In an alternative embodiment of the present application, the solar wing photovoltaic assembly comprises a plurality of power generation units and a second fixed plate, each power generation unit is fixed on a first surface of the second fixed plate, and a second surface of the second fixed plate is fixed to the reinforcing rib of the structural support frame.

[0009] In an alternative embodiment of the present application, the first fixed region comprises a first target region and a second target region, the first target region is a footprint of the master control plate fixed on the second surface of the solar wing photovoltaic assembly, and the satellite-borne communication integrated plate further comprises a battery unit, wherein a first side surface and a second side surface of the battery unit are respectively provided with a predetermined number of mounting ears, an inner surface of the reinforcing rib of the second target region of the structural support frame is provided with a predetermined number of support seats, and an outer contour of the mounting ear and an inner contour of the support seat are adapted in shape to fix the battery unit in the second target region of the structural support frame.

[0010] In an alternative embodiment of the present application, the satellite-borne communication integrated plate further comprises an attitude control plate, the attitude control plate comprises a circuit board and a plurality of magnetic torque devices, wherein each magnetic torque device is integrated on a first surface of the circuit board, and a plurality of fixing members are arranged at a frame of a second surface of the circuit board, such that the second connecting member fixes the attitude control plate on the reinforcing rib of the structural support frame through the fixing members to fix the attitude control plate in the second target region of the structural support frame.

[0011] In an optional embodiment of the application, the satellite-borne communication integrated board further comprises a thermal control unit, the thermal control unit comprising a heat dissipation material and a plurality of temperature sensors, wherein the heat dissipation material is applied on the first fixed plate of the phased array antenna assembly except for the antenna array surface to achieve heat dissipation of the phased array antenna assembly; the temperature sensors are installed at preset positions of the first fixed plate of the phased array antenna assembly to detect the temperature of the first fixed plate and send the temperature to the main control board; the temperature sensors are installed at preset positions of the second surface of the solar wing photovoltaic assembly to detect the temperature of the second surface and send the temperature to the main control board; the temperature sensors are installed at preset positions of the surface of the battery unit to detect the temperature of the battery unit and send the temperature to the main control board; the temperature sensors are installed at preset positions of the surface of the circuit board of the attitude control board to detect the temperature of the circuit board and send the temperature to the main control board.

[0012] In an optional embodiment of the application, the power supply interface of the solar wing photovoltaic assembly is electrically connected to the power supply interface of the battery unit through an energy line to convert solar energy into electrical energy and store the electrical energy in the battery unit; the power supply interface of the battery unit is electrically connected to the power supply interface of the main control board through an energy line to supply power to the main control board; the power supply interface of the battery unit is electrically connected to the power supply interface of the attitude control board through an energy line to supply power to the attitude control board; the power supply interface of the battery unit is electrically connected to the power supply interface of the phased array antenna assembly through an energy line to supply power to the phased array antenna assembly; and the power supply interface of the battery unit is electrically connected to the power supply interface of the plurality of temperature sensors through an energy line to supply power to the plurality of temperature sensors.

[0013] In an optional embodiment of the present application, the input and output interface of the main control board is connected with the input and output interface of the digital board of the phased array antenna assembly through a signal line to transmit and receive data with the ground station via the antenna subarray; the input and output interface of the main control board is connected with the input and output interface of the circuit board of the attitude control board through a signal line to send the attitude control signal to the circuit board to adjust the attitude of the on-board communication integrated board; the input and output interface of the main control board is connected with the input and output interface of the solar wing photovoltaic assembly through a signal line to determine whether the solar wing photovoltaic assembly is collecting solar energy by detecting the output voltage of the solar wing photovoltaic assembly; the input and output interface of the main control board is connected with the input and output interface of the battery unit through a signal line to control the battery unit to discharge and supply power to the on-board communication integrated board when it is detected that the solar wing photovoltaic assembly is not collecting solar energy; the input and output interface of the main control board is connected with the input and output interface of a plurality of temperature sensors through a signal line to receive the temperature detected by the plurality of temperature sensors and send the temperature to the satellite main controller of the communication satellite body to display on the communication satellite.

[0014] In a second aspect, the embodiments of the present application also provide a communication satellite, comprising: a communication satellite body; a satellite main controller arranged inside the communication satellite body; and the on-board communication integrated board in any of the optional embodiments above, wherein the main control board in the on-board communication integrated board is connected with the satellite main controller to form information interaction.

[0015] The on-board communication integrated board and the communication satellite provided by the embodiments of the present application comprise a structural support frame, the structural support frame comprises a plurality of reinforcing ribs, and a first fixed region and a second fixed region are formed by the plurality of reinforcing ribs, the first fixed region is a hollow region, and a plurality of through holes are formed by the reinforcing ribs in the second fixed region; a phased array antenna assembly, an antenna array surface is arranged on a first surface of the phased array antenna assembly, and a second surface of the phased array antenna assembly is fixed to the reinforcing ribs of the structural support frame; a solar wing photovoltaic assembly, a power generation unit is arranged on a first surface of the solar wing photovoltaic assembly, and a second surface of the solar wing photovoltaic assembly is fixed to the reinforcing ribs of the structural support frame; and a main control board, the main control board is fixed to a region in the first fixed region which is orthogonally projected onto the second surface of the solar wing photovoltaic assembly, and the main control board is connected with a plurality of transceiver assemblies. The communication between the satellite and the ground station is realized by the present application, and the effect of reducing the volume and weight is achieved.

[0016] In order to make the above objectives, characteristics and advantages of the present application more apparent and easy to understand, the following preferred embodiments are specifically described below with reference to the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced as follows. It should be understood that the following drawings only show some of the embodiments of the present application, and therefore should not be regarded as a limitation on the scope, and for those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0018] Figure 1 Structure schematic diagram of a satellite-borne communication integrated board provided by the embodiments of the present application;

[0019] Figure 2 Structure schematic diagram of an antenna array plane of a phased array antenna assembly provided by the embodiments of the present application;

[0020] Figure 3 Structure schematic diagram of an antenna sub-assembly in a phased array antenna assembly provided by the embodiments of the present application;

[0021] Figure 4 Structure schematic diagram of a satellite-borne communication integrated board provided by the embodiments of the present application;

[0022] Figure 5 Structure schematic diagram of a phased array antenna assembly provided by the embodiments of the present application;

[0023] Figure 6 Structure schematic diagram of working principle of a TR assembly in a phased array antenna assembly provided by the embodiments of the present application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be described clearly and completely in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. Based on the embodiments of the present application, every other embodiment obtained by those skilled in the art without creative labor belongs to the scope of the present application.

[0025] Firstly, the application scenarios applicable to the present application are introduced. The present application can be applied to the field of communication antenna technology.

[0026] It is found through research that the communication antenna is a core part of the on-board communication integrated board and is a key factor for determining signal transmission quality. A large-area antenna can improve the gain of signal reception and transmission, thereby improving communication quality. When the communication antenna is used, the satellite solar wing needs to power the communication function of the large-area antenna. However, the satellite solar wing and the communication antenna in the prior art are separately arranged on the satellite, which results in a large volume and weight, requires more control signals and power supply lines, and increases the weight and size of the entire satellite and the satellite development cost.

[0027] Therefore, an embodiment of the present application provides an on-board communication integrated board and a communication satellite, which include a structure support frame, the structure support frame including a plurality of reinforcing ribs and forming a first fixed area and a second fixed area by the plurality of reinforcing ribs, the first fixed area being a hollow area, and the second fixed area including a plurality of through holes formed by the reinforcing ribs; a phased array antenna assembly, the first surface of the phased array antenna assembly being provided with an antenna array surface, and the second surface of the phased array antenna assembly being fixed to the reinforcing ribs of the structure support frame; a solar wing photovoltaic assembly, the first surface of the solar wing photovoltaic assembly being provided with a power generation unit, and the second surface of the solar wing photovoltaic assembly being fixed to the reinforcing ribs of the structure support frame; and a main control board, the main control board being fixed to the orthographic projection area of the first fixed area on the second surface of the solar wing photovoltaic assembly, and the main control board being connected with a plurality of transceiver assemblies. The present application realizes communication between the satellite and the ground station, and achieves the effects of reducing the volume and weight.

[0028] Please refer to Figure 1 , Figure 1 for a structural schematic diagram of the on-board communication integrated board provided by the embodiment of the present application. As shown in Figure 1 , the on-board communication integrated board provided by the embodiment of the present application includes a structure support frame 1, a phased array antenna assembly 2, a solar wing photovoltaic assembly 3, and a main control board 4.

[0029] Specifically, the structure support frame includes a plurality of reinforcing ribs and forms a first fixed area 5 and a second fixed area 6 by the plurality of reinforcing ribs.

[0030] The first fixed area 5 is a hollow area, and the second fixed area 6 includes a plurality of through holes formed by the reinforcing ribs.

[0031] For example, the reinforcing ribs can be made of metal materials such as aluminum alloy and titanium alloy, which have high strength and rigidity and can meet the basic requirements of the satellite structure.

[0032] Specifically, the first surface of the phased array antenna assembly is provided with an antenna array surface, and the antenna array surface is formed by a plurality of antenna sub-arrays arranged in a phased array form.

[0033] The phased array antenna assembly is composed of multiple antenna sub-assemblies, each of which has independent and complete functions, arranged together according to certain rules to form a large array surface, to achieve greater antenna gain and fast data communication. In addition, the phased array antenna assembly combines multiple antenna sub-assemblies through spatial structural layout to expand the scanning space.

[0034] Referring to Figure 2 , Figure 2 The structure diagram of the antenna array surface of the phased array antenna assembly provided by the embodiment of the present application is shown in the figure. Figure 2 As shown in the figure, the first surface of the phased array antenna assembly provided by the embodiment of the present application includes an antenna sub-array 21.

[0035] For example, 16 antenna sub-arrays 21 are arranged in the form of a phased array to form an antenna array surface, the antenna array surface is a 4x4 array, and the number of antenna sub-arrays is 16.

[0036] Here, the gain of a single antenna in the phased array load antenna is about 5dB, the antenna bandwidth meets the requirement of 4.7-5.0GHz, the gain is increased, and the bandwidth requirement is reduced.

[0037] The second surface of the phased array antenna assembly 2 is fixed to the stiffener of the structural support frame 1, a plurality of transceiver assemblies are arranged on the second surface of the phased array antenna assembly 2, a predetermined number of transceiver assemblies are connected to a corresponding antenna sub-array 21, and the plurality of transceiver assemblies are embedded into a plurality of through holes.

[0038] Referring to Figure 3 , Figure 3 The structure diagram of the antenna sub-assembly in the phased array antenna assembly provided by the embodiment of the present application is shown in the figure. Figure 3 As shown in the figure, the antenna sub-assembly provided by the embodiment of the present application includes an antenna sub-array 21, a digital board 22, and a transceiver assembly 23.

[0039] The phased array antenna assembly includes a first fixed plate 24 and a plurality of antenna sub-assemblies, each of which includes an antenna sub-array 21, a digital board 22, and a predetermined number of transceiver assemblies 23.

[0040] For example, the first fixed plate can be an aluminum alloy plate, and the layout is arranged to realize the transmission and reception of signals between the antenna sub-array and the digital board.

[0041] Wherein, the plurality of antenna subarrays 21 are fixed on the first surface of the first fixed plate 24 in the form of phased array, the first surface of each digital plate 22 is fixed in the orthographic projection area of the corresponding antenna subarray 21 on the second surface of the first fixed plate 24, a predetermined number of transceiver components 23 form a group, and each group is arranged on the second surface of the corresponding digital plate 22. The predetermined number of transceiver components 23 in each group are arranged in an array on the second surface of the corresponding digital plate 22.

[0042] As shown in Figure 1 The first surface of the solar wing photovoltaic assembly 3 is arranged with power generation units, and the second surface of the solar wing photovoltaic assembly 3 is fixed to the reinforcing rib of the structural support frame 1.

[0043] Here, the solar wing photovoltaic assembly includes a plurality of power generation units and a second fixed plate, each power generation unit is fixed on the first surface of the second fixed plate, and the second surface of the second fixed plate is fixed to the reinforcing rib of the structural support frame 1.

[0044] For example, the power generation unit here is a photovoltaic cell that directly converts sunlight into electrical energy, and the type of photovoltaic cell can be polycrystalline silicon cell, monocrystalline silicon cell and thin-film solar cell, etc., which is not limited again.

[0045] For example, a three-junction gallium arsenide photovoltaic cell with an efficiency greater than 30% can be used to provide appropriate voltage and current parameters through series and parallel connection. Due to the size limitation of the photovoltaic cell area, a total of 132 pieces of cells are used in the form of 17 series and 14 parallel connection to form two subarrays to meet the power demand of the satellite communication integrated board.

[0046] Here, the power generation unit is connected to the main control board through the power supply interface and is controlled by the main control board to supply power to the entire satellite communication integrated board.

[0047] When the solar wing photovoltaic assembly collects solar energy, the solar energy is converted into electrical energy, which is divided into two parts, one part is stored in the battery unit, and the other part is controlled by the main control board to supply power to the entire satellite communication integrated board.

[0048] The second fixed plate is located on the second surface of the solar wing photovoltaic assembly and mainly plays the role of sealing, insulation, waterproofing and weather resistance, etc., to protect the power generation unit from environmental erosion. The second fixed plate material needs to have excellent high and low temperature resistance, ultraviolet radiation resistance, environmental aging resistance and electrical insulation performance, etc. Common backboard materials include TPT (Tedlar PET Tedlar, polyvinyl fluoride composite film), TPE (Thermoplastic Elastomer, thermoplastic elastomer), etc.

[0049] Here, the size of the second fixed plate is the same as the size of the first surface of the structural support frame 1.

[0050] The aluminum alloy frame is an external frame structure of the solar wing photovoltaic assembly, mainly plays a supporting, protecting and reinforcing role, has good mechanical strength and corrosion resistance, and can ensure stable operation of the solar wing photovoltaic assembly in a harsh environment.

[0051] As shown in Figure 1 The main control board 4 is fixed to the first fixed area 5 in the orthographic projection area of the second surface of the solar wing photovoltaic assembly 3, and the main control board 4 is connected with the plurality of transceiver assemblies 23.

[0052] Here, the main control board 4 is fixed to the second fixed plate of the solar wing photovoltaic assembly, and a plurality of mounting holes are arranged at the frame position of the main control board, and the main control board is fixed to the second fixed plate of the solar wing photovoltaic assembly through the first connecting piece passing through the mounting hole.

[0053] Each digital board 22 is connected with the main control board 4, so that the main control board 4 and the ground station are connected to convert digital signals and analog signals.

[0054] Here, the antenna subarray 21 is directed to the ground station, realizes the interaction of signals between the ground station and the communication satellite, and the plurality of antenna subassemblies in the phased array antenna assembly 2 adopts a tile structure layout, realizes the transmission and reception of radio frequency communication signals, and realizes the multi-region coverage application of the communication satellite to the ground.

[0055] Please refer to Figure 4 , Figure 4 The structure diagram of the satellite-borne communication integrated board provided by the embodiment of the application is provided. As shown in Figure 4 The satellite-borne communication integrated board provided by the embodiment of the application includes: a structure support frame 1, a phased array antenna assembly 2, a solar wing photovoltaic assembly 3, a main control board 4, a battery unit 7 and an attitude control board 8.

[0056] The inner surface of the structure support frame is provided with the main control board 4, the attitude control board 8, the battery unit 7 and a layer of heat radiation resistant coating film.

[0057] The minimum value of the thickness of the structure support frame is the sum of the thickness of the phased array antenna assembly 2, the thickness of the battery unit 7 and the thickness of the attitude control board 8.

[0058] The first fixed area 5 includes a first target area 51 and a second target area 52, and the first target area 51 is an orthographic projection area of the main control board 4 fixed to the second surface of the solar wing photovoltaic assembly 3.

[0059] The first side surface and the second side surface of the battery unit 7 are respectively provided with a preset number of mounting ears, and the inner surface of the reinforcing rib of the second target area 52 of the structural support frame 1 is provided with a preset number of support seats. The outer contour of the mounting ear and the inner contour of the support seat are matched to fix the battery unit to the second target area of the structural support frame.

[0060] For example, the preset number of mounting ears is two mounting ears on one side of the first side surface and the second side surface of the battery unit 7, and correspondingly, the first side surface and the second side surface of the inner surface of the reinforcing rib of the second target area 52 of the structural support frame 1 are also provided with two support seats on one side.

[0061] The battery unit 7 is connected to the main control board 4, and the main control board 4 controls the battery unit 7 to supply power to the satellite-borne communication integrated board.

[0062] The attitude control board 8 includes a circuit board and a plurality of magnetic torque devices, wherein each magnetic torque device is integrated on the first surface of the circuit board, and a plurality of fixing members are arranged at the frame of the second surface of the circuit board, so that the second connecting member fixes the attitude control board 8 on the reinforcing rib of the structural support frame 1 through the fixing members, so as to fix the attitude control board on the second target area of the structural support frame.

[0063] The plurality of magnetic torque devices include X-axis magnetic torque devices, Y-axis magnetic torque devices and Z-axis magnetic torque devices, and the three magnetic torque devices are integrated on the circuit board and generate torque by utilizing the interaction between the geomagnetic field and the magnetic rod, thereby realizing accurate control of the attitude of the spacecraft.

[0064] The magnetic torque devices in the attitude control board are connected to the main control board and receive the attitude control signals sent by the main control board. The main control board and the satellite main controller interact to control the attitude control board and the attitude control module on the communication satellite to realize the conversion of the attitude of the communication satellite. For example, the attitude of the satellite-borne communication integrated board can also be converted by controlling the magnetic torque devices through the main control board.

[0065] The satellite-borne communication integrated board further includes a thermal control unit, and the thermal control unit includes a heat dissipation material and a plurality of temperature sensors.

[0066] The heat dissipation material is applied to positions other than the antenna array surface of the first fixing plate of the phased array antenna assembly to achieve heat dissipation of the phased array antenna assembly.

[0067] For example, the heat dissipation material can be a thermal control coating, a multi-layer thermal insulation material, a heat-conducting grease and a heat-conducting pad, a thermistor and a heat insulation pad.

[0068] The thermal control coating is applied to positions other than the antenna array surface of the first fixing plate of the phased array antenna assembly, and can also be applied to the surfaces of part of the equipment and supports of the satellite-borne communication integrated board, the surfaces of part of the equipment and the inner wall plate of the satellite-borne communication integrated board, and the heat dissipation surface.

[0069] The multi-layer thermal insulation material is mainly used for coating the outer surface of the solar wing photovoltaic assembly, the thermal conductive grease and the thermal conductive pad are mainly used for thermal conductive fillers of part of the instrument mounting surface, and the thermal insulation pad is mainly used for thermal insulation between part of the external antenna and the space structure.

[0070] The temperature sensor can be a thermistor for temperature measurement of the instrument equipment.

[0071] The temperature sensor is installed at a preset position of the first fixing plate of the phased array antenna assembly 2 to detect the temperature of the first fixing plate and send the temperature to the main control board 4.

[0072] The temperature sensor is installed at a preset position of the second surface of the solar wing photovoltaic assembly 3 to detect the temperature of the second surface and send the temperature to the main control board 4.

[0073] The temperature sensor is installed at a preset position of the surface of the battery unit 7 to detect the temperature of the battery unit and send the temperature to the main control board 4.

[0074] The temperature sensor is installed at a preset position of the circuit board surface of the attitude control board 8 to detect the temperature of the circuit board and send the temperature to the main control board 4.

[0075] Specifically, the function of the energy line in the satellite communication integrated board is power supply, and the connection mode is as follows:

[0076] The power supply interface of the solar wing photovoltaic assembly is electrically connected with the power supply interface of the battery unit through the energy line to convert solar energy into electrical energy and store it in the battery unit.

[0077] The battery unit is connected with each device of the satellite communication integrated board to supply power for the devices.

[0078] The power supply interface of the battery unit is electrically connected with the power supply interface of the main control board through the energy line to supply power for the main control board; the power supply interface of the battery unit is electrically connected with the power supply interface of the attitude control board through the energy line to supply power for the attitude control board; the power supply interface of the battery unit is electrically connected with the power supply interface of the phased array antenna assembly through the energy line to supply power for the phased array antenna assembly; and the power supply interface of the battery unit is electrically connected with the power supply interface of the plurality of temperature sensors through the energy line to supply power for the plurality of temperature sensors.

[0079] Please refer to Figure 5 , Figure 5 The structure diagram of the phased array antenna assembly provided by the embodiment of the application is shown in the figure. Figure 5 As shown in the figure, the phased array antenna assembly provided by the embodiment of the application comprises an antenna subarray 21, a digital board 22 and a transceiver assembly 23.

[0080] The antenna subarray 21 is directed to the ground station, receives the signal of the ground station, and transmits the signal to the transceiver assembly 23 via the digital board 22, the transceiver assembly 23 is connected with the main control board 4, the main control board 4 is connected with the communication satellite main controller, and the signal is transmitted to the communication satellite main controller, the processed signal returned by the communication satellite main controller is transmitted to the transceiver assembly 23, and the transceiver assembly 23 transmits the processed signal to the ground station via the digital board 22 and the antenna subarray 21, so as to realize the transceiving of the signal between the ground station and the satellite.

[0081] Here, the transceiver assembly is a TR assembly (Transmitter and Receiver assembly), one antenna subassembly corresponds to one antenna subarray 21, one digital board 22 and a preset number of transceiver assemblies 23, for example, the preset number is 4.

[0082] Please refer to Figure 6 , Figure 6 The structure diagram of the working principle of the TR assembly in the phased array antenna assembly provided by the embodiment of the application is shown in the figure. Figure 6 As shown in the figure, the phased array antenna assembly provided by the embodiment of the application comprises a four-way power divider 61, a phase shifter 62, a filter 63, a radio frequency switch 64, a power amplifier 65 and a low noise amplifier 66.

[0083] Among them, the four-way power divider 61 is a power combiner in the TR assembly, mainly used for combining four input signals into one output signal, which can be used to realize the distribution and combination of multi-channel signals, and improve the flexibility and efficiency of the system.

[0084] The phase shifter 62 is used to adjust the phase of the signal to realize accurate control of the antenna beam, and by changing the phase difference of the signal on different antenna units, the scanning and pointing adjustment of the radar beam can be realized.

[0085] The filter 63 is used in the TR assembly to filter out unwanted frequency components and retain or enhance the required signals. In the transmitting mode, the filter 63 can ensure the spectral purity of the transmitted signal and reduce stray radiation; in the receiving mode, the filter 63 can suppress out-of-band interference and improve the signal-to-noise ratio of the received signal. The filter plays an important role in improving the anti-interference ability and signal quality of the radar system.

[0086] The power amplifier 65 (PA, Power Amplifier) is used to amplify the radio frequency signal in the transmitting mode to ensure that the antenna can emit radio waves with sufficient intensity.

[0087] The low noise amplifier 66 (LNA, Low Noise Amplifier) is used to amplify weak received signals in the receiving mode while minimizing the introduction of noise.

[0088] The radio frequency switch 64 is used for controlling the flow direction of the signal in the TR component, realizing the switching between the transmitting and receiving modes. When the radar is in the transmitting state, the radio frequency switch 64 guides the signal to the transmitting path; when the radar is in the receiving state, the radio frequency switch guides the signal to the receiving path, and the rapid switching capability of the radio frequency switch is crucial to the real-time performance and accuracy of the radar system.

[0089] Taking one path in a TR component as an example, the prior art needs a power amplifier 65 and a low noise amplifier 66 on both the signal receiving and transmitting paths, and 4 amplifiers are needed for signal transceiving, and the signal transceiving path of the application only needs 2 amplifiers, thereby saving devices, reducing wiring layout, and realizing the simultaneous transceiving of 16 signals, at the same time, the overall power consumption of the transceiving component is 102.4W, the power consumption is reduced, and the efficiency is higher.

[0090] Specifically, the input and output interface of the main control board is connected with the input and output interface of the circuit board of the attitude control board through a signal line, so as to send the attitude control signal to the circuit board, so as to adjust the attitude of the satellite-borne communication integrated board.

[0091] The input and output interface of the main control board is connected with the input and output interface of the circuit board of the attitude control board through a signal line, so as to send the attitude control signal to the circuit board, so as to adjust the attitude of the satellite-borne communication integrated board.

[0092] The input and output interface of the main control board is connected with the input and output interface of the solar wing photovoltaic component through a signal line, so as to determine whether the solar wing photovoltaic component is collecting solar energy by detecting the output voltage of the solar wing photovoltaic component.

[0093] The input and output interface of the main control board is connected with the input and output interface of the battery unit through a signal line, so as to control the battery unit to discharge and supply power to the satellite-borne communication integrated board when it is detected that the solar wing photovoltaic component is not collecting solar energy.

[0094] The input and output interface of the main control board is connected with the input and output interface of the plurality of temperature sensors through a signal line, so as to receive the temperature detected by the plurality of temperature sensors and send the temperature to the satellite main controller of the communication satellite body, so as to display on the communication satellite.

[0095] In a second aspect, the embodiments of the application provide a communication satellite, comprising:

[0096] A communication satellite body;

[0097] A satellite main controller arranged inside the communication satellite body;

[0098] The satellite-borne communication integrated board, and the main control board in the satellite-borne communication integrated board is connected with the satellite main controller to form information interaction.

[0099] The satellite-borne communication integrated board and the communication satellite provided by the embodiment of the application comprise a structural support frame, the structural support frame comprises a plurality of reinforcing ribs, and a first fixing area and a second fixing area are formed by the plurality of reinforcing ribs, the first fixing area is a hollow area, and a plurality of through holes are formed in the second fixing area by the reinforcing ribs; a phased array antenna assembly, an antenna array surface is arranged on a first surface of the phased array antenna assembly, and a second surface of the phased array antenna assembly is fixed to the reinforcing ribs of the structural support frame; a solar wing photovoltaic assembly, a power generation unit is arranged on a first surface of the solar wing photovoltaic assembly, and a second surface of the solar wing photovoltaic assembly is fixed to the reinforcing ribs of the structural support frame; and a main control board, the main control board is fixed to a normal projection area of the first fixing area on the second surface of the solar wing photovoltaic assembly, and the main control board is connected with a plurality of transceiver assemblies. The communication between the satellite and the ground station is realized, and the effects of reducing the volume and the weight are achieved.

[0100] The satellite-borne communication integrated board has the functions of power supply, load, attitude control, and thermal control, and can operate autonomously in an island mode, and is a modular component of a new generation of communication satellites.

[0101] For example, the outer dimensions of the satellite-borne communication integrated board can be 686 mm x 686 mm x 60.5 mm, the integrated structure is designed, and the total weight is 15 kg.

[0102] The satellite-borne communication integrated board has the functions of power supply, load, attitude control, and thermal control, and can operate autonomously in an island mode, and is a modular component of a new generation of communication satellites.

[0103] The main control board of the application provides power energy for each component of the satellite-borne communication integrated board and supports the required power energy for module operation; the application realizes information interaction between the module and the platform by information interaction between the main control board and the satellite main controller, has a communication function, and realizes information interaction between the module and the platform; the application has a reasonable layout installation, ensures that each device of the module meets the requirements of the carrying mechanical environment; the plurality of temperature sensors of the application have a temperature detection function, and ensure that each device of the module meets the working temperature environment requirements; the phased array antenna assembly of the application has a phased array load function and realizes information transmission between the satellite and the ground; and the magnetic torque device has an attitude control function and assists the satellite in adjusting the attitude after the satellite is launched into orbit.

[0104] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the system, device and unit described above can refer to the corresponding process in the foregoing method embodiments, which will not be described herein.

[0105] In several embodiments provided in the present application, it should be understood that the disclosed system, device and method can be implemented in other manners. The described device embodiments are merely illustrative, for example, the division of the units is only a logical function division, and there can be another division manner in actual implementation, for example, a plurality of units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed mutual couplings or direct couplings or communication connections between different units, or the among different units, can be indirect couplings or communication connections through some interfaces, devices or units, and can be in electrical, mechanical or other forms.

[0106] The units described as separated components can or can not be physically separated, and the components displayed as units can or can not be physical units, i.e., can be located in one place, or can be distributed on a plurality of network units. In actual implementation, some or all of the units can be selected according to actual needs to achieve the purposes of the embodiments of the present application.

[0107] In addition, each functional unit in the embodiments of the present application can be integrated in one processing unit, or each unit can exist physically as a separate unit, or two or more units can be integrated in one unit.

[0108] If the functions are implemented in the form of software function units and sold or used as independent products, they can be stored in a non-volatile computer readable storage medium executable by a processor. Based on this understanding, the technical solutions of the present application essentially or the part that contributes to the prior art or part of the technical solutions can be embodied in the form of a software product. The computer software product is stored in a storage medium, and includes a plurality of instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present application. The aforementioned storage medium includes: a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, and various other media that can store program codes.

[0109] Finally, it should be noted that the above-described embodiments are merely specific embodiments of the present application, which are used to illustrate the technical solutions of the present application, but not to limit the same. The protection scope of the present application is not limited thereto. Although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that any skilled person in the art can still modify or easily think of changes to the technical solutions recorded in the foregoing embodiments, or make equivalent replacements to some of the technical features, within the technical scope disclosed by the present application. The modifications, changes or replacements do not make the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A satellite-borne communication integrated board, characterized by, The application relates to a satellite communication integrated board. The satellite communication integrated board comprises a structural support frame, a phased array antenna assembly, a solar wing photovoltaic assembly, a main control board and a battery unit. The structural support frame comprises a plurality of reinforcing ribs, and a first fixing area and a second fixing area are formed by the reinforcing ribs, the first fixing area is a hollow area, and a plurality of through holes are formed in the second fixing area by the reinforcing ribs. The first surface of the phased array antenna assembly is provided with an antenna array, the antenna array is formed by a plurality of antenna subarrays arranged in a phased array form, the second surface of the phased array antenna assembly is fixed to the reinforcing ribs of the structural support frame, and a plurality of transceiver assemblies are arranged on the second surface of the phased array antenna assembly. The phased array antenna assembly comprises a first fixing plate and a plurality of antenna subassemblies, each antenna subassembly comprises an antenna subarray, a digital board and the predetermined number of transceiver assemblies, the plurality of antenna subarrays are fixed on the first surface of the first fixing plate in a phased array form, the first surface of each digital board is fixed in the orthographic projection area of the corresponding antenna subarray on the second surface of the first fixing plate, the predetermined number of transceiver assemblies are formed into a group, each group is arranged on the second surface of the corresponding digital board, and the predetermined number of transceiver assemblies in each group are arranged on the second surface of the corresponding digital board in an array form. The first surface of the solar wing photovoltaic assembly is provided with a power generation unit, and the second surface of the solar wing photovoltaic assembly is fixed to the reinforcing ribs of the structural support frame. The main control board is fixed to the orthographic projection area of the first fixing area on the second surface of the solar wing photovoltaic assembly, and the main control board is connected with the plurality of transceiver assemblies. The first fixing area comprises a first target area and a second target area, the first target area is the orthographic projection area of the main control board on the second surface of the solar wing photovoltaic assembly, and the satellite communication integrated board further comprises a battery unit.

2. The space-borne communications unitized panel of claim 1, wherein, The first side surface and the second side surface of the battery unit are respectively provided with a preset number of mounting ears, the inner surface of the reinforcing rib of the second target area of the structural support frame is provided with a preset number of support seats, and the outer contour of the mounting ear and the inner contour of the support seat are matched to fix the battery unit in the second target area of the structural support frame.

3. The space-borne communications unitized panel of claim 1, wherein, Each digital board is connected with the main control board, so that the main control board and a ground station are connected to convert digital signals and analog signals.

4. The space-borne communications unitized panel of claim 1, wherein, The solar wing photovoltaic assembly comprises a plurality of power generation units and a second fixing plate, each power generation unit is fixed on the first surface of the second fixing plate, and the second surface of the second fixing plate is fixed to the reinforcing ribs of the structural support frame. The satellite communication integrated board further comprises an attitude control board, the attitude control board comprises a circuit board and a plurality of magnetic torque devices. Each magnetic torque integrator is integrated on the first surface of the circuit board, and a plurality of fixing members are arranged at the frame of the second surface of the circuit board, so that the second connecting member fixes the attitude control board on the reinforcing rib of the structural support frame through the fixing members to fix the attitude control board on the second target area of the structural support frame.

5. The space-borne communications unitized panel of claim 4, wherein, The satellite-borne communication integrated board further comprises a thermal control unit, the thermal control unit comprising a heat dissipation material and a plurality of temperature sensors, The heat dissipation material is applied on the first fixing plate of the phased array antenna assembly except the antenna array surface to achieve heat dissipation of the phased array antenna assembly; The temperature sensors are installed at preset positions of the first fixing plate of the phased array antenna assembly to detect the temperature of the first fixing plate and send the temperature to the main control board; The temperature sensors are installed at preset positions of the second surface of the solar wing photovoltaic assembly to detect the temperature of the second surface and send the temperature to the main control board; The temperature sensors are installed at preset positions of the surface of the battery unit to detect the temperature of the battery unit and send the temperature to the main control board; The temperature sensors are installed at preset positions of the surface of the circuit board of the attitude control board to detect the temperature of the circuit board and send the temperature to the main control board.

6. The space-borne communications unitized panel of claim 5, wherein, The power supply interface of the solar wing photovoltaic assembly is electrically connected to the power supply interface of the battery unit through an energy line to convert solar energy into electrical energy and store the electrical energy in the battery unit; The power supply interface of the battery unit is electrically connected to the power supply interface of the main control board through an energy line to supply power to the main control board; The power supply interface of the battery unit is electrically connected to the power supply interface of the attitude control board through an energy line to supply power to the attitude control board; The power supply interface of the battery unit is electrically connected to the power supply interface of the phased array antenna assembly through an energy line to supply power to the phased array antenna assembly; The power supply interface of the battery unit is electrically connected to the power supply interface of the plurality of temperature sensors through an energy line to supply power to the plurality of temperature sensors.

7. The space-borne communications unitized panel of claim 6, wherein, The input / output interface of the main control board is connected to the input / output interface of the digital board of the phased array antenna assembly through a signal line to transmit / receive data between the antenna subarray and the ground station; The input / output interface of the main control board is connected to the input / output interface of the circuit board of the attitude control board through a signal line to send attitude control signals to the circuit board to adjust the attitude of the satellite-borne communication integrated board; The input / output interface of the main control board is connected to the input / output interface of the solar wing photovoltaic assembly through a signal line to determine whether the solar wing photovoltaic assembly is collecting solar energy by detecting the output voltage of the solar wing photovoltaic assembly; The input / output interface of the main control board is connected to the input / output interface of the battery unit through a signal line to control the battery unit to discharge to supply power to the satellite-borne communication integrated board when it is detected that the solar wing photovoltaic assembly is not collecting solar energy; The input and output interface of the master board is connected with the input and output interface of the plurality of temperature sensors through a signal line to receive the temperature detected by the plurality of temperature sensors and send the temperature to a satellite master controller of the communication satellite body to display on the communication satellite.

8. A communications satellite, characterized by Comprise: A communication satellite body; A satellite master controller arranged inside the communication satellite body; The master board in the on-board communication integrated board is connected with the satellite master controller to form information interaction.

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