Satellite-borne multi-channel frequency conversion device for on-orbit bidirectional multi-scene communication

Abstract

The application relates to a satellite-borne multi-channel frequency conversion device for on-orbit bidirectional multi-scene communication. The device comprises a control unit, a local oscillator unit, a same-source clock distribution module, a first frequency synthesizer, a second frequency synthesizer and a radio frequency switch module. The same-source clock provides a reference clock for each frequency synthesizer. The radio frequency switch module switches the first frequency synthesizer output link according to the working mode, so that the synthesizer is time-multiplexed. The local oscillator provides the local oscillator for the full link in mode one and provides the local oscillator for the first frequency conversion in mode two. The second frequency synthesizer provides the local oscillator for the second frequency conversion in mode two. The frequency conversion unit comprises a multi-path frequency conversion module, which switches the frequency conversion architecture according to the instruction. The low-frequency radio channel unit comprises corresponding radio frequency transceiver modules, which complete intermediate frequency preprocessing and post-processing and return the link detection results. The device can consider dual-mode communication and multi-channel transmission, and realizes miniaturization and low-power consumption optimization.

Description

Technical Field

[0001] This application relates to the field of satellite communication technology, and in particular to a spaceborne multi-channel frequency conversion device for on-orbit two-way multi-scenario communication. Background Technology

[0002] With the rapid development of satellite communication technology, the construction of the integrated air-space-ground communication system continues to accelerate. In order to cope with the industry's current situation where the communication capacity of low-frequency bands is gradually becoming saturated, the shift of communication frequencies to the Q / V high-frequency band has become the mainstream development direction of the industry. With its wider available bandwidth and higher transmission rate, the Q / V band is the core carrier for high-throughput satellites to achieve two types of on-orbit two-way communication. As the core component in satellite communication transponders that realizes signal frequency band conversion, the performance, power consumption and integration of the onboard frequency converter directly determine the overall operation effect of the satellite communication system.

[0003] Currently, traditional designs for spaceborne multi-channel frequency converters often employ a single-band fixed-link architecture. This involves designing independent frequency converter links and local oscillator supply circuits for different bidirectional communication scenarios in orbit, using multiple independent frequency synthesizer chips to provide local oscillator signals to each frequency converter channel, thus meeting the frequency band conversion requirements of multi-channel parallel communication. However, traditional spaceborne frequency converter designs generally suffer from low overall architecture integration. Multiple independent structural components and local oscillator circuits result in a large overall size and weight, making it unsuitable for the stringent miniaturization requirements of spaceborne equipment. Simultaneous operation of multiple frequency synthesizer chips also leads to excessive power consumption, significantly increasing the power supply pressure on the satellite bus and the burden on the temperature control system. Furthermore, the fixed-link architecture cannot flexibly adapt to multi-scenario communication needs, has poor future scalability, and is prone to local oscillator signal crosstalk and insufficient broadband link flatness when multiple channels operate simultaneously, making it difficult to guarantee the stability and reliability of high-frequency communication. Summary of the Invention

[0004] Therefore, it is necessary to provide a spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication to address the aforementioned technical problems.

[0005] A spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication, the device comprising: Control unit, local oscillator unit, frequency converter unit, low-frequency radio frequency channel unit; The control unit is used to receive the working mode switching command sent by the space service system. The working modes include spaceborne Q / V band communication mode one and spaceborne V band communication mode two, and mode one and mode two are time-division and mutually exclusive. The local oscillator unit is connected to the control unit and the frequency conversion unit, and includes a common clock distribution module, at least two frequency synthesizers, and an RF switch module. The common clock distribution module provides a common reference clock for each frequency synthesizer. The at least two frequency synthesizers include a first frequency synthesizer and a second frequency synthesizer. The output terminal of the first frequency synthesizer is connected to the input terminal of the RF switch module. The control terminal of the RF switch module is connected to the control unit and is used to switch the output link of the first frequency synthesizer according to the working mode switching command, so that the first frequency synthesizer can be time-division multiplexed between mode one and mode two. When mode one is working, the first frequency synthesizer provides a local oscillator signal for the entire link of mode one. When mode two is working, the first frequency synthesizer provides a local oscillator signal for the first frequency conversion of mode two, and the second frequency synthesizer provides a local oscillator signal for the second frequency conversion of mode two. The frequency conversion unit is connected to the local oscillator unit and the low-frequency radio frequency channel unit respectively, and includes multiple frequency conversion modules corresponding to the low-frequency radio frequency channel unit, which are used to match the corresponding frequency conversion architecture according to the working mode switching command to complete the signal frequency band conversion. The low-frequency radio frequency channel unit is connected to the control unit and the frequency conversion unit respectively, and includes multiple radio frequency transceiver modules corresponding one-to-one with the frequency conversion module, used for preprocessing and post-processing of intermediate frequency signals, and transmitting the link signal detection results back to the control unit.

[0006] The aforementioned spaceborne multi-channel frequency converter for on-orbit bidirectional multi-scenario communication, by setting up a time-division multiplexing (TDM) mutually exclusive working architecture adapted to both spaceborne Q / V band communication mode 1 and spaceborne V band communication mode 2, can be compatible with both communication scenarios within a single device, avoiding redundant settings of multiple independent frequency converters. By providing a common reference clock to multiple frequency synthesizers through a common clock distribution module, the synchronization and consistency of the local oscillator signal in both modes can be guaranteed, avoiding communication performance loss caused by frequency deviation. By switching the output link of the first frequency synthesizer through an RF switch module, a single frequency synthesizer can be time-division multiplexed across both modes, significantly reducing the number of core frequency synthesizer components and effectively reducing device power consumption and hardware size. Through multiple one-to-one corresponding frequency converter modules and RF transceiver modules, it can adapt to the requirements of multi-channel parallel communication, while simultaneously achieving closed-loop feedback control of link status. This embodiment of the invention can achieve miniaturization and low-power optimization of the spaceborne frequency converter while simultaneously considering the dual-mode communication and multi-channel transmission capabilities of spaceborne Q / V band communication mode 1 and spaceborne V band communication mode 2. Attached Figure Description

[0007] Figure 1 This is a schematic diagram of the structure of a spaceborne multi-channel frequency converter for on-orbit bidirectional multi-scenario communication in one embodiment. Figure 2This is a schematic diagram of the local oscillator unit in one embodiment; Figure 3 This is a schematic diagram of the structure of a mode-one frequency converter unit in one embodiment; Figure 4 This is a schematic diagram of the structure of the Mode 2 frequency converter unit in one embodiment. Detailed Implementation

[0008] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0009] In one embodiment, such as Figure 1 As shown, a spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication is provided, comprising: Control unit, local oscillator unit, frequency converter unit, low-frequency radio frequency channel unit; The control unit is used to receive the working mode switching command sent by the space service system. The working modes include spaceborne Q / V band communication mode 1 and spaceborne V band communication mode 2, and mode 1 and mode 2 are time-division and mutually exclusive. The local oscillator unit is connected to the control unit and the frequency conversion unit, and includes a common clock distribution module, at least two frequency synthesizers, and an RF switch module. The common clock distribution module provides a common reference clock for each frequency synthesizer. The at least two frequency synthesizers include a first frequency synthesizer and a second frequency synthesizer. The output terminal of the first frequency synthesizer is connected to the input terminal of the RF switch module. The control terminal of the RF switch module is connected to the control unit and is used to switch the output link of the first frequency synthesizer according to the working mode switching command, so that the first frequency synthesizer can be time-division multiplexed between mode one and mode two. When mode one is working, the first frequency synthesizer provides the local oscillator signal for the entire link of mode one. When mode two is working, the first frequency synthesizer provides the local oscillator signal for the first frequency conversion of mode two, and the second frequency synthesizer provides the local oscillator signal for the second frequency conversion of mode two. The frequency conversion unit is connected to the local oscillator unit and the low-frequency radio frequency channel unit respectively. It includes multiple frequency conversion modules that correspond one-to-one with the low-frequency radio frequency channel unit. It is used to match the corresponding frequency conversion architecture according to the working mode switching command to complete the signal frequency band conversion. The low-frequency radio frequency channel unit is connected to the control unit and the frequency conversion unit respectively. It includes multiple radio frequency transceiver modules that correspond one-to-one with the frequency conversion module. These modules are used for the preprocessing and post-processing of intermediate frequency signals and to transmit the link signal detection results back to the control unit.

[0010] In the aforementioned spaceborne multi-channel frequency converter for on-orbit bidirectional multi-scenario communication, a time-division multiplexing architecture adapted to both spaceborne Q / V band communication mode 1 and spaceborne V band communication mode 2 is adopted. This allows for compatibility with both communication scenarios within a single device, avoiding redundant setups of multiple independent frequency converters. A common-source clock allocation module provides a common-source reference clock for multiple frequency synthesizers, ensuring the synchronization and consistency of the local oscillator signal in both modes and mitigating communication performance loss due to frequency deviation. A radio frequency switch module switches the output link of the first frequency synthesizer, enabling time-division multiplexing of a single frequency synthesizer across both modes. This significantly reduces the number of core frequency synthesizer components, effectively lowering device power consumption and hardware size. Multiple one-to-one corresponding frequency converter modules and radio frequency transceiver modules adapt to multi-channel parallel communication requirements while achieving closed-loop feedback control of link status. This embodiment of the invention achieves miniaturization and low-power optimization of the spaceborne frequency converter while simultaneously considering both spaceborne Q / V band communication mode 1 and spaceborne V band communication mode 2 dual-mode communication and multi-channel transmission capabilities.

[0011] In one embodiment, the frequency conversion module of the frequency conversion unit uses a single-frequency conversion architecture to complete the signal frequency band conversion when operating in mode one, and uses a double-frequency conversion architecture to complete the signal frequency band conversion when operating in mode two.

[0012] In this embodiment, by configuring a single-conversion architecture for the first mode of spaceborne Q / V band communication and a double-conversion architecture for the second mode of spaceborne V band communication, the spurious suppression capability of high-frequency band communication can be improved while simplifying the corresponding frequency band link structure and reducing hardware space occupation. This ensures the signal transmission performance in dual-mode communication scenarios and adapts to the differentiated design requirements of different communication links.

[0013] In one embodiment, the operating frequency band of Mode 1 is the Q / V band communication sub-band; the operating frequency band of Mode 2 is the V band high frequency band.

[0014] In this embodiment, by matching the Q / V band communication sub-band to the first satellite Q / V band communication mode and matching the V band high frequency band to the second satellite V band communication mode, it is possible to adapt to the development needs of high-speed transmission in high frequency bands of satellite communication, break through the limitation of low frequency band communication capacity saturation, and at the same time, by dividing the frequency bands according to the scenario, frequency band interference between the two modes can be avoided, ensuring the stability of dual-mode communication.

[0015] In one embodiment, when the first frequency synthesizer operates in mode one, it outputs a first local oscillator signal to provide a unified local oscillator reference for the up-conversion and down-conversion stages of the entire link in mode one; when the first frequency synthesizer operates in mode two, it outputs a second local oscillator signal to provide a local oscillator reference for the first frequency conversion in mode two; when the second frequency synthesizer operates in mode two, it outputs a third local oscillator signal to provide a local oscillator reference for the second frequency conversion in mode two.

[0016] In this embodiment, the first frequency synthesizer provides a unified local oscillator reference for the full-link up and down conversion of Mode 1 and a local oscillator reference for the first frequency conversion of Mode 2. The second frequency synthesizer provides a local oscillator reference for the second frequency conversion of Mode 2. This enables precise matching of local oscillator signals in different scenarios, ensuring frequency synchronization and consistency in the dual-mode frequency conversion process. At the same time, by using a single frequency synthesizer for multiple scenarios, the number of core frequency synthesizer components is reduced, effectively reducing the hardware cost, power consumption and size of the device.

[0017] In one embodiment, within the frequency conversion unit, corresponding to the frequency conversion module of Mode 1, the upper frequency conversion link and the lower frequency conversion link have symmetrical architectures; the upper frequency conversion link along the direction of transmitting the signal and the lower frequency conversion link along the direction of receiving the signal both include a first main signal link and a first local oscillator branch; the first main signal link is provided with a mixer and a second amplifier in sequence; the first local oscillator branch is provided with a first amplifier, a filter and a frequency multiplier in sequence, and the output terminal of the first local oscillator branch is connected to the local oscillator input terminal of the mixer; the frequency multiplier of the upper frequency conversion link is a triple frequency multiplier, and the frequency multiplier of the lower frequency conversion link is a quadruple frequency multiplier.

[0018] In this embodiment, the up-conversion links of the frequency conversion module in mode one adopt a completely symmetrical architecture design, which can reduce the design complexity and debugging difficulty of the frequency conversion links, improve the maintainability and scalability of the device, and at the same time, through the differentiated frequency multiplier configuration of the up-conversion links, it can accurately adapt to the up-conversion requirements of the satellite Q / V band communication mode one, and ensure the signal mixing accuracy and performance consistency of the transceiver links.

[0019] In one embodiment, within the frequency conversion unit corresponding to mode two, the upper frequency conversion link and the lower frequency conversion link have symmetrical architectures. The upper frequency conversion link along the direction of transmitting the signal and the lower frequency conversion link along the direction of receiving the signal both include a second main signal link, a second local oscillator branch, and a third local oscillator branch. The second main signal link is provided with a first mixer, an intermediate frequency filter, a second mixer, and an output amplifier in sequence. The second local oscillator branch is provided with a filter and a second frequency multiplier in sequence, and the output terminal of the second local oscillator branch is connected to the local oscillator input terminal of the second mixer. The third local oscillator branch is provided with a filter, a first frequency multiplier, and an amplifier in sequence, and the output terminal of the third local oscillator branch is connected to the local oscillator input terminal of the second mixer.

[0020] In this embodiment, the up-conversion and down-conversion links of the frequency conversion module adopt a completely symmetrical architecture design through mode two, which can adapt to the standardized design requirements of the secondary frequency conversion architecture of spaceborne V-band communication, reduce link design redundancy and ensure the signal transmission quality of high-speed communication in spaceborne V-band communication.

[0021] In one embodiment, the RF transceiver module of the low-frequency RF channel unit is provided with a filter, a low-power amplifier, a discrete equalizer, an analog control attenuator, and a detector in sequence along the signal transmission direction; the detector is used to detect the link signal strength, and the control unit realizes automatic gain closed-loop control of the link based on the returned detection results.

[0022] In this embodiment, by sequentially setting a filter, a low-power amplifier, a discrete equalizer, an analog control attenuator, and a detector along the signal transmission direction within the RF transceiver module, the intermediate frequency signal can be optimized across the entire link. This effectively suppresses spurious signals, compensates for link flatness, and achieves precise power regulation. Simultaneously, by detecting the link signal strength and transmitting the results back through the detector, automatic gain closed-loop control of the link is achieved, ensuring the stability and purity of the intermediate frequency signal under different operating modes and improving the anti-interference capability of the communication link.

[0023] In one embodiment, the low-frequency radio frequency channel unit is provided with multiple independent radio frequency transceiver modules, corresponding to multiple upconversion channels and multiple downconversion channels. Each radio frequency transceiver module is matched with a corresponding working link according to its working mode. Each radio frequency transceiver module is independently turned on and off and its parameters are configured through a control unit.

[0024] In this embodiment, multiple independent radio frequency transceiver modules are set up through the low-frequency radio frequency channel unit, corresponding to multiple up-conversion and down-conversion channels. This can adapt to the usage requirements of multi-channel parallel communication. At the same time, through the working mode link matching, independent start-up and shutdown, and parameter configuration of each radio frequency transceiver module, it can flexibly adapt to the differentiated channel requirements of spaceborne Q / V band communication mode one and spaceborne V band communication mode two, improve the scenario adaptability and scalability of the device, realize the fine control of each communication link, and avoid signal crosstalk between multiple channels.

[0025] In one embodiment, the local oscillator unit is further provided with a multi-channel power divider module. After the local oscillator signal output by the first frequency synthesizer is switched by the radio frequency switch module, it is distributed to the multi-channel frequency conversion module in the corresponding mode through the corresponding multi-channel power divider module, supporting flexible expansion of the number of frequency conversion channels.

[0026] In this embodiment, by setting up a multi-channel power divider module within the local oscillator unit, the local oscillator signal output from the first frequency synthesizer after the RF switch module is switched is distributed to multiple channels. This can provide synchronous local oscillator signals for multiple frequency conversion modules in the corresponding mode, ensuring the consistency of local oscillator frequencies in multi-channel communication links. At the same time, the number of frequency conversion channels can be flexibly expanded without adding a frequency synthesizer, further reducing the hardware cost, power consumption, and size of the device for expansion and upgrade, and adapting to the upgrade requirements of multi-channel parallel transmission.

[0027] In one embodiment, the control unit also integrates power management functions and is electrically connected to the local oscillator unit, frequency converter unit, and low-frequency radio frequency channel unit to allocate operating power to each unit and can independently turn on or off the power supply of any radio frequency transceiver module and the corresponding frequency converter module.

[0028] In this embodiment, by integrating power management functions into the control unit, working power is allocated to the local oscillator unit, frequency conversion unit, and low-frequency radio frequency channel unit. This enables centralized control of the device's power supply, improving power supply reliability in spaceborne scenarios. Simultaneously, by independently controlling the power supply on / off of any radio frequency transceiver module and its corresponding frequency conversion module, the corresponding power supply can be shut off when a single communication link is idle, further reducing the overall operating power consumption of the device and deeply adapting to the low-power and miniaturized design requirements of spaceborne equipment.

[0029] Depend on Figure 1As can be seen, the device of the present invention includes a control unit, a local oscillator unit, a low-frequency radio frequency channel unit, and a frequency conversion unit. Taking a six-channel frequency conversion link as an example, it is described with two working modes. Each working mode supports subsequent multi-channel expansion to further improve transmission efficiency. The two modes operate in a time-sharing manner. The first mode of spaceborne Q / V band communication adopts a single-conversion architecture. In one case, its operating frequency band can be, for example, an up-conversion frequency of 42.65 GHz and a down-conversion frequency of 55.4 GHz; in another case, its operating frequency band can be, for example, an up-conversion frequency of 37.75 GHz and a down-conversion frequency of 49.75 GHz. The second mode is the second mode of spaceborne V band communication, which adopts a double-conversion architecture. Its operating frequency band is the high-frequency band of the V band. In one case, its operating frequency band can be, for example, an up-conversion frequency of 69.5 GHz and a down-conversion frequency of 74.4 GHz; in another case, its operating frequency band can be, for example, an up-conversion frequency of 65.55 GHz and a down-conversion frequency of 69.25 GHz. Mode 1 is tentatively set as two channels, representing a single frequency conversion; Mode 2 is tentatively set as one channel, representing a double frequency conversion, corresponding to the aforementioned six frequency conversion links. The frequency conversion unit is currently divided into six frequency conversion modules, with additional modules to be added later as needed to improve product maintainability and reusability. The low-frequency radio frequency channel unit is a single module, subdivided into six radio frequency transceiver modules, with additional modules to be added later as needed, corresponding to the frequency conversion modules of the aforementioned frequency conversion unit. Each radio frequency transceiver module is independently controlled through the satellite system (the control unit is linked to the satellite system). The control unit interfaces with the satellite system to receive and send commands. The low-frequency radio frequency channel unit is used for flatness equalization, power control, received signal detection, intermediate frequency signal amplification, and filtering. The low-frequency radio frequency (RF) channel unit includes six RF transceiver modules, which complete the amplification and filtering of the low-frequency link. These six RF transceiver modules correspond to three up-conversion and three down-conversion channels. The up-conversion channels consist of a first-stage filter, a first-stage amplifier, an equalizer, an analog control attenuator, a second-stage amplifier, and a detector. The down-conversion channels are the reverse of the up-conversion channels. The first-stage filter serves as the input filter to suppress spurious signals before mixing, ensuring signal purity. Both amplifier stages use low-power amplifiers to amplify the low-frequency signal. The equalizer is a discrete equalization link used to compensate for link flatness and ensure signal quality. The detector detects the signal strength and transmits it back to the satellite computer for AGC control.

[0030] In one specific embodiment, such as Figure 2The diagram illustrates the structure of a local oscillator unit. The reference clock signal input passes through amplifier 1 and power divider 1, then supplies clock signals to two frequency synthesizer chips. The first frequency synthesizer (frequency synthesizer 1) divides the output local oscillator into mode one or mode two via RF switch 1, each followed by a filter. Power divider 2 is a four-way power divider, providing local oscillators for two mode one up-conversions and two mode one down-conversions. In mode one operation, the first local oscillator signal output from the first frequency synthesizer can have a frequency of 13.15 GHz. In the low-frequency scenario of the spaceborne Q / V band communication mode one, the local oscillator driver is connected in series with a tripler, resulting in an up-conversion intermediate frequency of 3.2 GHz and a mixing frequency of 13.15 GHz. 3 + 3.2 = 42.65 GHz; In mode one, the downconverter module drives a quadruple frequency multiplier in series, the downconversion intermediate frequency is 2.8 GHz, and the mixing frequency is 55.4-13.15 GHz. 4 = 2.8GHz; a multi-channel power divider will be selected later to meet the local oscillator requirements of multiple Mode 1 channels. Mode 2 high-frequency scenarios involve two frequency conversions. The first frequency synthesizer outputs a frequency of 14.45GHz, providing a primary local oscillator for the Mode 2 up-conversion and down-conversion modules. The second frequency synthesizer (Frequency Synthesizer 2) outputs a frequency of 4.8GHz, providing a secondary local oscillator for the Mode 2 up-conversion and down-conversion modules. The first local oscillator of the up-conversion module is driven by a fourth frequency multiplier, resulting in an up-conversion intermediate frequency of 2.1GHz and a mixing frequency of 14.45GHz. 4+4.8 2 + 2.1 = 69.5 GHz; The first local oscillator driver of the downconverter module is connected in series with a frequency multiplier of four, and the second local oscillator driver is connected in series with a frequency multiplier of three. The downconverter output intermediate frequency is 2.2 GHz, and the mixing frequency is 74.4-14.45 GHz. 4-4.8 3 = 2.2GHz. Later, a multi-channel power divider was selected to meet the local oscillator requirements for multiple modes (mode 1 and mode 2). The first frequency synthesizer multiplexes the up-conversion and down-conversion local oscillators for both modes 1 and 2, operating in a time-sharing manner to eliminate spurious crosstalk. The second frequency synthesizer multiplexes the up-conversion and down-conversion local oscillators for mode 2, and its output local oscillator frequency differs significantly from that of the first frequency synthesizer, facilitating local oscillator filtering. The fewer frequency synthesizers significantly reduce size and power consumption.

[0031] In another alternative embodiment, the output frequencies of the two frequency synthesizers, the frequency multiplier configuration of the local oscillator path, and the corresponding intermediate frequency operating frequency can be adjusted according to the actual on-orbit application frequency requirements of spaceborne Q / V band communication mode one and spaceborne V band communication mode two, to adapt to the different frequency band planning requirements of dual-mode communication of spaceborne Q / V band communication mode one and spaceborne V band communication mode two. Specifically, when operating in mode one, the first local oscillator signal frequency output by the first frequency synthesizer can be 11.85 GHz. In the low-frequency scenario of mode one, the local oscillator driver of the upconversion module is connected in series with a third frequency multiplier, the upconversion intermediate frequency is 2.2 GHz, and the mixing frequency is 11.85 GHz. 3 + 2.2 = 37.75 GHz; In mode one, the local oscillator driver of the downconversion module is connected in series with a quadruple frequency multiplier, the intermediate frequency of the downconversion is 2.35 GHz, and the mixing frequency is 49.75-11.85 GHz. 4 = 2.35GHz; a multi-channel power divider will be selected later to meet the local oscillator requirements of multiple Mode 1 channels. Mode 2 high-frequency scenario involves two frequency conversions. The first frequency synthesizer outputs a frequency of 13.95GHz, providing a primary local oscillator for the Mode 2 up-conversion and down-conversion modules. The second frequency synthesizer (Frequency Synthesizer 2) outputs a frequency of 3.75GHz, providing a secondary local oscillator for the Mode 2 up-conversion and down-conversion modules. The first local oscillator of the up-conversion module is driven by a fourth frequency multiplier, and the second local oscillator is driven by a second frequency multiplier. The up-conversion intermediate frequency is 2.25GHz, and the mixing frequency is 2.25 + 3.75GHz. 2+13.95 4 = 65.55GHz; the downconverter module's first local oscillator driver is connected in series with a fourth frequency multiplier, and the second local oscillator driver is connected in series with a third frequency multiplier. The downconverter output intermediate frequency is 2.2GHz, and the mixing frequency is 69.25-13.95GHz. 4-3.75 3 = 2.2GHz. The number of power dividers can be selected according to channel expansion needs to meet the local oscillator supply requirements of the multi-channel dual-channel mode.

[0032] like Figure 3 The diagram illustrates the structure of a mode-one frequency converter unit. The mode-one frequency converter module in the frequency converter unit has a completely symmetrical upper and lower frequency conversion architecture. Both the upper and lower frequency conversion links include a first main signal link and a first local oscillator branch. The first local oscillator branch sequentially includes a first amplifier (amplifier 1), a filter (filter 1), and a frequency multiplier (frequency multiplier 1). The first main signal link sequentially includes a mixer (mixer 1) and a second amplifier (amplifier 2). Amplifier 1 amplifies the input local oscillator signal to ensure the local oscillator signal power meets the mixer's operating drive power. Filter 1 filters the amplified local oscillator signal to ensure the purity of the input mixer signal. Frequency multiplier 1 multiplies the filtered local oscillator signal. The frequency multiplier can be configured as a triple or quadruple frequency multiplier according to the requirements of the upper and lower frequency conversion links to adapt to the corresponding frequency band conversion requirements. Mixer 1 mixes the input low-frequency signal with the multiplied local oscillator signal and outputs the frequency-converted RF signal. Amplifier 2 amplifies and outputs the mixed signal.

[0033] like Figure 4The diagram illustrates the structure of a Mode 2 frequency converter unit. The Mode 2 frequency converter module in the unit has a completely symmetrical upper and lower frequency conversion architecture. Both the upper and lower frequency conversion links include a second main signal link, a second local oscillator branch, and a third local oscillator branch. The second main signal link sequentially includes a first mixer (mixer 1), an intermediate frequency filter (filter 2), a second mixer (mixer 2), and an output amplifier (amplifier 2). The second local oscillator branch sequentially includes a filter (filter 3) and a second frequency multiplier (frequency multiplier 2). The third local oscillator branch sequentially includes a filter (filter 1), a first frequency multiplier (frequency multiplier 1), and an amplifier (amplifier 1). Taking the upper frequency conversion link as an example, in the second local oscillator branch, i.e., the third local oscillator branch, filter 1 filters the input second local oscillator signal to ensure the purity of the input mixer signal, frequency multiplier 1 multiplies the second local oscillator signal, and amplifier 1 multiplies the frequency of the second local oscillator signal. The secondary local oscillator signal after frequency reduction is amplified to ensure that the power of the local oscillator signal meets the driving power of the mixer. The amplified secondary local oscillator signal is then connected to the local oscillator input terminal of mixer 2. In the primary local oscillator branch, i.e. the second local oscillator branch, filter 3 filters the input primary local oscillator signal, and frequency multiplier 2 multiplies the filtered primary local oscillator signal. The multiplied primary local oscillator signal is then connected to the local oscillator input terminal of mixer 1. In the second main signal link, mixer 1 mixes the input low-frequency signal with the multiplied primary local oscillator signal to output a KU band signal. Filter 2 filters the KU band signal, and mixer 2 mixes the KU band signal with the amplified secondary local oscillator signal to output a V band signal. Amplifier 2 amplifies and outputs the V band signal.

[0034] It is understood that this invention, through a differentiated frequency conversion architecture design adapted to different communication scenarios, adopts a single-frequency conversion architecture for the first satellite Q / V band communication mode, simplifying the link structure and reducing the link space occupied. For the second satellite V band communication mode, a double-frequency conversion architecture is adopted to improve spurious emission suppression capability and ensure link transmission performance. At the same time, relying on the highly integrated design of a single device integrating multiple transceiver links, it can adapt to the complex multi-channel communication scenarios of the first and second satellite Q / V band communication modes, significantly reducing the size and weight of satellite equipment. The reusable frequency conversion architecture greatly reduces the number of frequency synthesizer chips required, which can significantly reduce the power consumption of the device. This not only alleviates the power supply pressure on the satellite bus, but the low heat dissipation resulting from low power consumption can also greatly reduce the impact on the satellite temperature control system, fully meeting the core design requirements of miniaturization and low power consumption of satellite equipment.

[0035] The modules in the aforementioned spaceborne multi-channel frequency converter for on-orbit two-way multi-scenario communication can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the corresponding operations of each module.

[0036] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0037] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A spaceborne multi-channel frequency converter for on-orbit bidirectional multi-scenario communication, characterized in that, The device includes a control unit, a local oscillator unit, a frequency conversion unit, and a low-frequency radio frequency channel unit; The control unit is used to receive the working mode switching command sent by the space service system. The working modes include spaceborne Q / V band communication mode one and spaceborne V band communication mode two, and mode one and mode two are time-division and mutually exclusive. The local oscillator unit is connected to the control unit and the frequency conversion unit, and includes a common clock distribution module, at least two frequency synthesizers, and an RF switch module. The common clock distribution module provides a common reference clock for each frequency synthesizer. The at least two frequency synthesizers include a first frequency synthesizer and a second frequency synthesizer. The output terminal of the first frequency synthesizer is connected to the input terminal of the RF switch module. The control terminal of the RF switch module is connected to the control unit and is used to switch the output link of the first frequency synthesizer according to the working mode switching command, so that the first frequency synthesizer can be time-division multiplexed between mode one and mode two. When mode one is working, the first frequency synthesizer provides a local oscillator signal for the entire link of mode one. When mode two is working, the first frequency synthesizer provides a local oscillator signal for the first frequency conversion of mode two, and the second frequency synthesizer provides a local oscillator signal for the second frequency conversion of mode two. The frequency conversion unit is connected to the local oscillator unit and the low-frequency radio frequency channel unit respectively, and includes multiple frequency conversion modules corresponding to the low-frequency radio frequency channel unit, which are used to match the corresponding frequency conversion architecture according to the working mode switching command to complete the signal frequency band conversion. The low-frequency radio frequency channel unit is connected to the control unit and the frequency conversion unit respectively, and includes multiple radio frequency transceiver modules corresponding one-to-one with the frequency conversion module, used for preprocessing and post-processing of intermediate frequency signals, and transmitting the link signal detection results back to the control unit; The frequency conversion module of the frequency conversion unit uses a single-frequency conversion architecture to complete the signal frequency band conversion when operating in mode one, and a double-frequency conversion architecture to complete the signal frequency band conversion when operating in mode two.

2. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, The operating frequency band of Mode 1 is the Q / V band communication sub-band; the operating frequency band of Mode 2 is the V band high frequency band.

3. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, When the first frequency synthesizer operates in mode one, it outputs the first local oscillator signal, providing a unified local oscillator reference for the up-conversion and down-conversion links of the entire mode one link; When the first frequency synthesizer operates in mode two, it outputs the second local oscillator signal to provide a local oscillator reference for the first frequency conversion in mode two. When the second frequency synthesizer operates in mode two, it outputs a third local oscillator signal to provide a local oscillator reference for the secondary frequency conversion in mode two.

4. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, In the frequency conversion unit, within the frequency conversion module corresponding to mode one, the upper frequency conversion link and the lower frequency conversion link architecture are symmetrical. The upconversion link along the direction of transmitting the signal and the downconversion link along the direction of receiving the signal both include a first main signal link and a first local oscillator branch. The first main signal link is provided with a mixer and a second amplifier in sequence. The first local oscillator branch is provided with a first amplifier, a filter and a frequency multiplier in sequence. The output terminal of the first local oscillator branch is connected to the local oscillator input terminal of the mixer. The frequency multiplier of the upconversion link is a triple frequency multiplier and the frequency multiplier of the downconversion link is a quadruple frequency multiplier.

5. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, In the frequency conversion unit, within the frequency conversion module corresponding to mode two, the upper frequency conversion link and the lower frequency conversion link architecture are symmetrical. The upconversion link along the direction of transmitted signal transmission and the downconversion link along the direction of received signal transmission both include a second main signal link, a second local oscillator branch, and a third local oscillator branch. The second main signal link is provided with a first mixer, an intermediate frequency filter, a second mixer, and an output amplifier in sequence. The second local oscillator branch is provided with a filter and a second frequency multiplier in sequence, and the output terminal of the second local oscillator branch is connected to the local oscillator input terminal of the first mixer. The third local oscillator branch is provided with a filter, a first frequency multiplier, and an amplifier in sequence, and the output terminal of the third local oscillator branch is connected to the local oscillator input terminal of the second mixer.

6. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, The low-frequency radio frequency channel unit's radio frequency transceiver module is provided with a filter, a low-power amplifier, a discrete equalizer, an analog control attenuator, and a detector in sequence along the signal transmission direction. The detector is used to detect the link signal strength, and the control unit implements automatic gain closed-loop control of the link based on the returned detection results.

7. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 6, characterized in that, The low-frequency radio frequency channel unit is equipped with multiple independent radio frequency transceiver modules, corresponding to multiple up-conversion channels and multiple down-conversion channels. Each radio frequency transceiver module is matched with a corresponding working link according to its working mode. Each radio frequency transceiver module can be independently turned on and off and its parameters can be configured through the control unit.

8. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, The local oscillator unit is also equipped with a multi-channel power divider module. After the local oscillator signal output by the first frequency synthesizer is switched by the radio frequency switch module, it is distributed to the multi-channel frequency conversion module in the corresponding mode through the corresponding multi-channel power divider module, supporting flexible expansion of the number of frequency conversion channels.

9. The spaceborne multi-channel frequency conversion device for on-orbit bidirectional multi-scenario communication according to claim 1, characterized in that, The control unit also integrates power management functions and is electrically connected to the local oscillator unit, frequency converter unit, and low-frequency radio frequency channel unit. It is used to allocate working power to each unit and can independently turn on or off any one of the radio frequency transceiver modules and the power supply to the corresponding frequency converter module.

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