High and low orbit inter-satellite link and relay data transmission link integrated system

Abstract

The invention relates to a high and low orbit inter-satellite link and relay data transmission link integrated system comprising a Ka reflector antenna used for receiving a forward beacon signal, generating a sum branch signal and a difference branch signal, receiving a Ka frequency band forward inter-satellite link signal and transmitting a Ka frequency band backward inter-satellite link signal; the output end comprises a difference branch channel and a sum branch channel; the Ka input filter is used for filtering the difference branch signal; the transmit-receive multiplexer is used for performing transmit-receive isolation on the forward and backward inter-satellite link signals of the Ka frequency band and filtering sum branch signals; the input end of the tracking receiver is connected with the output end of the Ka input filter and the first output end of the transceiving multiplexer; the output end and the input end of the inter-satellite link terminal are respectively connected with the second input end and the second output end of the transceiving multiplexer; and the terminal controller is in communication connection with the tracking receiver, the inter-satellite link terminal and the Ka reflector antenna. The invention has the characteristics of integration, miniaturization and light weight.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and in particular to an integrated system of high-orbit and low-orbit inter-satellite links and relay data transmission links. Background Art

[0002] With the rapid development and application of aerospace technology, the traditional single-satellite independent working mode has become increasingly difficult to meet application needs due to its limited detection and communication areas. The satellite network composed of low-orbit satellites and high-orbit satellites can achieve the complementary advantages of satellites at two orbital heights. It has the advantages of high spatial spectrum utilization and large-scale coverage. It plays a special role in environmental and disaster monitoring, resource detection, navigation, communication and broadcasting. In the satellite network, it is necessary to timely interact and integrate the data obtained by each satellite through inter-satellite communication to improve the efficiency of mission execution and satellite effectiveness. Therefore, inter-satellite communication system technology plays a very important role.

[0003] At present, the domestic low-orbit satellite inter-satellite link system uses an independent set of Ka antennas, radio frequency and baseband processing equipment to complete inter-satellite communications with high-orbit satellites, and the relay data transmission system uses another independent set of Ka antennas, radio frequency and baseband processing equipment to complete inter-satellite data transmission with relay satellites. This results in a large number of system equipment, and the system has a large size, weight and power consumption, which makes it difficult to meet the engineering needs of low-orbit satellite system integration, miniaturization and lightweight. Summary of the invention

[0004] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide an integrated system of high- and low-orbit inter-satellite links and relay data transmission links, which has the characteristics of integration, miniaturization and lightweight.

[0005] To achieve the above-mentioned purpose, the present invention provides an integrated system of high-orbit inter-satellite links and relay data transmission links, comprising:

[0006] A Ka reflector antenna is used to receive a forward beacon signal transmitted by a relay satellite, generate a sum branch signal and a difference branch signal, and receive a Ka-band forward intersatellite link signal transmitted by a high-orbit satellite and a Ka-band return intersatellite link signal transmitted to the high-orbit satellite; the output end of the Ka reflector antenna includes a difference branch channel and a sum branch channel;

[0007] Ka input filter, whose input end is connected to the difference branch channel, for filtering the difference branch signal;

[0008] a transceiver multiplexer, used for performing transceiver isolation on the Ka-band forward intersatellite link signal and the Ka-band return intersatellite link signal, and filtering the sum branch signal; a first input end of the transceiver multiplexer is connected to the sum branch channel;

[0009] A tracking receiver, whose input end is connected to the output end of the Ka input filter and the first output end of the transceiver multiplexer;

[0010] an intersatellite link terminal, whose output end and input end are respectively connected to the second input end and the second output end of the transceiver multiplexer, and is used to receive the Ka-band forward intersatellite link signal from the transceiver multiplexer, and send the Ka-band return intersatellite link signal to the transceiver multiplexer;

[0011] A terminal controller is communicatively connected with the tracking receiver, the intersatellite link terminal and the Ka reflector antenna.

[0012] According to a technical solution of the present invention, when the relay data transmission link is working, the Ka reflector antenna receives the forward beacon signal transmitted by the relay satellite, when the Ka reflector antenna is aligned with the relay satellite, the antenna excitation generates the sum branch signal, and when the Ka reflector antenna 1 deviates from the relay satellite, the antenna excitation generates the difference branch signal; and the sum branch signal is transmitted to the tracking receiver through the sum branch channel after being filtered by the transceiver multiplexer; the difference branch signal is transmitted to the tracking receiver through the difference branch channel after being filtered by the Ka input filter;

[0013] The tracking receiver performs low-noise amplification on the received sum branch signal and difference branch signal, performs four-phase modulation on the difference branch signal, and then combines the difference branch signal and the sum branch signal into a single-channel modulated signal, and then performs two frequency conversions to an intermediate frequency signal to capture and track the carrier; after carrier synchronization, the angle error signal and the sum signal parameter value are separated under the action of the reference signal.

[0014] According to a technical solution of the present invention, when the high-orbit intersatellite link is working, the Ka reflector antenna receives the Ka-band forward intersatellite link signal transmitted by the high-orbit satellite, sends the Ka-band forward intersatellite link signal to the transceiver multiplexer through the sum branch channel, and transmits the signal to the intersatellite link terminal after filtering by the transceiver multiplexer;

[0015] The intersatellite link terminal transmits the Ka-band return intersatellite link signal to the transceiver multiplexer, and the transceiver multiplexer sends the Ka-band return intersatellite link signal to the Ka reflector antenna after filtering, and transmits the Ka-band return intersatellite link signal to the high-orbit satellite through the Ka reflector antenna.

[0016] According to a technical solution of the present invention, the transceiver multiplexer includes:

[0017] A sum signal filter, whose input end is connected to the sum branch channel and whose output end is connected to the tracking receiver;

[0018] A circulator, used to isolate the Ka-band forward intersatellite link signal and the Ka-band return intersatellite link signal;

[0019] A Ka-band forward intersatellite link signal filter, used for filtering the Ka-band forward intersatellite link signal;

[0020] The Ka-band return intersatellite link signal filter is used to filter the Ka-band return intersatellite link signal.

[0021] According to a technical solution of the present invention, it also includes:

[0022] An isolator is arranged between the input end of the Ka input filter and the output end of the differential branch channel.

[0023] According to a technical solution of the present invention, it also includes:

[0024] A crystal oscillator source is communicatively connected to the terminal controller; the crystal oscillator source is used to provide a precise clock signal to the tracking receiver and the intersatellite link terminal.

[0025] According to a technical solution of the present invention, the operating frequency band of the Ka input filter is 23535±20MHz;

[0026] The operating frequency bands of the transceiver multiplexer are: the forward operating frequency band is 23535±20MHz and 24600±150MHz; the return operating frequency band is 25050±150MHz;

[0027] The frequency range of the sum branch signal is 23535±20MHz, the frequency range of the Ka-band forward intersatellite link signal is 24600±150MHz; the frequency range of the Ka-band return intersatellite link signal is 25050±150MHz.

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

[0029] The present invention receives a forward beacon signal transmitted by a relay satellite through a reflector antenna, and divides the forward beacon signal into a sum branch signal and a difference branch signal. The sum branch signal is transmitted to a tracking receiver through a transceiver multiplexer, and the difference branch signal is transmitted to a tracking receiver through an input filter. The received sum branch signal and difference branch signal are processed by the tracking receiver to realize the operation of the relay data transmission link. The forward intersatellite link signal transmitted by the high-orbit satellite is received through the reflector antenna, and the forward intersatellite link signal is transmitted to the intersatellite link terminal through the sum branch channel through the transceiver multiplexer. The intersatellite link terminal transmits a Ka-band return intersatellite link signal, which is sent to the Ka reflector antenna through the transceiver multiplexer and the sum branch channel, and then transmitted to the high-orbit satellite.

[0030] The present invention, while ensuring smooth high-orbit and low-orbit inter-satellite link communication or relay data transmission link communication, only needs to point the Ka reflector antenna to the high-orbit satellite or the relay satellite respectively, so as to realize high-orbit and low-orbit inter-satellite link communication or relay data transmission link communication.

[0031] In the present invention, through the multiplexing and integrated design of Ka reflector antennas, transceiver multiplexers and other equipment, the integrated and integrated design of high- and low-orbit inter-satellite links and relay data transmission link communication systems is realized, which can effectively reduce the complexity of the system and the number of equipment, thereby achieving the goal of miniaturization, high integration and lightweight of the low-orbit satellite system. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0033] Figure 1 The structure diagram of the integrated system of high-orbit and low-orbit inter-satellite links and relay data transmission links provided according to one embodiment of the present invention is schematically shown.

[0034] The corresponding relationship between the reference numerals and component names is as follows:

[0035] 1. Ka reflector antenna; 2. Isolator; 3. Ka input filter; 4. Transceiver multiplexer; 5. Tracking receiver; 6. Terminal controller; 7. Intersatellite link terminal; 8. Crystal oscillator source;

[0036] 11. Differential branch channel; 12. Sum branch channel. DETAILED DESCRIPTION

[0037] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0038] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0039] like Figure 1 As shown, a high-orbit intersatellite link and relay data transmission link integrated system of the present invention comprises:

[0040] The Ka reflector antenna 1 is used to receive the forward beacon signal transmitted by the relay satellite, generate a sum branch signal and a difference branch signal, and receive the Ka-band forward intersatellite link signal transmitted by the high-orbit satellite and the Ka-band return intersatellite link signal transmitted to the high-orbit satellite; the output end of the Ka reflector antenna 1 includes a difference branch channel 11 and a sum branch channel 12;

[0041] Ka input filter 3, whose input end is connected to the difference branch channel 11, is used to filter the difference branch signal; the operating frequency of Ka input filter 3 is;

[0042] The transceiver multiplexer 4 is used for transmitting and receiving isolation of Ka-band forward intersatellite link signals and Ka-band return intersatellite link signals, and filtering the sum branch signal; its first input end is connected to the sum branch channel 12; the operating frequency of the transceiver multiplexer 4 is.

[0043] A tracking receiver 5, whose input end is connected to the output end of the Ka input filter 3 and the first output end of the transceiver multiplexer 4;

[0044] an intersatellite link terminal 7, whose output end and input end are respectively connected to the second input end and the second output end of the transceiver multiplexer 4, for receiving a Ka-band forward intersatellite link signal from the transceiver multiplexer 4, and sending a Ka-band return intersatellite link signal to the transceiver multiplexer 4;

[0045] The terminal controller 6 is communicatively connected with the tracking receiver 5 , the intersatellite link terminal 7 and the Ka reflector antenna 1 .

[0046] In the present invention, both the high- and low-orbit intersatellite links and the relay data transmission links adopt the Ka-band for data transmission. By reusing Ka antennas, radio frequency channels, and some transmission waveguides and other equipment for the intersatellite links and relay data transmission, the problems of independent operation of traditional low-orbit satellite systems, a large number of equipment, and large system size, weight, and power consumption are solved, thereby meeting the engineering needs of low-orbit satellite system integration, miniaturization, and lightweight.

[0047] In a technical solution of the present invention, the transceiver multiplexer 4 includes a sum signal filter, a circulator, a Ka-band forward intersatellite link signal filter and a Ka-band return intersatellite link signal filter. The input end of the sum signal filter is connected to the sum branch channel, and the output end is connected to the tracking receiver; the circulator is used to isolate the Ka-band forward intersatellite link signal and the Ka-band return intersatellite link signal; the Ka-band forward intersatellite link signal filter is used to filter the Ka-band forward intersatellite link signal; the Ka-band return intersatellite link signal filter is used to filter the Ka-band return intersatellite link signal.

[0048] In a technical solution of the present invention, the integrated system of high-orbit inter-satellite links and relay data transmission links also includes:

[0049] The isolator 2 is arranged between the input end of the Ka input filter 3 and the output end of the differential branch channel 11 .

[0050] The isolator 2 is used for the Ka input filter 3 and the Ka reflector antenna 1 to prevent the signal power received by the Ka reflector antenna 1 from being too high, thereby damaging the Ka input filter 3. The isolator 2 may be a radio frequency isolator, a circulator, or the like.

[0051] In a technical solution of the present invention, the integrated system of high-orbit inter-satellite links and relay data transmission links also includes:

[0052] The crystal oscillator source 8 is in communication connection with the terminal controller 6 ; the crystal oscillator source 8 is used to provide a precise clock signal to the tracking receiver 5 and the intersatellite link terminal 7 .

[0053] like Figure 1 As shown, the crystal oscillator source 8 can be a 100MHz crystal oscillator source, and the specific operating frequency of the crystal oscillator source can be set according to actual working needs. The crystal oscillator source 8 and the tracking receiver 5 can be connected to the terminal controller 6 through the 422 port.

[0054] The working process of the present invention is as follows:

[0055] The operating frequency band of the Ka input filter 3 is 23535±20MHz; the operating frequency band of the transceiver multiplexer 4 is: the forward operating frequency band is 23535±20MHz and 24600±150MHz; the return operating frequency band is 25050±150MHz. The frequency range of the sum signal is 23535±20MHz, the frequency range of the Ka-band forward intersatellite link signal is 24600±150MHz; the frequency range of the Ka-band return intersatellite link signal is 25050±150MHz.

[0056] like Figure 1 As shown, when the relay data transmission link is working, the terminal controller 6 controls the Ka reflector antenna 1 to point to the relay satellite, and the Ka reflector antenna 1 receives the forward beacon signal transmitted by the relay satellite. When the Ka reflector antenna 1 is aligned with the relay satellite, the antenna excitation generates a sum branch signal, and when the Ka reflector antenna 1 deviates from the relay satellite, the antenna excitation generates a difference branch signal; the sum branch signal is transmitted to the tracking receiver 5 after being filtered by the transceiver multiplexer 4 through the sum branch channel 12; the difference branch signal is transmitted to the tracking receiver 5 after being filtered by the Ka input filter 3 through the difference branch channel 11;

[0057] The tracking receiver 5 processes the received sum branch signal and difference branch signal to obtain the relay digital transmission signal.

[0058] The processing of the sum branch signal and the difference branch signal includes: the tracking receiver 5 respectively low-noise amplifies the received sum branch signal and difference branch signal, performs four-phase modulation on the difference branch signal, and then combines the difference branch signal and the sum branch signal into a single-channel modulated signal, and then performs two frequency conversions to an intermediate frequency signal to capture and track the carrier; after the carrier is synchronized, the angle error signal and the sum signal parameter value are separated under the action of the reference signal.

[0059] When the high-orbit intersatellite link is working, the terminal controller 6 controls the Ka reflector antenna 1 to point to the high-orbit satellite, and the Ka reflector antenna 1 receives the Ka-band forward intersatellite link signal transmitted by the high-orbit satellite, and sends the Ka-band forward intersatellite link signal to the transceiver multiplexer 4 through the branch channel 12. The 24600±150MHz signal is filtered out by the transceiver multiplexer 4 and then transmitted to the intersatellite link terminal 7;

[0060] The intersatellite link terminal 7 transmits the Ka-band return intersatellite link signal to the transceiver multiplexer 4. The transceiver multiplexer 4 filters out the 25050±150 MHz signal and sends the Ka-band return intersatellite link signal to the Ka reflector antenna 1. The Ka-band return intersatellite link signal is transmitted to the high-orbit satellite through the Ka reflector antenna 1.

[0061] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. An integrated system of high-orbit and low-orbit intersatellite links and relay data transmission links, characterized in that: include: A Ka reflector antenna (1) is used to receive a forward beacon signal transmitted by a relay satellite, generate a sum branch signal and a difference branch signal, and receive a Ka-band forward intersatellite link signal transmitted by a high-orbit satellite and a Ka-band return intersatellite link signal transmitted to the high-orbit satellite; the output end of the Ka reflector antenna (1) includes a difference branch channel (11) and a sum branch channel (12); A Ka input filter (3), an input end of which is connected to the differential branch channel (11) and is used to filter the differential branch signal; A transceiver multiplexer (4) is used for performing transceiver isolation on the Ka-band forward intersatellite link signal and the Ka-band return intersatellite link signal, and filtering the sum branch signal; a first input end of the multiplexer is connected to the sum branch channel (12); A tracking receiver (5), whose input end is connected to the output end of the Ka input filter (3) and the first output end of the transceiver multiplexer (4); an intersatellite link terminal (7), the output end and the input end of which are respectively connected to the second input end and the second output end of the transceiver multiplexer (4), for receiving the Ka-band forward intersatellite link signal from the transceiver multiplexer (4), and sending the Ka-band return intersatellite link signal to the transceiver multiplexer (4); A terminal controller (6) is communicatively connected with the tracking receiver (5), the intersatellite link terminal (7) and the Ka reflector antenna (1).

2. The integrated system of high-orbit and low-orbit intersatellite links and relay data transmission links according to claim 1 is characterized in that: When the relay data transmission link is working, the Ka reflector antenna (1) receives the forward beacon signal transmitted by the relay satellite. When the Ka reflector antenna (1) is aligned with the relay satellite, the antenna is excited to generate the sum branch signal. When the Ka reflector antenna (1) deviates from the relay satellite, the antenna is excited to generate the difference branch signal. The sum branch signal is transmitted to the tracking receiver (5) through the sum branch channel (12) and filtered by the transceiver multiplexer (4). The difference branch signal is transmitted to the tracking receiver (5) through the difference branch channel (11) and filtered by the Ka input filter (3). The tracking receiver (5) performs low-noise amplification on the received sum branch signal and difference branch signal, performs four-phase modulation on the difference branch signal, synthesizes the difference branch signal and the sum branch signal into a single-channel modulated signal, and then performs two frequency conversions to an intermediate frequency signal to capture and track the carrier; After carrier synchronization, the angle error signal and the signal parameter value are separated under the action of the reference signal.

3. The integrated system of high-orbit and low-orbit intersatellite links and relay data transmission links according to claim 1 is characterized in that: When the high-orbit intersatellite link is working, the Ka reflector antenna (1) receives a Ka-band forward intersatellite link signal transmitted by the high-orbit satellite, sends the Ka-band forward intersatellite link signal to the transceiver multiplexer (4) through the branch channel (12), and transmits the signal to the intersatellite link terminal (7) after filtering by the transceiver multiplexer (4); The intersatellite link terminal (7) transmits the Ka-band return intersatellite link signal to the transceiver multiplexer (4), and the transceiver multiplexer (4) sends the Ka-band return intersatellite link signal to the Ka reflector antenna (1) after filtering, and transmits the Ka-band return intersatellite link signal to the high-orbit satellite through the Ka reflector antenna (1).

4. The integrated system of high-orbit and low-orbit intersatellite links and relay data transmission links according to claim 1, characterized in that: The transceiver multiplexer (4) comprises: A sum signal filter, whose input end is connected to the sum branch channel and whose output end is connected to the tracking receiver; A circulator, used to isolate the Ka-band forward intersatellite link signal and the Ka-band return intersatellite link signal; A Ka-band forward intersatellite link signal filter, used for filtering the Ka-band forward intersatellite link signal; The Ka-band return intersatellite link signal filter is used to filter the Ka-band return intersatellite link signal.

5. The integrated system of high-orbit and low-orbit intersatellite links and relay data transmission links according to claim 1, characterized in that: Also includes: An isolator (2) is arranged between the input end of the Ka input filter (3) and the output end of the differential branch channel (11).

6. The high-orbit intersatellite link and relay data transmission link integrated system according to claim 1, characterized in that: Also includes: A crystal oscillator source (8) is communicatively connected to the terminal controller (6); the crystal oscillator source (8) is used to provide a precise clock signal to the tracking receiver (5) and the intersatellite link terminal (7).

7. The integrated system of high-orbit intersatellite links and relay data transmission links according to claim 1, characterized in that: The operating frequency band of the Ka input filter (3) is 23535±20 MHz; The operating frequency bands of the transceiver multiplexer (4) are: the forward operating frequency band is 23535±20MHz and 24600±150MHz; the return operating frequency band is 25050±150MHz; The frequency range of the neutralization signal is 23535±20MHz, the frequency range of the Ka-band forward intersatellite link signal is 24600±150MHz, and the frequency range of the Ka-band return intersatellite link signal is 25050±150MHz.

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