Multi-orbit and multi-system oriented inter-satellite communication system of low-orbit remote sensing satellites

Abstract

The invention discloses a multi-orbit and multi-system oriented low-orbit remote sensing satellite inter-satellite communication system, which comprises an inter-satellite medium and low orbit subsystem, an inter-satellite ground subsystem and an inter-satellite high orbit subsystem. The inter-satellite medium and low orbit subsystem is used for establishing a communication link with low orbit satellites and transmitting measurement and control information between the low orbit satellites; the inter-satellite ground subsystem is used for establishing a communication link with a ground station and transmitting measurement and control information between the satellite and the ground; the inter-satellite to-ground subsystem is also used for establishing a communication link with the near-ground aircraft to complete measurement and control information transmission; the inter-satellite high-orbit subsystem is used for establishing a communication link with a high-orbit satellite and transmitting satellite-ground measurement and control information; when a satellite-ground fault occurs, the inter-satellite communication system of the low-orbit remote sensing satellites establishes a satellite-ground fault troubleshooting communication channel to transmit information required by system troubleshooting. According to the method, the problem of simultaneous communication of inter-satellite communication links of the low-orbit remote sensing satellite under various systems in a cross-orbit manner is solved, and a technical foundation is laid for a multi-orbit multi-system inter-satellite communication application scene of the low-orbit remote sensing satellite.

Description

Technical Field

[0001] The present invention relates to a multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system, which is used for providing low-orbit satellites with communication services of multiple different systems with co-orbit, different-orbit, high-orbit satellites and the ground, and belongs to the field of aerospace technology. Background Art

[0002] With the development of satellite technology and the gradual increase in user demand, constellations are being used more and more. Intersatellite communication is a trend in the future development of satellites. The main task of intersatellite links is to realize relative measurement and intersatellite communication between space satellites. At present, my country has gradually carried out the application of intersatellite links in orbit. The most typical one is the Beidou constellation in high orbit. There are only some local intersatellite link applications in low orbit, and there is no large-scale intersatellite link application.

[0003] At present, there are several problems between low-orbit remote sensing satellites:

[0004] 1. Due to the low orbit of intersatellite low-orbit remote sensing satellites, their current application scope is relatively narrow, and most of them are between the same orbits;

[0005] 2. The inter-satellite communication modulation of low-orbit remote sensing satellites is relatively simple and not scalable;

[0006] 3. When an abnormal inter-satellite communication problem occurs in the satellite, since it only has inter-satellite communication capability, it lacks a satellite-to-ground transmission channel for evaluating the system status to quickly troubleshoot the problem.

[0007] It can be seen that the current inter-satellite link communication system of low-orbit remote sensing satellites is difficult to directly apply to meet the communication needs of multi-orbit and multi-system, and there is currently a lack of communication design for ground stations, making it difficult for the ground to troubleshoot inter-satellite problems on orbit. Therefore, it is necessary to design an inter-satellite communication system for low-orbit remote sensing satellites that is oriented to multi-orbit and multi-system. Summary of the invention

[0008] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a low-orbit remote sensing satellite inter-satellite communication system for multi-orbit and multi-system, to solve the problem of simultaneous communication of various inter-satellite communication links of low-orbit remote sensing satellites across orbits under multiple systems, and to lay a technical foundation for multi-orbit and multi-system inter-satellite communication application scenarios of low-orbit remote sensing satellites.

[0009] The technical solution of the present invention is:

[0010] A multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system, comprising: an inter-satellite medium-low orbit subsystem, an inter-satellite ground-to-earth subsystem, and an inter-satellite high-orbit subsystem;

[0011] The intersatellite medium and low orbit subsystem is used to establish communication links with low-orbit satellites and transmit measurement and control information between low-orbit satellites;

[0012] The intersatellite-to-ground subsystem is used to establish a communication link with the ground station and transmit measurement and control information between the satellite and the ground. The intersatellite-to-ground subsystem is also used to establish a communication link with the nearby aircraft to complete the measurement and control information transmission.

[0013] The intersatellite high-orbit subsystem is used to establish a communication link with a high-orbit satellite and transmit measurement and control information between the satellite and the ground;

[0014] When a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel to transmit the information required for system fault troubleshooting.

[0015] Furthermore, the intersatellite low-orbit subsystem includes: a low-orbit intersatellite co-orbit antenna (101), a low-orbit intersatellite hetero-orbit antenna (102), a first input-output filter component (103), a second input-output filter component (104), a first solid-state amplifier (105), a second solid-state amplifier (106), an intersatellite communicator (107), and an antenna controller (108);

[0016] The intersatellite medium and low orbit subsystem receives the intersatellite signal on the same orbit through the low orbit intersatellite co-orbit antenna (101), filters the signal through the first input and output filter component (103), and then sends it to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signal, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the first solid-state amplifier (105). After the signal is amplified, it is filtered through the first input and output filter component (103), and then sent to other satellites in medium and low orbits through the low orbit intersatellite co-orbit antenna (101); at the same time, the antenna controller (108) obtains the orbit position information of the own satellite and the target satellite sent by the satellite service to calculate the pointing angle, and controls the angle pointing of the low orbit intersatellite co-orbit antenna (101);

[0017] The intersatellite medium and low orbit subsystem receives intersatellite signals of different orbits through the low orbit intersatellite different orbit antenna (102), filters the signals through the second input and output filter component (104), and then sends them to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signals, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the second solid-state amplifier (106). After the signals are amplified, they are filtered through the second input and output filter component (104), and then sent to other satellites in medium and low orbits through the low orbit intersatellite different orbit antenna (102); at the same time, the antenna controller (108) calculates the pointing angle through the orbit position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the low orbit intersatellite different orbit antenna (102).

[0018] Furthermore, the intersatellite-to-ground subsystem includes: a ground-to-ground receiving antenna (201), a ground-to-ground transmitting antenna (202), an intersatellite communication machine (107) and an antenna controller (108);

[0019] The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or a nearby aircraft via a ground receiving antenna (201) and sends it to an intersatellite communicator (107). The intersatellite communicator (107) demodulates and decodes the received input signal and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated and the modulated information is sent to the ground or a nearby aircraft via a ground transmitting antenna (202). At the same time, the antenna controller (108) calculates the pointing angle based on the orbital position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the ground receiving antenna (201) and the ground transmitting antenna (202).

[0020] Furthermore, the intersatellite high-orbit subsystem includes: an intersatellite high-orbit antenna (301), an input filter (302), an output filter (303), a traveling wave tube amplifier (304), a high-orbit communication machine (305) and an antenna controller (108);

[0021] The intersatellite high-orbit subsystem receives intersatellite information downlinked from a high-orbit satellite through an intersatellite high-orbit antenna (301), filters the information through an input filter (302), and sends the information to a high-orbit communication machine (305). The high-orbit communication machine (305) demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then sent to a traveling wave tube amplifier (304). After the signal is amplified, it is filtered through an output filter (303) and then sent to the high-orbit satellite through the intersatellite high-orbit antenna (301). At the same time, the antenna controller (108) obtains the orbital position information of the own satellite and the target satellite sent by the satellite service, calculates the pointing angle, and controls the angle pointing of the intersatellite high-orbit antenna (301).

[0022] Furthermore, the intersatellite ground-to-earth subsystem and the intersatellite medium- and low-orbit subsystem share an intersatellite communication machine (107); the intersatellite medium- and low-orbit subsystem, the intersatellite ground-to-earth subsystem and the intersatellite high-orbit subsystem share an antenna controller (108).

[0023] Furthermore, when a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel, specifically:

[0024] The low-orbit intersatellite off-orbit antenna and the low-orbit intersatellite on-orbit antenna rotate to the direction of the earth and communicate with the ground station, providing a communication channel for the ground to conduct on-orbit fault troubleshooting of low-orbit satellites;

[0025] The high-orbit antenna rotates to the direction facing the earth and communicates with the ground station, providing a communication channel for the ground to conduct in-orbit fault troubleshooting of high-orbit satellites.

[0026] Furthermore, the intersatellite communication machine (107) supports QPSK, BPSK, and UQPSK, and the code rate supports multiple adjustable levels; when the intersatellite communication machine (107) adopts the UQPSK modulation method, one branch is used to transmit measurement and control information, and the other branch is used for ranging information, thereby realizing the integrated function of inter-satellite ranging communication.

[0027] Second,

[0028] The present invention also proposes a method for establishing a measurement and control link, comprising the following steps:

[0029] The first step is to record the orbit information and control information of the target satellite to be linked on the ground. After the satellite receives the information, the satellite service sends the information recorded on the ground to the antenna controller.

[0030] In the second step, the antenna controller selects the controlled antenna according to the information recorded on the ground, calculates the position information of the target satellite, and controls the corresponding antenna to point to the target satellite;

[0031] In the third step, the antenna motor works according to the control signal, so that the antenna turns to the target satellite and communicates with the target satellite;

[0032] Step 4: After the initial link is established, the two parties exchange their respective navigation position information through inter-satellite measurement and control information. The inter-satellite communication machine or high-orbit communication machine sends the received navigation data of the target satellite to the antenna controller.

[0033] Step 5: The antenna controller calculates the position information of the target satellite and the pointing angle of the antenna based on the orbital position data of the local satellite and the target satellite, and controls the corresponding antenna to continuously point to the target satellite.

[0034] Step 6: After the link is established stably, data transmission is carried out.

[0035] Furthermore, the intersatellite medium and low orbit subsystem receives intersatellite signals of different orbits and same orbits through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna respectively, filters the signal sent by the antenna through the input and output filter component and then sends it to the intersatellite communication machine, the transceiver demodulates and decodes the input signal received by the receiving antenna, and sends the baseband data to the satellite service, while the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the solid-state amplifier, after the signal is amplified, it is filtered through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna, and then sent to other satellites in medium and low orbits;

[0036] The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or nearby aircraft through the ground receiving antenna and sends it to the intersatellite communicator. The intersatellite communicator demodulates and decodes the input signal received by the receiving antenna and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then the modulated information is sent to the ground or nearby aircraft through the ground transmitting antenna.

[0037] The intersatellite high-orbit subsystem receives the intersatellite information downlinked from the high-orbit satellite through the intersatellite high-orbit antenna, and sends it to the high-orbit communication machine after filtering through the input filter. The high-orbit communication machine demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service; at the same time, the information sent by the satellite service is encoded and modulated and sent to the traveling wave tube amplifier. After the signal is amplified, it is filtered through the output filter and sent to the high-orbit satellite through the intersatellite high-orbit antenna.

[0038] The beneficial effects of the present invention compared with the prior art are:

[0039] (1) The low-orbit inter-satellite communication system of the present invention has three independent communication channels, can communicate with multi-orbit satellites, and can communicate with high-orbit satellites, medium-orbit and low-orbit satellites in the same or different orbits, and ground stations at the same time, greatly improving the satellite's airspace communication capability and survivability, and providing technical support for all-day, all-airspace and all-weather communications;

[0040] (2) The low-orbit inter-satellite communication system of the present invention has multiple communication systems and multiple code rates, which can meet multiple systems such as QPSK, BPSK, and UQPSK, and can meet the requirements of low-speed and high-speed multiple code rates;

[0041] (3) Each link of the low-orbit inter-satellite communication system of the present invention can realize ground communication, establish a communication link with the ground station to transmit information, realize on-orbit problem diagnosis, and quickly locate the problem, which greatly improves the satellite's testability and maintainability, and improves the satellite's survivability;

[0042] (4) The present invention can realize a variety of modes of on-orbit application combinations, and real-time communication in various modes such as high-low-ground, low-low-ground, and high-low-low, which greatly improves the task coordination response speed, expands the scope of coordinated work, and enhances the on-orbit application capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a schematic diagram of the composition of the intersatellite communication system of the present invention;

[0044] Figure 2 Create a flow chart for the link. DETAILED DESCRIPTION

[0045] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0046] like Figure 1 As shown, the present invention provides a satellite-borne anti-interference and high-speed measurement and control system for low-orbit satellite measurement and control applications, the system comprising an inter-satellite low-orbit subsystem 10, an inter-satellite ground-to-earth subsystem 20, and an inter-satellite high-orbit subsystem 30.

[0047] The intersatellite medium and low orbit subsystem is used to establish communication links with low-orbit satellites and transmit measurement and control information between low-orbit satellites;

[0048] The intersatellite-to-ground subsystem is used to establish a communication link with the ground station and transmit measurement and control information between the satellite and the ground. The intersatellite-to-ground subsystem is also used to establish a communication link with the nearby aircraft to complete the measurement and control information transmission.

[0049] The intersatellite high-orbit subsystem is used to establish a communication link with a high-orbit satellite and transmit measurement and control information between the satellite and the ground;

[0050] When a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel to transmit the information required for system fault troubleshooting.

[0051] like Figure 1 As shown, in the present invention, the intersatellite low-orbit subsystem includes: a low-orbit intersatellite co-orbit antenna (101), a low-orbit intersatellite hetero-orbit antenna (102), a first input-output filter component (103), a second input-output filter component (104), a first solid-state amplifier (105), a second solid-state amplifier (106), an intersatellite communicator (107) and an antenna controller (108);

[0052] The intersatellite medium and low orbit subsystem receives the intersatellite signal on the same orbit through the low orbit intersatellite co-orbit antenna (101), filters the signal through the first input and output filter component (103), and then sends it to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signal, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the first solid-state amplifier (105). After the signal is amplified, it is filtered through the first input and output filter component (103), and then sent to other satellites in medium and low orbits through the low orbit intersatellite co-orbit antenna (101); at the same time, the antenna controller (108) obtains the orbit position information of the own satellite and the target satellite sent by the satellite service to calculate the pointing angle, and controls the angle pointing of the low orbit intersatellite co-orbit antenna (101);

[0053] The intersatellite medium and low orbit subsystem receives intersatellite signals of different orbits through the low orbit intersatellite different orbit antenna (102), filters the signals through the second input and output filter component (104), and then sends them to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signals, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the second solid-state amplifier (106). After the signals are amplified, they are filtered through the second input and output filter component (104), and then sent to other satellites in medium and low orbits through the low orbit intersatellite different orbit antenna (102); at the same time, the antenna controller (108) calculates the pointing angle through the orbit position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the low orbit intersatellite different orbit antenna (102).

[0054] like Figure 1 As shown, in the present invention, the intersatellite-to-ground subsystem includes: a ground-to-ground receiving antenna (201), a ground-to-ground transmitting antenna (202), an intersatellite communication machine (107) and an antenna controller (108);

[0055] The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or a nearby aircraft via a ground receiving antenna (201) and sends it to an intersatellite communicator (107). The intersatellite communicator (107) demodulates and decodes the received input signal and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated and the modulated information is sent to the ground or a nearby aircraft via a ground transmitting antenna (202). At the same time, the antenna controller (108) calculates the pointing angle based on the orbital position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the ground receiving antenna (201) and the ground transmitting antenna (202).

[0056] like Figure 1 As shown, in the present invention, the intersatellite high-orbit subsystem includes: an intersatellite high-orbit antenna (301), an input filter (302), an output filter (303), a traveling wave tube amplifier (304), a high-orbit communication machine (305) and an antenna controller (108);

[0057] The intersatellite high-orbit subsystem receives intersatellite information downlinked from a high-orbit satellite through an intersatellite high-orbit antenna (301), filters the information through an input filter (302), and sends the information to a high-orbit communication machine (305). The high-orbit communication machine (305) demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then sent to a traveling wave tube amplifier (304). After the signal is amplified, it is filtered through an output filter (303) and then sent to the high-orbit satellite through the intersatellite high-orbit antenna (301). At the same time, the antenna controller (108) obtains the orbital position information of the own satellite and the target satellite sent by the satellite service, calculates the pointing angle, and controls the angle pointing of the intersatellite high-orbit antenna (301).

[0058] In the present invention, the intersatellite ground-to-earth subsystem and the intersatellite medium-to-low orbit subsystem share an intersatellite communication machine (107); the intersatellite medium-to-low orbit subsystem, the intersatellite ground-to-earth subsystem and the intersatellite high-orbit subsystem share an antenna controller (108).

[0059] In the present invention, when a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel, specifically:

[0060] The low-orbit intersatellite off-orbit antenna and the low-orbit intersatellite on-orbit antenna rotate to the direction of the earth and communicate with the ground station, providing a communication channel for the ground to conduct on-orbit fault troubleshooting of low-orbit satellites;

[0061] The high-orbit antenna rotates to the direction facing the earth and communicates with the ground station, providing a communication channel for the ground to conduct in-orbit fault troubleshooting of high-orbit satellites.

[0062] Preferably, the intersatellite communication machine (107) supports QPSK, BPSK, and UQPSK, and the code rate supports multiple adjustable levels; when the intersatellite communication machine (107) adopts the UQPSK modulation method, one branch is used to transmit measurement and control information, and the other branch is used for ranging information, thereby realizing the integrated function of inter-satellite ranging communication.

[0063] like Figure 2 As shown, the process of establishing each measurement and control link provided by the present invention is as follows:

[0064] The first step is to record the orbit information (if it is actually facing the ground, record the ground station coordinates) and control information of the target satellite to be linked. After the satellite receives it, the satellite service sends the information recorded on the ground to the antenna controller.

[0065] In the second step, the antenna controller selects the controlled antenna according to the information recorded on the ground, calculates the position information of the target satellite, and controls the corresponding antenna to point to the target satellite;

[0066] In the third step, the antenna motor works according to the control signal, so that the antenna turns to the target satellite and communicates with the target satellite;

[0067] The intersatellite medium and low orbit subsystem receives intersatellite signals in different orbits and in the same orbit through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna respectively. The signal sent by the antenna is filtered by the input and output filter components and then sent to the intersatellite communication machine. The transceiver demodulates and decodes the input signal received by the receiving antenna and sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the solid-state amplifier. After the signal is amplified, it is filtered by the input and output filter components and then sent to other satellites in medium and low orbits through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna.

[0068] The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or nearby aircraft through the ground receiving antenna and sends it to the intersatellite communicator. The intersatellite communicator demodulates and decodes the input signal received by the receiving antenna and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then the modulated information is sent to the ground or nearby aircraft through the ground transmitting antenna.

[0069] The intersatellite high-orbit subsystem receives the intersatellite information downlinked from the high-orbit satellite through the intersatellite high-orbit antenna, and sends it to the high-orbit communication machine after filtering through the input filter. The high-orbit communication machine demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service; at the same time, the information sent by the satellite service is encoded and modulated and sent to the traveling wave tube amplifier. After the signal is amplified, it is filtered through the output filter and sent to the high-orbit satellite through the intersatellite high-orbit antenna.

[0070] Step 4: After the initial link is established, the two parties exchange their respective navigation position information through inter-satellite measurement and control information. The inter-satellite communication machine or high-orbit communication machine sends the received navigation data of the target satellite to the antenna controller.

[0071] Step 5: The antenna controller calculates the position information of the target satellite and the pointing angle of the antenna based on the orbital position data of the local satellite and the target satellite, and controls the corresponding antenna to continuously point to the target satellite.

[0072] The sixth step is to continuously and stably establish the link and then carry out data transmission with large data rates such as digital transmission.

[0073] The above description is only the best specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

[0074] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A low-orbit remote sensing satellite intersatellite communication system for multiple orbits and multiple systems, characterized in that include: Intersatellite low and medium orbit subsystem, intersatellite ground subsystem, and intersatellite high orbit subsystem; The intersatellite medium and low orbit subsystem is used to establish communication links with low-orbit satellites and transmit measurement and control information between low-orbit satellites; The intersatellite-to-ground subsystem is used to establish a communication link with the ground station and transmit measurement and control information between the satellite and the ground; The intersatellite ground subsystem is also used to establish a communication link with nearby ground vehicles to complete the transmission of measurement and control information; The intersatellite high-orbit subsystem is used to establish a communication link with a high-orbit satellite and transmit measurement and control information between the satellite and the ground; When a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel to transmit the information required for system fault troubleshooting.

2. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 1, characterized in that: The intersatellite medium and low orbit subsystem comprises: a low orbit intersatellite co-orbit antenna (101), a low orbit intersatellite hetero-orbit antenna (102), a first input and output filter component (103), a second input and output filter component (104), a first solid-state amplifier (105), a second solid-state amplifier (106), an intersatellite communicator (107) and an antenna controller (108); The intersatellite medium and low orbit subsystem receives the intersatellite signal on the same orbit through the low orbit intersatellite co-orbit antenna (101), filters the signal through the first input and output filter component (103), and then sends it to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signal, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the first solid-state amplifier (105). After the signal is amplified, it is filtered through the first input and output filter component (103), and then sent to other satellites in medium and low orbits through the low orbit intersatellite co-orbit antenna (101); at the same time, the antenna controller (108) obtains the orbit position information of the own satellite and the target satellite sent by the satellite service to calculate the pointing angle, and controls the angle pointing of the low orbit intersatellite co-orbit antenna (101); The intersatellite medium and low orbit subsystem receives intersatellite signals of different orbits through the low orbit intersatellite different orbit antenna (102), filters the signals through the second input and output filter component (104), and then sends them to the intersatellite communication machine (107). The intersatellite communication machine (107) demodulates and decodes the received input signals, and then sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the second solid-state amplifier (106). After the signals are amplified, they are filtered through the second input and output filter component (104), and then sent to other satellites in medium and low orbits through the low orbit intersatellite different orbit antenna (102); at the same time, the antenna controller (108) calculates the pointing angle through the orbit position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the low orbit intersatellite different orbit antenna (102).

3. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 2, characterized in that: The intersatellite ground subsystem comprises: a ground receiving antenna (201), a ground transmitting antenna (202), an intersatellite communication device (107) and an antenna controller (108); The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or a nearby aircraft via a ground receiving antenna (201) and sends it to an intersatellite communicator (107). The intersatellite communicator (107) demodulates and decodes the received input signal and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated and the modulated information is sent to the ground or a nearby aircraft via a ground transmitting antenna (202). At the same time, the antenna controller (108) calculates the pointing angle based on the orbital position information of the own satellite and the target satellite sent by the satellite service, and controls the angle pointing of the ground receiving antenna (201) and the ground transmitting antenna (202).

4. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 3, characterized in that: The intersatellite high-orbit subsystem includes: an intersatellite high-orbit antenna (301), an input filter (302), an output filter (303), a traveling wave tube amplifier (304), a high-orbit communication device (305) and an antenna controller (108); The intersatellite high-orbit subsystem receives intersatellite information downlinked from a high-orbit satellite through an intersatellite high-orbit antenna (301), filters the information through an input filter (302), and sends the information to a high-orbit communication machine (305). The high-orbit communication machine (305) demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then sent to a traveling wave tube amplifier (304). After the signal is amplified, it is filtered through an output filter (303) and then sent to the high-orbit satellite through the intersatellite high-orbit antenna (301). At the same time, the antenna controller (108) obtains the orbital position information of the own satellite and the target satellite sent by the satellite service, calculates the pointing angle, and controls the angle pointing of the intersatellite high-orbit antenna (301).

5. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 4, characterized in that: The intersatellite ground-to-earth subsystem and the intersatellite medium-to-low orbit subsystem share an intersatellite communication machine (107); the intersatellite medium-to-low orbit subsystem, the intersatellite ground-to-earth subsystem and the intersatellite high-orbit subsystem share an antenna controller (108).

6. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 1, characterized in that: When a satellite-to-ground fault occurs, the low-orbit remote sensing satellite inter-satellite communication system establishes a satellite-to-ground fault troubleshooting communication channel, specifically: The low-orbit intersatellite off-orbit antenna and the low-orbit intersatellite on-orbit antenna rotate to the direction of the earth and communicate with the ground station, providing a communication channel for the ground to conduct on-orbit fault troubleshooting of low-orbit satellites; The high-orbit antenna rotates to the direction facing the earth and communicates with the ground station, providing a communication channel for the ground to conduct in-orbit fault troubleshooting of high-orbit satellites.

7. The multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 1, characterized in that: The intersatellite communication machine (107) supports QPSK, BPSK, and UQPSK, and the code rate supports multiple adjustable levels; when the intersatellite communication machine (107) adopts the UQPSK modulation mode, one branch is used to transmit measurement and control information, and the other branch is used for ranging information, thereby realizing the integrated function of inter-satellite ranging communication.

8. A method for establishing a measurement and control link based on the multi-orbit and multi-system low-orbit remote sensing satellite inter-satellite communication system according to claim 1, characterized in that include: The first step is to record the orbit information and control information of the target satellite to be linked on the ground. After the satellite receives the information, the satellite service sends the information recorded on the ground to the antenna controller. In the second step, the antenna controller selects the controlled antenna according to the information recorded on the ground, calculates the position information of the target satellite, and controls the corresponding antenna to point to the target satellite; In the third step, the antenna motor works according to the control signal, so that the antenna turns to the target satellite and communicates with the target satellite; Step 4: After the initial link is established, the two parties exchange their respective navigation position information through inter-satellite measurement and control information. The inter-satellite communication machine or high-orbit communication machine sends the received navigation data of the target satellite to the antenna controller. Step 5: The antenna controller calculates the position information of the target satellite and the pointing angle of the antenna based on the orbital position data of the local satellite and the target satellite, and controls the corresponding antenna to continuously point to the target satellite. Step 6: After the link is established stably, data transmission is carried out.

9. The method for establishing a measurement and control link according to claim 8, characterized in that: The intersatellite medium and low orbit subsystem receives intersatellite signals in different orbits and in the same orbit through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna respectively. The signal sent by the antenna is filtered by the input and output filter components and then sent to the intersatellite communication machine. The transceiver demodulates and decodes the input signal received by the receiving antenna and sends the baseband data to the satellite service. At the same time, the intersatellite communication machine encodes and modulates the information sent by the satellite service and sends it to the solid-state amplifier. After the signal is amplified, it is filtered by the input and output filter components and then sent to other satellites in medium and low orbits through the low-orbit intersatellite different-orbit antenna and the low-orbit intersatellite same-orbit antenna. The intersatellite-to-ground subsystem receives intersatellite information uplinked from the ground or nearby aircraft through the ground receiving antenna and sends it to the intersatellite communicator. The intersatellite communicator demodulates and decodes the input signal received by the receiving antenna and sends the baseband data to the satellite service. At the same time, the information sent by the satellite service is coded and modulated, and then the modulated information is sent to the ground or nearby aircraft through the ground transmitting antenna. The intersatellite high-orbit subsystem receives the intersatellite information downlinked from the high-orbit satellite through the intersatellite high-orbit antenna, and sends it to the high-orbit communication machine after filtering through the input filter. The high-orbit communication machine demodulates and decodes the input signal received by the intersatellite high-orbit antenna, and sends the baseband data to the satellite service; at the same time, the information sent by the satellite service is encoded and modulated and sent to the traveling wave tube amplifier. After the signal is amplified, it is filtered through the output filter and sent to the high-orbit satellite through the intersatellite high-orbit antenna.

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