A multi-orbit satellite-borne laser communication terminal system

Abstract

The invention discloses a multi-orbit satellite-borne laser communication terminal system, comprising an optical machine body, a tracking and aiming circuit, a communication main control circuit and a laser communication terminal system. The tracking and aiming circuit comprises a motor drive circuit board, a piezoelectric ceramic circuit board, a first and second power conversion circuit board, and a tracking and aiming control circuit board. The communication main control circuit comprises a main control communication circuit board, a second and second power conversion circuit board, a first optical receiving and transmitting circuit board and a second optical receiving and transmitting circuit board. The system, as a satellite payload, completes the establishment of a communication link with a ground terminal, uses laser as an information carrier to exchange and transmit information, and performs satellite-to-ground, inter-satellite and ground terminal laser communications, achieving high code rate, miniaturization, light weight and low occupancy rate requirements, and finally uses a set of optical transceiver system and tracking and aiming system to achieve satellite-to-ground, inter-satellite and ground terminal laser communications.

Description

Technical Field

[0001] The present invention relates to the field of aerospace communication technology, and in particular to a multi-orbit satellite-borne laser communication terminal system. Background Art

[0002] Laser communication technology is the key technology to achieve the mutual transmission of space big data. It is a high-speed, convenient, safe, and flexible modern communication technology. With the development of science and technology, human space activities have gradually increased, and the amount of communication data between satellites and satellites and between satellites and the ground has increased year by year. The required coverage is also getting wider and wider. A large amount of scientific data needs to rely on large-capacity, high-speed, and long-distance space information transmission technology to achieve. At present, only superpowers have mastered intersatellite laser communication technology, and they are in a point-to-point communication state, which cannot form a laser communication network. How to make the laser communication link become the intersatellite backbone link and even form a laser communication network. Existing aerospace lacks such technology.

[0003] Due to the huge cost of satellite payloads, especially large-aperture optical transceivers and high-precision capture, tracking and aiming devices, their implementation is technically difficult and requires a lot of manpower and material resources. At the same time, the space resources, power resources on the satellite, and the orbital time resources between the satellite and the ground station are very valuable, so there are higher requirements for the layout and wiring of the payload and resource sharing. Therefore, this requires a more reasonable layout of the payload and a more reasonable planning of the resources used, so as to save huge costs and satellite resources and complete more communication functions, and its beneficial effects are quite obvious. Summary of the invention

[0004] Technical Solution

[0005] The present invention provides a multi-orbit satellite-borne laser communication terminal system, comprising an optical machine body, a tracking and aiming circuit, a communication main control circuit and a laser communication terminal system, wherein the tracking and aiming circuit comprises a motor drive circuit board, a piezoelectric ceramic circuit board, a first and second power conversion circuit board, and a tracking and aiming control circuit board, and the communication main control circuit comprises a communication main control circuit board, a second and second power conversion circuit board, a first optical receiving and transmitting amplification circuit board and a second optical receiving and transmitting amplification circuit board.

[0006] Preferably, there are four optical machine bodies and four tracking and aiming circuits, which are respectively located at the end angles of the satellite, and the communication main control circuit is located at the center point of the satellite. The communication main control is star-connected to the optical machine body, and the optical machine body is point-to-point connected to the tracking and aiming circuit. The laser communication terminal system adopts a one-to-four layout and wiring method.

[0007] Preferably, the one-to-four layout and wiring method of the laser communication terminal system is that one communication main control circuit, four optical machine bodies and four tracking and aiming circuits work together, and the angle between the line connecting two adjacent optical machine bodies and the center of the communication main control circuit is 90°.

[0008] Preferably, the first secondary power conversion circuit board is connected to the piezoelectric ceramic circuit board, the piezoelectric ceramic circuit board is connected to the motor drive circuit board, the motor drive circuit board is connected to the tracking and aiming control circuit board. The control bus of the tracking and aiming circuit is connected to the optical machine body, and the communication bus of the tracking and aiming circuit is connected to the communication main control circuit.

[0009] Preferably, the second secondary power conversion circuit board is connected to the first optical receiving and transmitting amplification circuit board and the communication main control circuit board respectively, the first optical receiving and transmitting amplification circuit board is connected to the optical machine body through an optical fiber, and the communication main control circuit board is connected to the tracking and aiming circuit through a communication bus. The communication main control circuit board is connected to other devices of the satellite platform through a communication bus.

[0010] Compared with the prior art, the above technical solution of the present invention has the following beneficial technical effects:

[0011] To sum up, the device has a simple structure and novel design. It adopts the method of four optical machines located at the four corners of the satellite, which can be used for simultaneous full-duplex communication in four orbits. It adopts four optical machine bodies that can work simultaneously, which solves the problem that the current laser communication can only be point-to-point, optimizes the layout of satellite-borne equipment, and greatly reduces the weight of onboard cables. It adopts a star-shaped connection between the communication main control circuit and the optical machine body, which optimizes the resource sharing problem of satellite-borne equipment. The four optical machine bodies share one communication main control circuit, which reduces resource investment, improves the reliability of satellite-borne equipment, and further reduces the total weight of onboard cables. This device is suitable for wide promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of the system layout structure of a multi-orbit satellite-borne laser communication terminal system proposed by the present invention.

[0013] Figure 2 This is a schematic diagram of the system wiring structure of a multi-orbit satellite-borne laser communication terminal system proposed by the present invention.

[0014] Figure 3 This is a schematic diagram of the tracking and aiming circuit structure of a multi-orbit satellite-borne laser communication terminal system proposed by the present invention.

[0015] Figure 4 This is a schematic diagram of the structure of a communication main control circuit board of a multi-orbit satellite-borne laser communication terminal system proposed by the present invention.

[0016] Figure numerals: 1. Optical machine body; 2. Tracking and aiming circuit; 3. Communication main control circuit; 4. Motor drive circuit board; 5. Piezoelectric ceramic circuit board; 6. First and second power conversion circuit board; 7. Tracking and aiming control circuit board; 8. Communication main control circuit board; 9. Second and second power conversion circuit board; 10. First optical receiving and transmitting circuit board; 11. Second optical receiving and transmitting circuit board; 12. Payload controller; 13. Onboard router; 14. Integrated communication processor. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0018] like Figure 1-2 As shown, a multi-orbit satellite-borne laser communication terminal system proposed by the present invention includes an optical machine body 1, a tracking and aiming circuit 2, a communication main control circuit 3 and a laser communication terminal system. There are four optical machine bodies 1 and four tracking and aiming circuits 2. The four optical machine bodies 1 and the four tracking and aiming circuits 2 are respectively located at the end angle positions of the satellite, the communication main control circuit 3 is located at the center point of the satellite, the communication main control and the optical machine body 1 are star-connected, and the optical machine body 1 and the tracking and aiming circuit 2 are point-to-point connected. The laser communication terminal system adopts a one-to-four layout and wiring method. The one-to-four layout and wiring method of the laser communication terminal system is that one communication main control circuit 3, four optical machine bodies 1 and four tracking and aiming circuits 2 work together, and the angle between the center lines of two adjacent optical machine bodies 1 and the communication main control circuit 3 is 90°.

[0019] Furthermore, four tracking and aiming circuits 2 provide temperature measurement, temperature control, tracking, aiming, and status monitoring functions for the four optical machine bodies 1 nearby, and a communication main control circuit 3 provides integrated communication encoding and decoding, optical amplification, remote control and telemetry, error correction coding of communication data, data interleaving, data stream randomization, and modulation of optical signal output power. The tracking and aiming accuracy directly determines the efficiency of laser energy transmission. Especially when the target system (i.e., the system receiving laser energy) is a mobile target (e.g., a drone or spacecraft), a low-precision tracking and aiming system will cause part of the laser beam to "miss the target", so that part of the photovoltaic panel does not receive laser irradiation, resulting in energy loss, which directly leads to reduced energy transmission efficiency.

[0020] Furthermore, it supports simultaneous full-duplex communication of laser communication terminals on four tracks, including two same-tracks, two different-tracks or four different-tracks laser communications, and the four communication tracks are all capable of working independently.

[0021] Furthermore, the tracking and aiming control of each optical machine body 1 is implemented by the nearest tracking and aiming circuit 2, the temperature measurement and temperature control of each optical machine body 1 is implemented by the nearest tracking and aiming circuit 2, the status monitoring of each optical machine body 1 is implemented by the nearest tracking and aiming circuit 2, and the laser signal of each optical machine body 1 is transmitted to the communication main control circuit 3 through the optical fiber for communication encoding and decoding and optical amplification. The communication main control circuit 3 is responsible for connecting to the satellite platform for business data and monitoring data transmission, and the communication main control circuit 3 is responsible for routing allocation and remote control and telemetry data distribution for each tracking and aiming circuit 2.

[0022] like Figure 3 As shown, the tracking and aiming circuit 2 includes a motor drive circuit board 4, a piezoelectric ceramic circuit board 5, a first secondary power conversion circuit board 6, and a tracking and aiming control circuit board 7. The first secondary power conversion circuit board 6 is connected to the primary power supply on the satellite for secondary power conversion. After the conversion, the first secondary power conversion circuit board 6 is connected to the piezoelectric ceramic circuit board 5, the piezoelectric ceramic circuit board 5 is connected to the motor drive circuit board 4, and the motor drive circuit board 4 is connected to the tracking and aiming control circuit board 7. The control bus of the tracking and aiming circuit 2 is connected to the optical machine body 1, and the communication bus of the tracking and aiming circuit 2 is connected to the communication main control circuit 3.

[0023] Furthermore, the motor drive circuit board 4 in the tracking and aiming circuit 2 drives the two-dimensional turntable of the optical machine body 1, the piezoelectric ceramic circuit board 5 drives the piezoelectric fast reflection mirror, the first and second power conversion circuit board 6 provides secondary power, and the tracking and aiming control circuit board 7 provides thermal control, servo drive, tracking and aiming algorithm, and thermal control algorithm.

[0024] Furthermore, the tracking and aiming algorithm and the thermal control algorithm are: in a mobile environment, the relative movement of the communication transceiver will cause the receiving angle and optical power of the optical signal to change dramatically. Therefore, the tracking and aiming control circuit board 7 used in this scenario requires higher tracking accuracy and stability, and the tracking response delay should be small, and the tracking speed should be as high as possible. The existing scheme has obvious lag in the tracking and aiming action due to the problem of processing data processing delay and mechanical movement delay, resulting in poor laser communication performance and even link transmission interruption. Now the prediction of the motion trajectory is added, so that the tracking and aiming action can be carried out in advance, and by shortening the straight-line distance between the optical machine body 1 and the tracking and aiming control circuit board 7, and shortening the straight-line distance between the tracking and aiming circuit 2 and the communication main control circuit 3, the lag phenomenon can be eliminated to a certain extent.

[0025] like Figure 4As shown, the communication main control circuit 3 includes a communication main control circuit board 8, a second secondary power conversion circuit board 9, a first optical receiving and transmitting circuit board 10, and a second optical receiving and transmitting circuit board 11. The second secondary power conversion circuit board 9 is connected to the primary power supply on the satellite for secondary power conversion. After the conversion, the second secondary power conversion circuit board 9 is respectively connected to the first optical receiving and transmitting circuit board 10 and the communication main control circuit board 3 MS1. The first optical receiving and transmitting circuit board 10 is connected to the optical machine body 1 through an optical fiber, and the communication main control circuit board 3 MS1 is connected to the tracking and aiming circuit 2 through a communication bus. The communication main control board circuit is connected to other devices on the satellite platform through a communication bus.

[0026] Furthermore, the communication main control circuit board 8 in the communication main control circuit 3 provides remote control and telemetry for the satellite platform, encodes and decodes four laser signals, and uploads business data. The second secondary power conversion circuit board 9 provides secondary power. The first optical receiving and transmitting circuit board 10 and the second optical receiving and transmitting circuit board 11 amplify the laser signal received by the optical machine body 1 and the laser signal encoded by the communication main control circuit 3, and transmit them to the optical machine body 1 for transmission.

[0027] like Figure 2 As shown, the integrated communication processor 14 is used for: the communication main control circuit 3 is connected to the onboard payload controller 12 for remote control and telemetry, the communication main control circuit 3 is connected to the onboard router 13 to transmit business data through optical fiber, the communication main control unit is connected to the four optical machine bodies 1 through optical fiber, the laser signal of the optical machine body 1 is introduced into the communication main control circuit 3 for encoding and decoding, the communication main control circuit 3 is connected to the four tracking and aiming circuits 2 for routing management and distribution of remote control and telemetry, and the primary power supply of the satellite platform is respectively connected to the secondary power supply conversion board of the communication main control circuit 3 and the secondary power supply board of the tracking and aiming circuit 2.

[0028] like Figure 1-4As shown, the four optical machine bodies 1 are located at the four corners of the satellite platform and can work at the same time, so as to solve the problem that the current space laser communication form can only complete point-to-point communication, which limits the promotion and application of space laser technology. For example, in the process of satellite information transmission, low-orbit satellites cannot directly transmit information back to the control center on the ground, but must use relay communication satellites as transmission intermediaries. Therefore, solving the one-to-many space laser communication technology has a great impact and effect on the field of communication transmission, so laser communication networking can solve this problem. The four optical machine bodies 1 work at the same time, so that the communication main control circuit 3 can simultaneously receive multiple optical signals from different directions, so as to achieve one-to-many space laser communication technology. The four tracking and aiming circuits 2 are located near the optical machine body 1, responsible for providing tracking, aiming and thermal control functions for the optical machine body 1. Because the tracking and aiming circuit 2 is very close, it can greatly shorten the on-board cable, thereby reducing the total weight of the on-board cable. The four optical machine bodies 1 and the four tracking and aiming circuits 2 share a communication main control circuit 3, which reduces on-board resources and the total amount of circuit boards; the communication main control circuit 3 uniformly transmits and processes data to the satellite platform, further reducing the total weight of the on-board cable.

[0029] It should be understood that the above specific embodiments of the present invention are only used to illustrate or explain the principles of the present invention, and do not constitute a limitation of the present invention. Therefore, any modifications, equivalent substitutions, improvements, etc. made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. In addition, the appended claims of the present invention are intended to cover all changes and modifications that fall within the scope and boundaries of the appended claims, or the equivalent forms of such scope and boundaries.

Claims

1. A multi-orbit satellite-borne laser communication terminal system, comprising an optical machine body (1), a tracking and aiming circuit (2), a communication main control circuit (3) and a laser communication terminal system, characterized in that: The tracking and aiming circuit (2) comprises a motor drive circuit board (4), a piezoelectric ceramic circuit board (5), a first secondary power conversion circuit board (6), and a tracking and aiming control circuit board (7); the communication main control circuit (3) comprises a communication main control circuit board (8), a second secondary power conversion circuit board (9), a first optical receiving and transmitting amplifying circuit board (10), and a second optical receiving and transmitting amplifying circuit board (11); The optical machine body (1) and the tracking and aiming circuit (2) are each provided with four, the four optical machine bodies (1) and the four tracking and aiming circuits (2) are respectively located at the end angle positions of the satellite, the communication main control circuit (3) is located at the center point of the satellite, the communication main control circuit (3) and the optical machine body (1) are star-connected, the optical machine body (1) and the tracking and aiming circuit (2) are point-to-point connected, and the laser communication terminal system adopts a one-to-four layout wiring method; The one-to-four layout and wiring method of the laser communication terminal system is that one communication main control circuit (3), four optical machine bodies (1) and four tracking and aiming circuits (2) work together, and the angle between the center connection line of two adjacent optical machine bodies (1) and the communication main control circuit (3) is 90°; The first secondary power conversion circuit board (6) is connected to the piezoelectric ceramic circuit board (5), the piezoelectric ceramic circuit board (5) is connected to the motor drive circuit board (4), the motor drive circuit board (4) is connected to the tracking and aiming control circuit board (7), the control bus of the tracking and aiming circuit (2) is connected to the optical machine body (1), and the communication bus of the tracking and aiming circuit (2) is connected to the communication main control circuit (3); The second secondary power conversion circuit board (9) is respectively connected to the first optical receiving and transmitting amplification circuit board (10) and the communication main control circuit board (8); the first optical receiving and transmitting amplification circuit board (10) is connected to the optical machine body (1) via an optical fiber; the communication main control circuit board (8) is connected to the tracking and aiming circuit (2) via a communication bus; and the communication main control circuit board (8) is connected to other devices on the satellite platform via the communication bus.

2. A multi-orbit satellite-borne laser communication terminal system according to claim 1, characterized in that: The four tracking and aiming circuits (2) provide temperature measurement, temperature control, tracking, aiming, and status monitoring functions for the four optical machine bodies (1) nearby, and a communication main control circuit (3) provides integrated communication encoding and decoding, optical amplification, remote control and telemetry, error correction encoding of communication data, data interleaving, data stream randomization, and modulation of optical signal output power.

3. A multi-orbit satellite-borne laser communication terminal system according to claim 1, characterized in that: The tracking and aiming control of each optical machine body (1) is implemented by the nearest tracking and aiming circuit (2), the temperature measurement and temperature control of each optical machine body (2) is implemented by the nearest tracking and aiming circuit (2), the status monitoring of each optical machine body (1) is implemented by the nearest tracking and aiming circuit (2), the laser signal of each optical machine body (1) is transmitted to the communication main control circuit (3) through the optical fiber for communication encoding and decoding and optical amplification, the communication main control circuit (3) is responsible for connecting to the satellite platform for business data and monitoring data transmission, and the communication main control circuit (3) is responsible for routing allocation and remote control and telemetry data distribution for each tracking and aiming circuit (2).

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