Optical-mechanical system for intersatellite laser communication terminal

Abstract

The present invention provides an optical-mechanical system for an intersatellite laser communication terminal, comprising: an optical path unit, the optical path unit comprising a single pendulum mirror, the single pendulum mirror scanning the received light from another intersatellite laser communication terminal in a first mode; and a tracking and aiming receiving unit, the tracking and aiming receiving unit determines the spot position of the received light when detecting the received light from the optical path unit, wherein the optical path unit is further configured to adjust the deflection direction of the single pendulum mirror after determining the spot position of the received light to guide the spot position to the center of the tracking and aiming receiving unit and scan the received light in a second mode, wherein the scanning angle of the second mode is smaller than that of the first mode, and the scanning frequency of the second mode is higher than that of the first mode. The optical-mechanical system of the present invention improves the layout flexibility and simplifies the optical-mechanical composition by adopting discrete components.

Description

Technical Field

[0001] The present invention generally relates to the field of intersatellite communications, and more specifically, to an optical-mechanical system for an intersatellite laser communication terminal. Background Art

[0002] At present, with the continuous development of satellite technology and the continuous increase in satellite application scenarios, multiple low-orbit satellite networks have emerged or are planned. In satellite networks, communication between satellites (called intersatellite communication) has become a key technology that restricts the performance of satellite networks. Compared with microwave intersatellite communication, laser communication has the advantages of high bandwidth, light weight, small size and no restrictions on the electromagnetic spectrum, becoming a necessary means to solve the problem of high-speed data transmission in space in the future. Furthermore, compared with high-speed intersatellite laser communication technology, the layout and application advantages of low-speed, low-cost, and large-scale intersatellite laser communication technology are more obvious and the complexity is significantly reduced. Therefore, it is more suitable as a transition technology between microwave intersatellite communication technology and high-speed intersatellite laser communication technology, which has important practical significance for the large-scale commercial application of intersatellite laser communication technology.

[0003] Therefore, the design of intersatellite laser communication terminals carried on satellites for performing intersatellite communication has also become a hot topic in the field of intersatellite laser communication technology.

[0004] Currently, the high-speed transmission design of intersatellite laser communication terminals is complex, costly and cannot be applied on a large scale. Summary of the invention

[0005] In view of the above problems, the present invention provides an inter-satellite laser communication terminal, and more specifically, provides an optical-mechanical system for an inter-satellite laser communication terminal, which improves layout flexibility and simplifies optical-mechanical composition by adopting discrete components.

[0006] According to one aspect of the present invention, there is provided an optical-mechanical system for an intersatellite laser communication terminal, comprising: an optical path unit, the optical path unit comprising a single-oscillating mirror, the single-oscillating mirror scanning a received light from another intersatellite laser communication terminal in a first mode; and a tracking and aiming receiving unit, the tracking and aiming receiving unit determining a spot position of the received light when detecting the received light from the optical path unit, wherein the optical path unit is further configured to, after determining the spot position of the received light, adjust a deflection direction of the single-oscillating mirror to guide the spot position to the center of the tracking and aiming receiving unit and scan the received light in a second mode, wherein a scanning angle of the second mode is smaller than that of the first mode, and a scanning frequency of the second mode is higher than that of the first mode.

[0007] In some implementations, the optical path unit includes: a receiving optical path, the receiving optical path includes the single swing mirror, the transceiver antenna mirror group, the color dichroic mirror, the dual narrow-band filter and the beam splitter arranged in sequence according to the traveling direction of the received light, wherein the transceiver antenna mirror group shrinks the received light from the single swing mirror and transmits it to the color dichroic mirror, the color dichroic mirror transmits the received light and sends it into the dual narrow-band filter, the dual narrow-band filter transmits the received light and transmits the received light to the tracking and aiming receiving unit via the beam splitter.

[0008] In some implementations, the tracking and receiving unit includes a four-quadrant avalanche photodiode detector.

[0009] In some implementations, the optomechanical system further includes: a communication receiving unit, located downstream of the beam splitter, configured to receive the received light from the beam splitter.

[0010] In some implementations, the communication receiving unit includes an avalanche photodiode detector.

[0011] In some implementations, the optical path unit further includes: a first reflector group, the first reflector group is located between the beam splitter and the communication receiving unit, and is used to reflect the received light so that the direction of the received light enters the communication receiving unit vertically.

[0012] In some implementations, the optical path unit further includes a transmitting optical path, and the transmitting optical path is used to send transmitting light to the other inter-satellite laser communication terminal.

[0013] In some implementations, the emission light path includes: a transmitting mirror group, a fast reflection mirror, a color dichroic mirror, a transceiver antenna mirror group and the single swing mirror arranged in sequence according to the direction of travel of the emission light, wherein the transmitting mirror group transmits the emission light emitted by the laser, the fast reflection mirror reflects the emission light to the color dichroic mirror, the color dichroic mirror reflects the emission light, the transceiver antenna mirror group expands the emission light reflected by the color dichroic mirror, and transmits the expanded emission light through the single swing mirror.

[0014] In some implementations, the receiving optical path further includes: a second reflector group, the second reflector group is located between the transceiver antenna mirror group and the dichroic mirror, and is used to reverse the received light in the receiving optical path.

[0015] In some implementations, the emission light path further includes: a second reflector group, the second reflector group is located between the transceiver antenna mirror group and the dichroic mirror, and is used to reverse the emission light in the emission light path.

[0016] In some implementations, the optomechanical system further includes: an advance aiming unit, which determines an advance control amount of the emission light according to received light previously received from the other intersatellite laser communication terminal, so as to perform advance deflection on the emission light emitted by the laser.

[0017] Utilizing the optical-mechanical system for an intersatellite laser communication terminal of the present invention not only improves the layout flexibility of the optical-mechanical system but also simplifies the optical-mechanical components. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The present invention will be better understood and other objects, details, features and advantages of the present invention will become more apparent through the following description of specific embodiments of the present invention given with reference to the accompanying drawings.

[0019] Figure 1 A schematic diagram of an exemplary satellite network according to an embodiment of the present invention is shown.

[0020] Figure 2 A schematic structural diagram of an inter-satellite laser communication terminal according to some embodiments of the present invention is shown.

[0021] Figure 3 A schematic structural diagram of an optical path unit according to an embodiment of the present invention is shown.

[0022] Figure 4 A light path schematic diagram of a light path unit according to an embodiment of the present invention is shown. DETAILED DESCRIPTION

[0023] The preferred embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the preferred embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0024] In the following description, certain specific details are set forth for the purpose of illustrating various embodiments of the invention to provide a thorough understanding of the various embodiments of the invention. However, those skilled in the relevant art will recognize that the embodiments may be practiced without one or more of these specific details. In other cases, well-known devices, structures, and techniques associated with the present application may not be shown or described in detail to avoid unnecessarily obscuring the description of the embodiments.

[0025] Unless the context requires otherwise, throughout the specification and claims, the word "comprise" and variations such as "include" and "have" should be construed in an open, inclusive sense, ie, should be interpreted as "including, but not limited to."

[0026] References throughout the specification to "one embodiment" or "some embodiments" indicate that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, the appearance of "in one embodiment" or "some embodiments" in various places throughout the specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any manner in one or more embodiments.

[0027] In addition, the terms "first", "second", "third", etc. used in the specification and claims are only used to distinguish each object for the sake of clarity of description, and do not limit the size or other order of the objects described, unless otherwise specified.

[0028] Figure 1 A schematic diagram of an exemplary satellite network according to an embodiment of the present invention is shown. Figure 1 , two satellite orbits 1a and 2a around the earth are exemplarily shown, wherein multiple satellites 1b and 2b are arranged on the satellite orbits 1a and 2a respectively, and the multiple satellites 1b and the multiple satellites 2b can communicate with each other in the same orbit.

[0029] Figure 1 The example shows a co-orbit low-orbit satellite network, the orbit type is a sun-synchronous orbit, and the orbit altitude is within 500km. Several co-orbit laser communication terminals can be deployed on each satellite orbit to complete laser communication within a small maneuvering range and within the same orbit. The relative positions between the laser communication terminals used for co-orbit laser communication are stable, the relative maneuvering range is small, the deflection angle range is small, the azimuth angle deflection range is (-90°~+90°), the pitch angle deflection range is (-10°~+10°), and the communication distance range is (300km~1500km).

[0030] In addition, several, for example, three, inter-orbit laser communication terminals can be deployed on each satellite orbit, which can complete information transmission between different orbits with a large angle maneuvering range, for example, to achieve inter-orbit communication between satellite 1b on satellite orbit 1a and satellite 2b on satellite orbit 2a. In this article, only co-orbit communication is used as an example to describe the inter-satellite laser communication terminal on satellite 1b or 2b.

[0031] Figure 2 The schematic diagram of the structure of the intersatellite laser communication terminal 100 according to some embodiments of the present invention is shown. The intersatellite laser communication terminal 100 may be located on satellites 1b and 2b, and is used to perform laser communication with other intersatellite laser communication terminals 100 on other satellites in the same orbit.

[0032] like Figure 2As shown in , the intersatellite laser communication terminal 100 includes an optomechanical system 10 and a processing system 20. The optomechanical system 10 is used to search and capture another intersatellite laser communication terminal 100 on another satellite in the same orbit, and to track and aim at the other intersatellite laser communication terminal 100, as well as to send optical signals to the other intersatellite laser communication terminal 100 and / or receive optical signals from the other intersatellite laser communication terminal 100. The processing system 20 is used to receive optical signals from another laser communication terminal 100, process the optical signals to parse the data carried by the optical signals, and / or process the data to be sent to another laser communication terminal 100 for modulation and transmission to the other laser communication terminal 100. In addition, the processing system 20 can also be used to implement various control strategies, manage peripheral devices, and drive various actuators of the optomechanical system 10. Figure 2 In the figure, an optical signal is shown with a dotted line, an electrical signal is shown with a solid line, and arrows point to indicate the flow direction of the optical signal or the electrical signal.

[0033] At present, the optical-mechanical system of intersatellite laser communication terminals usually adopts a coarse-fine composite detection architecture of pitch motor + azimuth motor + small-angle, high-frequency single pendulum mirror, which makes the cost of intersatellite laser communication terminals high and difficult to achieve large-scale networking.

[0034] In order to solve the above problems, in the optical-mechanical system 10 of the intersatellite laser communication terminal 100 of the present invention, a single-oscillating mirror supporting a large angle is used to perform coarse scanning tracking and fine scanning tracking in different scanning modes, thereby reducing the system software and hardware complexity and hardware cost.

[0035] like Figure 2 As shown in FIG. 1 , the optical-mechanical system 10 includes an optical path unit 110, and the optical path unit 110 includes a single pendulum mirror 32 (combined as follows: Figure 3 and Figure 4 Detailed description). The oscillating mirror 32 may be a oscillating mirror that supports large-angle swing, which may also be referred to as a large-angle oscillating mirror in this article. When the intersatellite laser communication terminal 100 enters the tracking scanning state, the oscillating mirror 32 scans the received light from another intersatellite laser communication terminal 100 in a first mode. Here, the first mode may be a coarse scanning mode with a larger scanning angle and a lower scanning frequency. In the first mode, the oscillating mirror 32 may perform a spiral scan on an uncertain area to capture the incoming received light. Here, the large scanning angle is, for example, an angle range of ±5°, and the low scanning frequency is, for example, below 100 Hz.

[0036] The optical-mechanical system 10 further includes a tracking and aiming receiving unit 120 , which determines the spot position of the received light when detecting the received light from the optical path unit 110 .

[0037] By determining the spot position of the received light, the tracking receiving unit 120 can achieve rough aiming of another intersatellite laser communication terminal 100.

[0038] In some embodiments, the tracking and aiming receiving unit 120 may include a quadrant avalanche photodiode (QAPD) detector for detecting the received light and determining the spot position of the received light. Here, the spot position of the received light may be determined, for example, by imaging the received light on the photosensitive surface of the tracking and aiming receiving unit 120.

[0039] After determining the spot position of the received light, the deflection direction of the oscillating mirror 32 is adjusted to guide the spot position to the center of the tracking and aiming receiving unit 120 (for example, to the center of the photosensitive surface of the QAPD detector). For example, the tracking and aiming receiving unit 120 or the processing system 20 can calculate the adjustment value of the deflection direction of the oscillating mirror 32 according to the deviation between the spot position and the center of the tracking and aiming receiving unit 120, and control the oscillating mirror 32 to adjust according to the adjustment value.

[0040] When the spot position of the received light is guided to the center of the tracking and aiming receiving unit 120 , the tracking and aiming receiving unit 120 can determine that another inter-satellite laser communication terminal 100 has been scanned.

[0041] Then, the single swing mirror 32 switches to the second mode for scanning. Here, the scanning angle of the second mode is smaller than that of the first mode, and the scanning frequency is higher than that of the first mode. That is, the second mode is a fine scanning mode with a small scanning angle range and a high scanning frequency, so that another intersatellite laser communication terminal 100 can be stably tracked. Here, the small scanning angle is, for example, an angle range of 3 milliradians (mrad), and the high scanning frequency is, for example, on the order of 1000 Hz.

[0042] By using the single swing mirror 32 to perform fast tracking at a small angle and high frequency, the light spot position can be locked at the center of the tracking and receiving unit 120.

[0043] The optical-mechanical system 10 of another intersatellite laser communication terminal 100 may perform similar operations until the two intersatellite laser communication terminals 100 complete scanning, tracking and locking each other. In this case, the two intersatellite laser communication terminals 100 may enter the intersatellite communication process, or the two intersatellite laser communication terminals 100 may send tracking completion signals to the ground control system respectively, and when the ground control system determines that the tracking of the two intersatellite laser communication terminals 100 has been completed, it sends a communication start signal to the two intersatellite laser communication terminals 100, so that the two intersatellite laser communication terminals 100 enter the intersatellite communication process.

[0044] In addition, the optical-mechanical system 10 may further include a communication receiving unit 130 , which detects received light from the optical path unit 110 , and transmits the received light to the processing system 20 when the received light is detected, so as to process the received light to obtain communication data carried therein.

[0045] Figure 3 1 shows a schematic structural diagram of an optical path unit 110 according to an embodiment of the present invention. Figure 4 FIG. 1 is a schematic diagram of the optical path of the optical path unit 110 according to an embodiment of the present invention. Figure 3 and Figure 4 The specific structure and working process of the optical path unit 110 and the working relationship between the optical path unit 110 and other components of the optomechanical system 10 are described.

[0046] According to the direction of light flow in the optical path unit 110 (i.e., receiving light or transmitting light), the optical path unit 110 can be further divided into a receiving optical path and a transmitting optical path, wherein the receiving optical path is used to receive receiving light from another intersatellite laser communication terminal 100, and the transmitting optical path is used to send transmitting light to another intersatellite laser communication terminal 100.

[0047] like Figure 3 and Figure 4 As shown, the receiving optical path of the optical path unit 110 includes a single pendulum mirror 32, a transceiver antenna mirror group 33, a dichroic mirror 39, a dual narrowband filter 40 and a beam splitter 41 which are arranged in sequence according to the traveling direction of the received light.

[0048] In addition, a solar filter 31 may be included before the single-oscillating mirror 32. The solar filter 31 may be located at the light aperture of the optical path unit 110 to filter out sunlight from all incoming light so as to retain only lasers from other intersatellite laser communication terminals 100 as received light.

[0049] The transceiver antenna mirror group 33 contracts the received light from the pendulum mirror 32 and transmits it to the dichroic mirror 39. Here, the transceiver antenna mirror group 33 is used to proportionally expand (i.e., expand) or reduce (i.e., contract) the diameter of the collimated input light beam, and it can have a Keplerian or Galilean lens structure, for example.

[0050] The dichroic mirror 39 transmits the received light and sends the received light to the dual narrowband filter 40. The dichroic mirror is an optical device with a filtering effect, which can selectively transmit light of a certain range of wavelengths and reflect light of another range of wavelengths. On the receiving light path, the dichroic mirror 39 can transmit the received light, and on the transmitting light path, the dichroic mirror 39 can reflect the transmitting light (as described below).

[0051] The dual narrowband filter 40 further transmits the received light and transmits the received light to the tracking receiving unit 120 via the beam splitter 41. The dual narrowband filter 40 can transmit the received light and attenuate the emitted light (if the emitted light leaks to the dual narrowband filter 40), thereby further improving the isolation between the emitted light path and the received light path.

[0052] The beam splitter 41 can split the received light into two different light beams according to a ratio, one of which is transmitted to the tracking and aiming receiving unit 120 for capture and tracking of another intersatellite laser communication terminal 100, and the other can be transmitted to the downstream communication receiving unit 130 for further parsing the communication data carried in the received light.

[0053] In some embodiments, the communication receiving unit 130 may include an avalanche photodiode (APD) detector for detecting received light and, when the received light is detected, transmitting the received light to the processing system 20 to process the received light to obtain the communication data carried therein.

[0054] In some embodiments, Figure 3 and Figure 4 As shown in the figure, the optical path unit 110 may also include a first reflector group (for example, two reflectors 42 and 43 arranged in parallel and spaced apart), the first reflector group is located between the beam splitter 41 and the communication receiving unit 130, and is used to reflect the received light so that the direction of the received light enters the communication receiving unit 130 vertically.

[0055] Here, the provision of the first reflective mirror group enables the traveling direction of the received light to be controlled to match the installation position of the communication receiving unit 130 , and makes the structure of the optical path unit 110 more compact.

[0056] In this way, the optical path unit 110 of the optical-mechanical system 10 of the present invention can detect the received light from another intersatellite laser communication terminal 100, and transmit the received light to the tracking and aiming receiving unit 120 and the communication receiving unit 130, so that the tracking and aiming receiving unit 120 can achieve locking with another intersatellite laser communication terminal 100, and enable the received light to be parsed to determine the communication data carried therein.

[0057] like Figure 3 and Figure 4 As shown, the emission light path includes an emission mirror group 37, a fast reflection mirror 38, a color separation mirror 39, a transceiver antenna mirror group 33 and a single swing mirror 32 which are arranged in sequence according to the traveling direction of the emission light.

[0058] The emission mirror group 37 can transmit the emission light emitted by the laser (not shown in the figure).

[0059] The fast reflection mirror 38 reflects the emission light from the emission mirror group 37 to the dichroic mirror 39 .

[0060] The dichroic mirror 39 reflects the emitted light to the transceiver antenna mirror group 33 , and the transceiver antenna mirror group 33 expands the emitted light reflected by the dichroic mirror 39 and transmits the expanded emitted light via the oscillating mirror 32 .

[0061] In addition, if Figure 2 As shown in , as a part of the optical-mechanical system 10, an advance aiming unit 140 may also be included. The advance aiming unit 140 may determine the advance control amount of the emission light according to the satellite broadcast data of the current satellite (i.e., the satellite where the intersatellite laser communication terminal 100 is located) and another satellite (i.e., the satellite where another intersatellite laser communication terminal 100 is located) to advance the deflection of the emission light emitted by the laser. The satellite broadcast data may at least include the coordinates and speeds of the two satellites. The coordinates and speed of the current satellite may be provided by the satellite platform of the current satellite (i.e., the components of the current satellite other than the payload), for example, and may be measured and provided by the measurement and control subsystem of the satellite platform of the current satellite. The coordinates and speed of another satellite may be provided to the ground station by the satellite platform of another satellite, and provided by the ground station to the advance aiming unit 140 of the intersatellite laser communication terminal 100 of the current satellite. More specifically, the advance aiming unit 140 can calculate the relative position change between the current satellite and another satellite based on the coordinates and speed of the current satellite and the coordinates and speed of another satellite, calculate the next position of the other satellite based on the relative position change, and determine the advance control amount based on the calculated next position so that the emission light finally emitted by the optical-mechanical system 10 points to the next position.

[0062] In some embodiments, Figure 3 and Figure 4 As shown in the figure, the optical path unit 110 may also include a second reflector group (for example, two reflectors 34 and 35 vertically spaced apart), the second reflector group is located between the transceiver antenna mirror group 33 and the color separation mirror 39, and is used to reverse the received light in the receiving light path and reverse the transmitted light in the transmitting light path.

[0063] Here, the provision of the second reflector group makes the structure of the optical path unit 110 more compact.

[0064] Note that although Figure 3 and Figure 4The first reflector group and the second reflector group are shown in the embodiment, but those skilled in the art will understand that these reflector groups are only provided to control the direction of the light path so as to make the light path unit 110 compact and reduce the occupied area. When there is no restriction on the size of the light path unit 110 or the optical-mechanical system 10, the light path unit 110 may not include such a reflector group or may include only one of the reflector groups.

[0065] exist Figure 3 and Figure 4 In the structure of the optical path unit 110 shown, each component is laid out in a flat and tiled manner, thereby lowering the center of gravity of the terminal, increasing the anti-vibration property of the terminal, and reducing the optical path deviation of the optical system introduced by vibration.

[0066] In addition, in the optical-mechanical system 10 of the present invention, each component is constructed by discrete devices, and the driving module of the laser (not shown in the figure) and the communication receiving unit 130 can be based on the laser's pigtail and the communication receiving unit 130, such as the physical structure of the photosensitive surface of the APD detector to adapt the transceiver optical system, and the consistency of the transceiver and light-transmitting circuits is completed through optical assembly and adjustment. Compared with the system in the prior art that realizes optical signal transmission based on polarized light, the system complexity is reduced and it is easier to implement.

[0067] Those skilled in the art will appreciate that the various exemplary modules and units described in conjunction with the embodiments of the present invention may be implemented as hardware devices, and where feasible, a portion thereof may be implemented in software form or a combination of the two.

[0068] The above description of the present invention is intended to enable any person of ordinary skill in the art to implement or use the present invention. Various modifications of the present invention are apparent to those of ordinary skill in the art, and the general principles defined herein may also be applied to other variations without departing from the spirit and scope of the present invention. Therefore, the present invention is not limited to the examples and designs described herein, but is consistent with the broadest range of principles and novel features disclosed herein.

Claims

1. An optical-mechanical system for an intersatellite laser communication terminal, comprising: An optical path unit, the optical path unit comprising a single pendulum mirror, the single pendulum mirror scanning the received light from another intersatellite laser communication terminal in a first mode; as well as a tracking and aiming receiving unit, wherein when the tracking and aiming receiving unit detects the received light from the optical path unit, the light spot position of the received light is determined, The optical path unit is further configured to, after determining the spot position of the received light, adjust the deflection direction of the single pendulum mirror to guide the spot position to the center of the tracking receiving unit and scan the received light in a second mode, wherein the scanning angle of the second mode is smaller than that of the first mode, and the scanning frequency of the second mode is higher than that of the first mode. The optical path unit comprises: A receiving optical path, wherein the receiving optical path comprises the single pendulum mirror, the transceiver antenna mirror group, the dichroic mirror, the dual narrowband filter and the beam splitter arranged in sequence according to the traveling direction of the received light, wherein The transmitting and receiving antenna mirror group shrinks the received light from the single swing mirror and transmits it to the dichroic mirror. The dichroic mirror transmits the received light and sends it to the dual narrow-band filter. The dual narrowband filter transmits the received light and transmits the received light to the tracking receiving unit via the beam splitter.

2. The optomechanical system of claim 1, wherein the tracking and receiving unit comprises a four-quadrant avalanche photodiode detector.

3. The optomechanical system of claim 1, wherein the optomechanical system further comprises: A communication receiving unit is located downstream of the beam splitter and is used to receive the received light from the beam splitter.

4. The optomechanical system of claim 3, wherein the communication receiving unit comprises an avalanche photodiode detector.

5. The optical-mechanical system as claimed in claim 3, wherein the optical path unit further comprises: A first reflector group, wherein the first reflector group is located between the beam splitter and the communication receiving unit and is used for reflecting the received light so that the received light enters the communication receiving unit vertically.

6. The optical-mechanical system as claimed in claim 1, wherein the optical path unit further comprises a transmitting optical path, and the transmitting optical path is used to send transmitting light to the other inter-satellite laser communication terminal.

7. The optomechanical system of claim 6, wherein the transmitting optical path comprises: The transmitting mirror group, the fast reflection mirror, the dichroic mirror, the transmitting and receiving antenna mirror group and the single swing mirror are arranged in sequence according to the traveling direction of the transmitting light, wherein The emission mirror group transmits the emission light emitted by the laser, The fast reflection mirror reflects the emitted light to the dichroic mirror, The dichroic mirror reflects the emitted light, The transmitting and receiving antenna mirror group expands the emission light reflected by the dichroic mirror, and transmits the expanded emission light through the single pendulum mirror.

8. The optical-mechanical system of claim 1, wherein the receiving optical path further comprises: A second reflector group, the second reflector group is located between the transceiver antenna mirror group and the dichroic mirror, and is used for reversing the received light in the receiving light path.

9. The optomechanical system of claim 7, wherein the transmitting optical path further comprises: A second reflector group, the second reflector group is located between the transmitting and receiving antenna mirror group and the dichroic mirror, and is used for reversing the emission light in the emission light path.

10. The optomechanical system of claim 7, further comprising: An advance aiming unit, wherein the advance aiming unit determines the advance control amount of the emission light according to the satellite broadcast data of the current satellite where the intersatellite laser communication terminal is located and the other satellite where the other intersatellite laser communication terminal is located, so as to deflect the emission light emitted by the laser in advance, wherein the satellite broadcast data at least includes the coordinates and speed of the current satellite and the other satellite.

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