Compact Kudet-type airborne laser communication optical system

Abstract

The present invention discloses a compact Kude-type airborne laser communication optical system, the device of which includes a laser emission optical subsystem and a laser receiving optical subsystem; the laser emission optical subsystem includes a laser emission processing module, a transceiver spectroscope, a control fast-reflection mirror and a laser transmission direction alignment module arranged in sequence along the laser emission direction; the laser receiving optical subsystem includes a laser transmission direction alignment module, a control fast-reflection mirror, a transceiver spectroscope and a laser receiving processing module arranged in sequence along the laser receiving direction; the laser emission processing module emits laser; the laser transmission direction alignment module aligns the laser direction and then emits laser or receives laser; the laser receiving processing module performs signal analysis on the received laser. The present invention can integrate a laser communication optical system in any airborne communication platform to simultaneously realize information reception and information transmission, improve information transmission capability, and meet the requirements of real-time information communication.

Description

Technical Field

[0001] The invention relates to the technical field of laser communications, and in particular to a compact Kuder-type airborne laser communication optical system. Background Art

[0002] Laser communication technology is one of the important technical directions in the field of high-bandwidth information transmission in space. It uses lasers emitted directionally in space as communication carriers and can be applied to various platforms such as aircraft, satellites, and ships. Airborne laser communication is used for air-to-air or air-to-ground / satellite communication, and is an important way to meet the needs of large-capacity, high-speed, and real-time data transmission between platforms. At present, the demand for the application of aerial flight platforms, mainly drones, in the military and civilian fields has increased sharply, and the complexity of missions and flight time requirements are constantly increasing, which has led to the continuous improvement of the integration requirements of airborne platforms for mission payloads.

[0003] Therefore, how to universally integrate a laser communication optical device into any airborne platform to simultaneously realize information reception and information transmission, improve information transmission capabilities, and meet the requirements of real-time information communication has become an urgent problem to be solved in the field of airborne laser communication optics. Summary of the invention

[0004] The purpose of the present invention is to overcome the shortcomings of the above-mentioned background technology and provide a compact Kuder-type airborne laser communication optical system to simultaneously realize information reception and information transmission, improve information transmission capabilities, and meet the real-time information communication requirements.

[0005] In a first aspect, a compact Kudet-type airborne laser communication optical system is provided, which is applied to a communication platform, and includes: a laser emission optical subsystem for emitting laser light externally and a laser receiving optical subsystem for receiving laser light emitted by another communication platform;

[0006] The laser emission optical subsystem includes a laser emission processing module, a transceiver spectroscope, a control fast-reflection mirror and a laser transmission direction alignment module which are sequentially arranged along the laser emission direction;

[0007] The laser receiving optical subsystem includes a laser transmission direction alignment module, a control fast reflection mirror, a transceiver beam splitter and a laser receiving processing module which are sequentially arranged along the laser receiving direction;

[0008] Among them, the laser emission processing module is used to emit laser and correct the laser emission direction; the laser transmission direction alignment module is used to align the laser transmission direction with another communication platform and then emit laser or receive laser; the laser reception processing module is used to perform signal analysis on the laser emitted by another communication platform.

[0009] In some embodiments, the laser transmission direction alignment module includes a telescope front lens group, a telescope rear lens group arranged directly to the right of the telescope front lens group, a first folding mirror arranged directly to the right of the telescope rear lens group, a second folding mirror arranged directly above the first folding mirror, a first kude mirror arranged directly to the left of the second folding mirror, a secondary beam reduction mirror arranged directly below the first kude mirror, a second kude mirror arranged directly below the secondary beam reduction mirror, a third kude mirror arranged directly to the right of the second kude mirror, and a fourth kude mirror arranged directly above the third kude mirror and arranged directly to the left of the control fast reflection mirror;

[0010] The laser transmission direction alignment module also includes a servo drive control mechanism for driving the front end lens group of the telescope, the rear end lens group of the telescope, the first folding mirror, the second folding mirror, the first Kudet mirror, the secondary beam reduction mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror to rotate.

[0011] In some embodiments, the telescope front end lens group, the telescope rear end lens group, the first folding mirror, the second folding mirror, the first Kudet mirror and the secondary reduction mirror form a pitch rotation envelope, and the pitch rotation axis of the pitch rotation envelope coincides with the center line between the first Kudet mirror and the second Kudet mirror.

[0012] In some embodiments, the telescope front end lens group, the telescope rear end lens group, the first folding mirror, the second folding mirror, the first Kudet mirror, the secondary reduction mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror form an azimuth rotation envelope, and the azimuth rotation axis of the azimuth rotation envelope passes horizontally through the center of the fourth Kudet mirror.

[0013] In some embodiments, the servo drive control mechanism drives the first folding mirror, the second folding mirror, the first Kudet mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror to rotate so that they are all set at a 45-degree angle to the laser transmission direction.

[0014] In some embodiments, the azimuth rotation axis is perpendicular to the pitch rotation axis.

[0015] In some embodiments, in the laser emission optical subsystem, the transceiver spectroscope is used to reflect the laser emitted by the laser emission processing module to the control fast reflection mirror;

[0016] In the laser receiving optical subsystem, the transceiver spectroscope is used to transmit the laser received by the control fast reflection mirror to the laser receiving processing module.

[0017] In some embodiments, the laser emission processing module includes a laser emission light source for emitting laser light, and an axis alignment fast reflection mirror for correcting the laser emission direction and reflecting the laser light to the transceiver spectroscope.

[0018] In some embodiments, the laser receiving and processing module includes a receiving beam splitter that receives the laser transmitted by the transceiver beam splitter and splits the laser into two beams, a laser analysis module that performs optical analysis on the first laser beam reflected by the receiving beam splitter, and a photoelectric conversion module that performs photoelectric conversion analysis on the second laser beam reflected by the receiving beam splitter.

[0019] In some embodiments, the laser analysis module includes a beacon light spot detection optical path for receiving the first laser beam, and a detection camera for performing laser analysis on the first laser beam transmitted by the beacon light spot detection optical path;

[0020] The photoelectric conversion module includes a receiving and detecting optical path for receiving the second laser beam, and a detector for performing photoelectric conversion on the second laser beam transmitted by the receiving and detecting optical path.

[0021] Compared with the prior art, the present invention includes a laser emission optical subsystem and a laser receiving optical subsystem in any airborne laser communication optical device. In the laser emission optical subsystem, the laser emission processing module emits laser and corrects the laser emission direction, reflects the emitted laser to the control quick reflection mirror through the transceiver spectroscope, and reflects it to the laser transmission direction alignment module through the control quick reflection mirror, and finally aligns the laser transmission direction with another communication platform through the laser transmission direction alignment module to emit laser or. In the laser receiving optical subsystem, the laser transmission direction alignment module receives the laser emitted by another communication platform, and then enters the control quick reflection mirror and the transceiver spectroscope in sequence, and finally performs signal analysis on the laser through the laser receiving processing module.

[0022] Therefore, the present invention can integrate a laser communication optical device in any airborne communication platform to simultaneously realize information reception and information transmission, improve information transmission capabilities, and meet real-time information communication requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the optical path structure of a compact Kuder-type airborne laser communication optical system of the present invention;

[0024] Figure 2 It is a schematic diagram of the envelope size of the optical path design of the present invention;

[0025] Figure 3 It is a schematic diagram of the rotation envelope of the present invention.

[0026] Figure Number:

[0027] 1. Telescope front lens group; 2. Telescope rear lens group; 3. First folding mirror; 4. Second folding mirror; 5. First Coode mirror; 6. Second beam reduction mirror; 7. Second Coode mirror; 8. Third Coode mirror; 9. Fourth Coode mirror; 10. Control quick-reflection mirror; 11. Transceiver beam splitter; 12. Axis alignment quick-reflection mirror; 13. Laser emission light source; 14. Receiving beam splitter; 15. Receiving detection optical path; 16. Detector; 17. Beacon spot detection optical path; 18. Detection camera. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] See also Figure 1 As shown, an embodiment of the present invention provides a compact Kuder-type airborne laser communication optical system, which is applied to a communication platform and includes:

[0030] A laser transmitting optical subsystem for transmitting laser light externally and a laser receiving optical subsystem for receiving laser light transmitted by another communication platform;

[0031] The laser emission optical subsystem includes a laser emission processing module, a transceiver spectroscope 11, a control fast reflection mirror 10 and a laser transmission direction alignment module which are sequentially arranged along the laser emission direction;

[0032] The laser receiving optical subsystem includes a laser transmission direction alignment module, a control fast reflection mirror 10, a transceiver beam splitter 11 and a laser receiving processing module which are sequentially arranged along the laser receiving direction;

[0033] Among them, the laser emission processing module is used to emit laser and correct the laser emission direction; the laser transmission direction alignment module is used to align the laser transmission direction with another communication platform and then emit laser or receive laser; the laser reception processing module is used to perform signal analysis on the laser emitted by another communication platform.

[0034] Optionally, in the laser emission optical subsystem, the transceiver spectroscope 11 is used to reflect the laser emitted by the laser emission processing module to the control fast reflection mirror 10;

[0035] In the laser receiving optical subsystem, the transceiver beam splitter 11 is used to transmit the laser received by the control fast reflection mirror 10 to the laser receiving processing module.

[0036] Specifically, in this embodiment, the present invention includes a laser emission optical subsystem and a laser receiving optical subsystem in any airborne laser communication optical device. In the laser emission optical subsystem, the laser emission processing module emits laser and corrects the laser emission direction, reflects the emitted laser to the control quick reflection mirror 10 through the transceiver spectroscope 11, and reflects it to the laser transmission direction alignment module through the control quick reflection mirror 10, and finally aligns the laser transmission direction with another communication platform through the laser transmission direction alignment module to emit laser. In the laser receiving optical subsystem, the laser transmission direction alignment module receives the laser emitted by another communication platform, and then enters the control quick reflection mirror 10 and the transceiver spectroscope 11 in sequence, and finally performs signal analysis on the laser through the laser receiving processing module.

[0037] Therefore, the present invention can integrate a laser communication optical device in any airborne communication platform to simultaneously realize information reception and information transmission, improve information transmission capabilities, and meet real-time information communication requirements.

[0038] Due to the current surge in demand for aerial flight platforms, mainly drones, in the military and civilian fields, and the growing complexity of missions and flight time requirements, the requirements for lightweight and miniaturized mission payloads on flight platforms are also increasing. Airborne laser communication payloads need to be as compact and lightweight as possible to improve payload adaptability while ensuring good communication performance and completing high-bandwidth data transmission.

[0039] The design of the front-end optical system for laser transmission and reception is a key link that restricts the volume, weight and performance of the payload. Traditional airborne laser communication payloads usually adopt a turret-type pod configuration, and the optical system generally adopts a multi-optical path parallel axis design. The optical path size envelope is large, and the optoelectronic / electro-optical conversion module needs to be placed inside the turret, which is not conducive to the lightweight and miniaturization of the payload, and the internal thermal control design of the payload is difficult.

[0040] Therefore, in view of the above problems, the laser transmission direction alignment module of the present invention includes a telescope front lens group 1, a telescope rear lens group 2 arranged directly to the right of the telescope front lens group 1, a first folding mirror 3 arranged directly to the right of the telescope rear lens group 2, a second folding mirror 4 arranged directly above the first folding mirror 3, a first Kude mirror 5 arranged directly to the left of the second folding mirror 4, a secondary beam reduction mirror 6 arranged directly below the first Kude mirror 5, a second Kude mirror 7 arranged directly below the secondary beam reduction mirror 6, a third Kude mirror 8 arranged directly to the right of the second Kude mirror 7, and a fourth Kude mirror 9 arranged directly above the third Kude mirror 8 and directly to the left of the control fast reflection mirror. Therefore, a compact optical path layout can be achieved to meet the requirements of lightweight and miniaturization of airborne payloads.

[0041] The laser transmission direction alignment module also includes a servo drive control mechanism for driving the telescope front end lens group 1, the telescope rear end lens group 2, the first folding mirror 3, the second folding mirror 4, the first Kudet mirror 5, the secondary beam reduction mirror 6, the second Kudet mirror 7, the third Kudet mirror 8 and the fourth Kudet mirror 9 to rotate.

[0042] The emission and reception lasers use wavelength multiplexing to achieve the common aperture and optical path of the front telescope group and the Kude mirror group. For laser reception, the receiving beam is first compressed by the transmission telescope group, and the compressed beam is subsequently processed to greatly reduce the size of the Kude reflector. After the compressed receiving beam is folded twice (the first folding mirror 3, the second folding mirror 4), it enters four small-sized Kude reflectors in turn, aligns the direction of the beam (along the negative direction of the OX axis), and is incident on the control fast reflection mirror for precise control, and then the receiving and transmitting wavelengths are split by the receiving and transmitting spectroscope, and the received light is transmitted to the laser receiving processing module. The laser emission optical path is opposite to the receiving optical path. The optical signal is modulated and emitted by the laser emission processing module. After the axis is calibrated in the laser emission direction, it is reflected by the receiving and transmitting spectroscope to the control fast reflection mirror, and then enters the Kude mirror group and the folding mirror group in turn, and finally the telescope group completes the emission.

[0043] The compression ratio of the telescope group is designed to be 5-10, and the beam diameter is constrained to within 1.6 cm. The transmitting and receiving beam splitter is designed as a wavelength filter, which transmits the receiving laser and reflects the transmitting laser, and the isolation degree for the 20nm wavelength reaches above OD5.

[0044] Compared with the parallel axis system or off-axis reflection type, the compact optical path designed by the present invention reduces the envelope of the entire optical path by more than 15% based on the same receiving aperture, as shown in the comparison in Table 1 below. Figure 2The envelope size of the optical path design of the present invention is shown in Figure 1. With a compact overall optical path and uniform lens layout, it is relatively easy to achieve the coincidence of the envelope center of gravity and the centroid design, without the need to add additional internal counterweights, and it is easy to achieve the balance of the load's moment of inertia, which is beneficial to the improvement of the control performance of the servo drive control mechanism outside the onboard load, that is, to facilitate servo control.

[0045] Table 1 Comparison of optical path envelope size design results

[0046]

[0047] Since some existing airborne laser communication devices adopt a swinging mirror or periscope optical structure: although the swinging mirror optical path is suitable for the compact spatial layout of the airborne payload, the pitch rotation angle range is severely limited; the periscope optical structure has a large three-dimensional tracking and aiming angle, but due to the asymmetric optical path layout, it is not conducive to improving the servo control accuracy under strong airborne vibration conditions.

[0048] Therefore, the present invention has achieved a compact symmetrical optical path layout, which is convenient for servo control. For a large angle range and aiming angle, the present invention adopts the following technical solutions, see Figure 3 As shown:

[0049] The telescope front end lens group 1, the telescope rear end lens group 2, the first folding mirror 3, the second folding mirror 4, the first Kudet mirror 5 and the secondary reduction mirror 6 form a pitch rotation envelope, and the pitch rotation axis of the pitch rotation envelope coincides with the center line between the first Kudet mirror 5 and the second Kudet mirror 7.

[0050] The telescope front end lens group 1, the telescope rear end lens group 2, the first folding mirror 3, the second folding mirror 4, the first Kudet mirror 5, the secondary reduction mirror 6, the second Kudet mirror 7, the third Kudet mirror 8 and the fourth Kudet mirror 9 form an azimuth rotation envelope, and the azimuth rotation axis of the azimuth rotation envelope passes horizontally through the center of the fourth Kudet mirror 9.

[0051] The azimuth rotation axis is perpendicular to the pitch rotation axis.

[0052] Specifically, in this embodiment, the azimuth rotation and pitch rotation are controlled by a servo drive control mechanism, and the servo drive control mechanism includes a torque motor, an angle measuring element, and a drive control electronics module. Taking pitch rotation as an example, all elements in the pitch rotation envelope are fixedly linked to the designed structural support, and a bearing is installed at one end of the pitch rotation envelope passing through the pitch rotation axis. The pitch torque motor is fixedly connected to the bearing and can control the bearing to drive the entire pitch rotation envelope to rotate. A precision angle measuring element is installed at the other end of the pitch rotation envelope passing through the rotation axis. The drive control electronics module controls the torque motor to rotate to the required angle position by collecting the angle information measured by the angle measuring element to achieve precise pitch pointing. The principle of azimuth rotation is the same as that of pitch. It should be noted that no matter how the laser communication optical system rotates, the two axis systems of the azimuth rotation axis and the pitch rotation axis remain vertically orthogonal, so that decoupling control in two directions can be achieved.

[0053] The rotation axis is designed as follows: The rotation envelope is as follows Figure 3 As shown, the pitch rotation envelope ① includes all the optical elements in the small box in the figure, the pitch rotation axis ③ coincides with the center line of the first Kude mirror 5 and the second Kude mirror 7 (parallel to the OY axis in the coordinate system in the figure), the azimuth rotation envelope ② includes all the optical elements in the large box in the figure (including the pitch envelope), and the azimuth rotation axis ④ passes through the center of the fourth Kude mirror 9 and is parallel to the OX axis. Through the design of the rotation envelope, no matter how the azimuth pitch axis rotates, that is, when the tracking and aiming axis points to any direction, the transmission direction of the transmitting / receiving light between the fourth Kude mirror 9 and the control fast-reflection mirror 10 after passing through the Kude mirror group is aligned with the prescribed direction (the transmitting light is along the positive direction of the OX axis, and the receiving light is along the negative direction of the OX axis); that is, during the communication process between the two platforms, the pitch rotation envelope and the azimuth rotation envelope rotate continuously in real time to change the pitch angle and azimuth angle of one communication platform, so that the transmitting / receiving laser direction is aligned with the distant target (the other communication platform) in real time. However, since the pointing error caused by factors such as the vibration of the aircraft platform cannot be completely offset by controlling the rotation of the device, the remaining pointing error is offset by controlling the quick-reflection mirror 10 to rotate quickly and at a small angle. Therefore, the small pointing error caused by factors such as platform vibration will be controlled, adjusted and corrected by controlling the quick-reflection mirror 10.

[0054] Therefore, after adopting the optical path of the present invention, the load tracking angle range is large and is not limited by the optical path design. The azimuth rotation angle range is n×360 o , pitch rotation angle range +20 o ~-100 o , realizing a large pitch rotation angle range for the payload's beam tracking and aiming, meeting the requirements of overhead tracking and aiming.

[0055] Optionally, the servo drive control mechanism drives the first folding mirror 3, the second folding mirror 4, the first Kudet mirror 5, the second Kudet mirror 7, the third Kudet mirror 8 and the fourth Kudet mirror 9 to rotate so that they are all set at an angle of 45 degrees to the laser transmission direction.

[0056] All the folding mirrors and Coode mirrors are placed at an angle of 45 degrees to the incident or outgoing light, so that when the laser transmission direction alignment module is rotated and pointed in different directions, the direction of the incident / outgoing light (from the fourth Coode mirror 9 to the control fast reflection mirror 10, or from the control fast reflection mirror 10 to the fourth Coode mirror 9) before entering the split light path remains relatively fixed, that is, the transmitting / receiving laser direction is aligned with the distant target in real time.

[0057] Optionally, the laser emission processing module includes a laser emission light source 13 for emitting laser light, and an axis-correcting quick-reflection mirror 12 for correcting the laser emission direction and reflecting the laser light to the transceiver spectroscope.

[0058] Specifically, in this embodiment, the output light with modulation information is emitted by the laser emitting light source 13, and enters the Coode mirror group after being reflected by the axis alignment fast reflection mirror 12 and the transceiver spectroscope 11 in sequence. The direction of the axis alignment fast reflection mirror is calibrated before use and is no longer adjusted during normal operation.

[0059] Optionally, the laser receiving and processing module includes a receiving beam splitter 14 that receives the laser transmitted by the transceiver spectroscope 11 and splits the laser into two beams, a laser analysis module that performs optical analysis on the first laser beam reflected by the receiving beam splitter 14, and a photoelectric conversion module that performs photoelectric conversion analysis on the second laser beam reflected by the receiving beam splitter 14.

[0060] Optionally, the laser analysis module includes a beacon spot detection optical path 17 for receiving the first laser beam, and a detection camera 18 for performing laser analysis on the first laser beam transmitted by the beacon spot detection optical path 17;

[0061] The photoelectric conversion module includes a receiving detection optical path 15 for receiving the second laser beam, and a detector 16 for performing photoelectric conversion on the second laser beam transmitted by the receiving detection optical path 15 .

[0062] Specifically, in this embodiment, the receiving beam splitter reflects 10% of the received light energy into the beacon spot detection optical path, and the detection camera performs spot detection, centroid and deflection measurement. The receiving beam splitter transmits 90% of the received light energy into the receiving detection optical path, and the detector performs photoelectric conversion and sends it to the back-end demodulation circuit for processing.

[0063] At the same time, the optical path design allows the transmitting / receiving light directions to be relatively aligned, and the transmitting / receiving back end (position 13 and position 16) can be derived using coupled optical fibers. Therefore, the high-power laser light source, optical amplifier, and signal processing circuit can be placed separately in a chassis outside the payload, greatly reducing the power consumption inside the payload and achieving the purpose of facilitating thermal control.

[0064] It should be noted that the beacon light detection optical path is used to project the light spot onto the target surface of the detection camera after focusing and filtering the 10% energy of the received laser after splitting, so as to facilitate the subsequent beacon light spot imaging display, deviation measurement calculation and other processing. The beacon light detection optical path needs to be used in conjunction with the front-end telescope optical path, and the total focal length generally needs to reach 800mm to 1000mm or more.

[0065] The receiving detection optical path is the same as the beacon spot detection optical path mentioned above. Through convergence, filtering and other operations, 90% of the energy of the receiving laser is collected on the APD target surface for subsequent photoelectric conversion, signal demodulation and other processing. The total focal length of this optical path is generally around 150mm to 300mm.

[0066] Therefore, the present invention adopts the Couder optical path as the basic optical path configuration, optimizes the layout of the telescope group, multiple reflectors and Couder mirrors, fast reflector mirrors and splitter optical paths, and realizes a compact and symmetrical laser communication optical terminal with a large rotation range to meet the installation requirements of airborne platforms. That is, under the premise of ensuring a large angle range and aiming angle, a compact optical path layout is realized to meet the requirements of light and miniaturized airborne payloads, while achieving the purpose of easy thermal control design implementation and convenient servo control.

[0067] In the description of the present invention, it should be noted that the terms "upper", "lower", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as a limitation on the present invention. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0068] It should be noted that, in the present invention, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0069] The above description is only a specific embodiment of the present invention, so that those skilled in the art can understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but should conform to the widest scope consistent with the principles and novel features invented herein.

Claims

1. A compact Kudet-type airborne laser communication optical system, applied to a communication platform, characterized in that: include: A laser transmitting optical subsystem for transmitting laser light externally and a laser receiving optical subsystem for receiving laser light transmitted by another communication platform; The laser emission optical subsystem includes a laser emission processing module, a transceiver spectroscope, a control fast-reflection mirror and a laser transmission direction alignment module which are sequentially arranged along the laser emission direction; The laser receiving optical subsystem includes a laser transmission direction alignment module, a control fast reflection mirror, a transceiver beam splitter and a laser receiving processing module which are sequentially arranged along the laser receiving direction; The laser emission processing module is used to emit laser and correct the laser emission direction; the laser transmission direction alignment module is used to align the laser transmission direction with another communication platform and then emit laser or receive laser; the laser reception processing module is used to perform signal analysis on the laser emitted by another communication platform; The laser transmission direction alignment module includes a telescope front lens group, a telescope rear lens group arranged directly to the right of the telescope front lens group, a first folding mirror arranged directly to the right of the telescope rear lens group, a second folding mirror arranged directly above the first folding mirror, a first kude mirror arranged directly to the left of the second folding mirror, a secondary beam reduction mirror arranged directly below the first kude mirror, a second kude mirror arranged directly below the secondary beam reduction mirror, a third kude mirror arranged directly to the right of the second kude mirror, and a fourth kude mirror arranged directly above the third kude mirror and arranged directly to the left of the control fast reflection mirror; The laser transmission direction alignment module also includes a servo drive control mechanism for driving the front end lens group of the telescope, the rear end lens group of the telescope, the first folding mirror, the second folding mirror, the first Kudet mirror, the secondary beam reduction mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror to rotate.

2. The compact Kuder airborne laser communication optical system according to claim 1, characterized in that: The telescope front end lens group, the telescope rear end lens group, the first folding mirror, the second folding mirror, the first Kudet mirror and the secondary reduction mirror form a pitch rotation envelope, and the pitch rotation axis of the pitch rotation envelope coincides with the center line between the first Kudet mirror and the second Kudet mirror.

3. The compact Kuder airborne laser communication optical system according to claim 2, characterized in that: The telescope front end lens group, the telescope rear end lens group, the first folding mirror, the second folding mirror, the first Kudet mirror, the secondary beam reduction mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror form an azimuth rotation envelope, and the azimuth rotation axis of the azimuth rotation envelope passes horizontally through the center of the fourth Kudet mirror.

4. The compact Kuder airborne laser communication optical system according to claim 3, characterized in that: The azimuth rotation axis is perpendicular to the pitch rotation axis.

5. The compact Kuder airborne laser communication optical system according to claim 1, characterized in that: The servo drive control mechanism drives the first folding mirror, the second folding mirror, the first Kudet mirror, the second Kudet mirror, the third Kudet mirror and the fourth Kudet mirror to rotate so that they are all arranged at an angle of 45 degrees to the laser transmission direction.

6. The compact Kuder airborne laser communication optical system according to claim 1, characterized in that: In the laser emission optical subsystem, the transceiver spectroscope is used to reflect the laser emitted by the laser emission processing module to the control fast reflection mirror; In the laser receiving optical subsystem, the transceiver spectroscope is used to transmit the laser received by the control fast reflection mirror to the laser receiving processing module.

7. The compact Kuder airborne laser communication optical system according to claim 1, characterized in that: The laser emission processing module comprises a laser emission light source for emitting laser light, and an axis correction quick reflection mirror for correcting the laser emission direction and reflecting the laser light to the transceiver spectroscope.

8. The compact Kuder airborne laser communication optical system according to claim 1, characterized in that: The laser receiving and processing module includes a receiving beam splitter that receives the laser transmitted by the transceiver beam splitter and splits the laser into two beams, a laser analysis module that performs optical analysis on the first laser beam reflected by the receiving beam splitter, and a photoelectric conversion module that performs photoelectric conversion analysis on the second laser beam reflected by the receiving beam splitter.

9. The compact Kuder airborne laser communication optical system according to claim 8, characterized in that: The laser analysis module includes a beacon light spot detection optical path for receiving the first laser beam, and a detection camera for performing laser analysis on the first laser beam transmitted by the beacon light spot detection optical path; The photoelectric conversion module includes a receiving and detecting optical path for receiving the second laser beam, and a detector for performing photoelectric conversion on the second laser beam transmitted by the receiving and detecting optical path.

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