Inter-satellite laser communication link simulation device based on energy feature inversion

Abstract

The invention discloses an inter-satellite laser communication link simulation device based on energy feature inversion. Belongs to the technical field of satellite laser communication, particularly relates to the technical field of inter-satellite laser communication link simulation devices based on energy feature inversion, and provides an inter-satellite laser communication link simulation device based on energy feature inversion. And an equivalent energy environment is constructed in the system, and accurate testing of the communication capability of the terminal machine is realized. The device comprises a transmitting optical transceiver, a receiving optical transceiver, a communication attenuation simulation module and a computer, the transmitting optical transmitter and receiver transmits a communication light beam along the communication attenuation light path A or the communication attenuation light path B, and the communication light beam is transmitted into the receiving optical transmitter and receiver after being subjected to dynamic simulation communication attenuation by the communication attenuation simulation module; the computer is used for controlling the communication attenuation simulation module to dynamically simulate communication attenuation.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite laser communication, and in particular to the technical field of inter-satellite laser communication link simulation devices based on energy characteristic inversion. Background Art

[0002] Satellite laser communication, which uses lasers as a transmission medium, is a current focus of research both domestically and internationally. It boasts numerous advantages, including high information capacity, low power consumption, light weight, and excellent confidentiality. Before intersatellite laser communication systems can be deployed in orbit, a series of ground-based operational tests are required. These tests must closely simulate the actual intersatellite operating environment. This requires the development of an intersatellite laser communication link simulator to verify the communication capabilities of the laser communication payload within the confined space of a laboratory.

[0003] Currently, there are several main types of intersatellite laser communication link simulation devices. The first is to conduct laser communication experiments at actual ground distances. The second is to obtain the far-field light field distribution through optical Fourier transform and increase the simulated distance through cascade amplification. The third is that the distance simulated by the far-field light field link is related to the size of the receiving aperture. Using nanoprobes as receivers allows the simulation device to simulate longer distances. All of the above methods can simulate intersatellite laser communication links, but each has its shortcomings. Testing optical terminals at actual ground distances is affected by atmospheric turbulence. The method of simulating the link using Fourier transform plus cascade amplification may also amplify the aberrations of the communication light. The structure of the nanoprobe link simulation device is relatively complex, not conducive to operation, and is relatively expensive.

[0004] The Chinese invention patent "Ground Detection System for Capture and Link Establishment of Inter-orbital Laser Communication" (CN117811657A) uses a micro-aperture diaphragm to limit the energy of the outgoing communication light to simulate the capture process of inter-orbital laser communication. However, the device described in the patent lacks the ability to simulate dynamic links. Summary of the Invention

[0005] To address the challenges faced by intersatellite laser communication link simulation devices, such as the effects of atmospheric turbulence, large aberrations in communication light, complex structures, inconvenient operation, and relatively high costs, the present invention provides an intersatellite laser communication link simulation device based on energy signature inversion. Based on the energy signature of long-distance links received by intersatellite in-orbit communication optical terminals, an equivalent energy environment is constructed within the system to accurately test the terminal's communication capabilities.

[0006] The device comprises:

[0007] Transmitting optical terminal, receiving optical terminal, communication attenuation simulation module and computer;

[0008] The transmitting optical terminal transmits a communication light beam along the communication attenuation optical path A or the communication attenuation optical path B. After the communication attenuation is dynamically simulated by the communication attenuation simulation module, the light beam is emitted into the receiving optical terminal.

[0009] The computer is used to control the communication attenuation simulation module to dynamically simulate communication attenuation, specifically:

[0010] S1, the communication attenuation simulation module sends the incident light spot position information to the computer;

[0011] S2. The computer uses the formula: Calculate the light intensity I received by the receiving optical terminal when there is a pointing error in the inter-satellite laser communication on orbit z , where z represents the communication distance between the transmitting optical terminal and the receiving optical terminal, (x, y) represents the position coordinates of the incident light spot, ω(z) represents the beam radius of the Gaussian beam at the propagation distance z, λ represents the wavelength of the communication beam, (x1, y1) represents the position coordinates within the aperture of the transmitting optical terminal, circ(x′, y′) represents the aperture function of the receiving optical terminal, (x′, y′) represents the position coordinates within the aperture of the receiving optical terminal, and A represents the amplitude of the communication transmitted light;

[0012] S3. Computer Feedback I z To the communication attenuation simulation module;

[0013] S4, the communication attenuation simulation module attenuates the intensity of the received communication beam to I z , and obtain the attenuated communication beam.

[0014] Further, the communication attenuation simulation module includes: a communication attenuation simulation module A and a communication attenuation simulation module B;

[0015] The optical terminal A to be tested and the optical terminal B to be tested are both used to represent the transmitting optical terminal or the receiving optical terminal;

[0016] The communication attenuation optical path A includes: an optical terminal to be tested A, a telescope antenna A, a communication attenuation simulation module A, a fast reflection mirror A, a telescope antenna B and an optical terminal to be tested B;

[0017] In the communication attenuation optical path A, the communication beam is emitted from the optical terminal A to be tested, passes through the telescope antenna A and wavelength splitter A in sequence, and then enters the communication attenuation simulation module A for dynamic attenuation. After exiting the communication attenuation simulation module A, the attenuated communication beam passes through the fast reflector A and telescope antenna B in sequence before entering the optical terminal B to be tested.

[0018] The communication attenuation optical path B includes: an optical terminal to be tested B, a telescope antenna B, a communication attenuation simulation module B, a fast reflection mirror B, a wavelength splitter A and a telescope antenna A;

[0019] In the communication attenuation optical path B, after the communication light beam is emitted from the optical terminal B to be tested, it passes through the telescope antenna B and the wavelength splitter B in sequence, and then enters the communication attenuation simulation module B for dynamic attenuation. After the attenuated communication light beam is emitted from the communication attenuation simulation module B, it passes through the fast reflector B and the telescope antenna A in sequence, and then enters the optical terminal A to be tested.

[0020] Furthermore, the communication attenuation simulation module A includes: an energy beam splitter A, an infrared camera collimating lens A, an infrared camera A, a controllable attenuation A, a micro-aperture diaphragm collimating lens A and a micro-aperture diaphragm A;

[0021] In the communication attenuation simulation module A, the incident light beam is split into two light beams at a ratio of 1:9 by the energy beam splitter A. One light beam passes through the infrared camera collimator lens A and enters the infrared camera A; the other light beam passes through the controllable attenuator A, the microaperture diaphragm collimator lens A and the microaperture diaphragm A and then exits.

[0022] Furthermore, the communication attenuation simulation module B includes: an energy beam splitter B, an infrared camera collimating lens B, an infrared camera B, a controllable attenuation B, a micro-aperture diaphragm collimating lens B and a micro-aperture diaphragm B;

[0023] In the communication attenuation simulation module B, the incident light beam is split into two beams at a ratio of 1:9 by the energy beam splitter B. One beam passes through the infrared camera collimator lens B and then enters the infrared camera B to obtain the position information of the incident light spot; the other beam passes through the controllable attenuator B, the microaperture diaphragm collimator lens B, and the microaperture diaphragm B and then exits.

[0024] Furthermore, the computer is connected to the infrared camera A, the infrared camera B, the quick-reflection mirror A and the quick-reflection mirror B respectively;

[0025] The computer receives the incident light spot position information sent by infrared camera A and infrared camera B respectively, and sends I z Give controllable attenuation A and controllable attenuation B;

[0026] Both fast mirror A and fast mirror B are used to simulate satellite micro-vibration. Specifically, the computer sends NASDA vibration spectrum to fast mirror A and fast mirror B respectively, and performs disturbance processing on the communication attenuation light beams entering fast mirror A and fast mirror B.

[0027] Furthermore, the aperture of micro-aperture stop A and micro-aperture stop B is calculated by the formula: d=f·θ, wherein d represents the aperture of micro-aperture stop A or micro-aperture stop B, f represents the focal length of the collimating lens of micro-aperture stop A or micro-aperture stop B, and θ represents the beam divergence angle of the emitted light beam.

[0028] Furthermore, the wavelength splitter A, the wavelength splitter B, the energy splitter A, the energy splitter, the quick mirror A and the quick mirror B are all placed at an angle of 45° to the horizontal plane.

[0029] Furthermore, the device further comprises: an azimuth-tilt platform A and an azimuth-tilt platform B;

[0030] Azimuth and elevation platform A is used to connect to the optical terminal A to be tested;

[0031] Azimuth and tilt platform B is used to connect to the optical terminal B to be tested.

[0032] The beneficial effects of the present invention are:

[0033] The device described in the present invention combines controllable attenuation with a micro-aperture aperture, and acts as a link attenuation simulation device to regulate the light field energy of the incident communication light, so that the communication light passing through the communication attenuation simulation module reaches the far-field state. It has high accuracy and stability, strong intersatellite link dynamic simulation capabilities, and can flexibly simulate links of different communication distances and energy changes during communication. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is a structural diagram of the device according to the present invention;

[0035] Figure 2 Schematic diagram of far-field light field sampling by the optical receiving terminal of the present invention, (a) shows a schematic diagram of the receiving aperture and the far-field light field spot; (b) shows a schematic diagram of the light intensity received within the receiving aperture and the far-field light intensity distribution, wherein the horizontal axis represents the far-field light field spot and the vertical axis represents the light intensity;

[0036] 101-Optical terminal to be tested A, 102-Telescopic antenna A, 103-Wavelength spectrometer A, 104-Energy spectrometer A, 105-Infrared camera collimating lens A, 106-Infrared camera A, 107-Controllable attenuator A, 108-Micro-aperture diaphragm collimating lens A, 109-Micro-aperture diaphragm A, 110-Fast reflex mirror A, 111-Azimuth and pitching platform A, 201-Optical terminal to be tested B, 202-Telescopic antenna B, 203-Wavelength spectrometer B, 204-Energy spectrometer B, 205-Infrared camera collimating lens B, 206-Infrared camera B, 207-Controllable attenuator B, 208-Micro-aperture diaphragm collimating lens B, 209-Micro-aperture diaphragm B, 210-Fast reflex mirror B and 211-Azimuth and pitching platform B. DETAILED DESCRIPTION

[0037] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0038] Example 1

[0039] This embodiment provides an intersatellite laser communication link simulation device based on energy characteristic inversion, which can realize dynamic simulation of long-distance intersatellite links, including simulation of the capture field of view angle of the optical terminal and the energy characteristics of the optical terminal's two-way communication process.

[0040] like Figure 1 As shown, the device includes: a transmitting optical terminal, a receiving optical terminal, a communication attenuation simulation module and a computer;

[0041] The transmitting optical terminal transmits a communication light beam along the communication attenuation optical path A or the communication attenuation optical path B. After the communication attenuation is dynamically simulated by the communication attenuation simulation module, the light beam is emitted into the receiving optical terminal.

[0042] like Figure 2 As shown, when a pointing error exists in the transmitting optical terminal, the energy (light intensity) received within the receiving aperture of the receiving optical terminal is equivalent to the energy sampling performed by the receiving optical terminal within the beam divergence angle range (light spot) of the communication light emitted by the transmitting optical terminal. The amount of energy received by the receiving optical terminal varies with different error angles. Based on the principle that the energy variation of the communication light of the device described in the present invention is consistent with the energy variation of the on-orbit inter-satellite laser communication under corresponding pointing error conditions, the computer calculates the energy that the receiving terminal can receive when the on-orbit inter-satellite laser communication has a pointing error. This is used to control the communication attenuation simulation module to dynamically simulate communication attenuation. Specifically,

[0043] S1, the communication attenuation simulation module sends the incident light spot position information to the computer;

[0044] S2. The computer uses the formula: Calculate the light intensity I received by the receiving optical terminal when there is a pointing error in the inter-satellite laser communication on orbit z , where z represents the communication distance between the transmitting optical terminal and the receiving optical terminal, (x, y) represents the position coordinates of the incident light spot, ω(z) represents the beam radius of the Gaussian beam at the propagation distance z, λ represents the wavelength of the communication beam, (x1, y1) represents the position coordinates within the aperture of the transmitting optical terminal, circ(x′, y′) represents the aperture function of the receiving optical terminal, (x′, y′) represents the position coordinates within the aperture of the receiving optical terminal, and A represents the amplitude of the communication transmitted light;

[0045] S3. Computer Feedback I z To the communication attenuation simulation module;

[0046] S4, the communication attenuation simulation module attenuates the intensity of the received communication beam to I z , and obtain the attenuated communication beam.

[0047] In the device described herein, the communication light emitted by the optical terminal under test undergoes a Fourier transform after passing through a Fourier lens (a micro-aperture diaphragm collimator). Based on the Fresnel diffraction law, the energy distribution of the light field at the focal point of the optical system after the Fourier transform is determined. This allows the determination of the light intensity of the transmitting optical terminal under test through the micro-aperture diaphragm at different pointing errors. The communication attenuation simulation module uses a controllable optical attenuator combined with the micro-aperture diaphragm to regulate the incident light intensity. The controllable attenuator and micro-aperture diaphragm regulate the incident light intensity to ensure that the emitted light intensity is consistent with the light intensity actually received by the on-orbit receiving optical terminal.

[0048] The communication attenuation simulation module includes: a communication attenuation simulation module A and a communication attenuation simulation module B;

[0049] The optical terminal A101 to be tested and the optical terminal B201 to be tested are both used to represent the transmitting optical terminal or the receiving optical terminal;

[0050] The transmitting and receiving communication light wavelengths of the optical terminal A101 to be tested are 1560nm band and 1540nm band respectively, and the transmitting and receiving communication light wavelengths of the optical terminal B201 to be tested are 1540nm band and 1560nm band respectively.

[0051] Example 2: This example further limits Example 1.

[0052] The communication attenuation optical path A includes: an optical terminal to be tested A101, a telescopic antenna A102, a communication attenuation simulation module A, a fast reflection mirror A110, a telescopic antenna B202 and an optical terminal to be tested B201;

[0053] In the communication attenuation optical path A, the communication beam is emitted by the optical terminal A101 to be tested, passes through the telescope antenna A102 and the wavelength splitter A103 in sequence, and then enters the communication attenuation simulation module A for dynamic attenuation. After exiting the communication attenuation simulation module A, the attenuated communication beam passes through the fast reflection mirror A110 and the telescope antenna B202 in sequence before entering the optical terminal B201 to be tested.

[0054] The communication attenuation simulation module A includes: an energy beam splitter A104, an infrared camera collimating lens A105, an infrared camera A106, a controllable attenuation A107, a micro-aperture diaphragm collimating lens A108 and a micro-aperture diaphragm A109;

[0055] In the communication attenuation simulation module A, the incident light beam is split into two light beams at a ratio of 1:9 by the energy splitter A104. One light beam passes through the infrared camera collimating lens A105 and then enters the infrared camera A106; the other light beam passes through the controllable attenuation A107, the micro-aperture diaphragm collimating lens A108 and the micro-aperture diaphragm A109 and then exits.

[0056] Example 3: This example further limits Example 1.

[0057] The communication attenuation optical path B includes: an optical terminal to be tested B201, a telescope antenna B202, a communication attenuation simulation module B, a fast reflection mirror B210, a wavelength splitter A103 and a telescope antenna A102;

[0058] In the communication attenuation optical path B, after the communication light beam is emitted from the optical terminal to be tested B201, it passes through the telescope antenna B202 and the wavelength splitter B203 in sequence, and then enters the communication attenuation simulation module B for dynamic attenuation. After the attenuated communication light beam is emitted from the communication attenuation simulation module B, it passes through the fast reflection mirror B210 and the telescope antenna A102 in sequence, and then enters the optical terminal to be tested A101.

[0059] The communication attenuation simulation module B includes: an energy beam splitter B204, an infrared camera collimating lens B205, an infrared camera B206, a controllable attenuation B207, a micro-aperture diaphragm collimating lens B208, and a micro-aperture diaphragm B209;

[0060] In the communication attenuation simulation module B, the incident light beam is split into two light beams at a ratio of 1:9 by the energy splitter B204. One light beam passes through the infrared camera collimating lens B205 and then enters the infrared camera B206 to obtain the position information of the incident light spot; the other light beam passes through the controllable attenuation B207, the micro-aperture diaphragm collimating lens B208 and the micro-aperture diaphragm B209 and then exits.

[0061] Example 4: This example further limits Examples 1, 2 and 3.

[0062] The computer is respectively connected to the infrared camera A106, the infrared camera B206, the quick-reflection mirror A110 and the quick-reflection mirror B210 for communication;

[0063] The computer receives the incident light spot position information sent by infrared camera A106 and infrared camera B206 respectively, and sends I z Controllable attenuation A107 and B207 are fed back to controllable attenuation modules. These modules provide corresponding attenuation values when pointing errors occur in the transmitting optical terminal, ensuring that the communication light emitted by the link simulator matches the energy received by the actual on-orbit receiving optical terminal. As the incident communication light passes through the long-distance link simulation system, the communication attenuation simulation module adjusts the energy of the emitted light in real time based on the incident angle. This energy variation simulates the energy jitter caused by tracking and pointing errors in actual intersatellite laser communications.

[0064] Laser communication on-orbit microvibrations are minute vibrations caused by various factors during satellite orbital motion. These vibrations can affect the performance of laser communication systems, leading to a decrease in communication quality or even interruption. In the present invention, both quick-reflection mirrors A110 and B210 are used to simulate satellite microvibrations. Specifically, a computer transmits a NASDA vibration spectrum to quick-reflection mirrors A110 and B210, respectively, perturbing the attenuated communication light beams incident on quick-reflection mirrors A110 and B210. The inverted vibration spectrum generated by quick-reflection mirrors A110 and B210 perturbs the transmitted communication light path, achieving laser communication microvibration simulation and providing a realistic on-orbit environment for the optical terminal under test.

[0065] When the quick mirror A110 and the quick mirror B210 do not perform the perturbation process, they function as reflection mirrors to perform a folding process on the incident light beam.

[0066] If the aperture of the micro-aperture diaphragm is on the incident light axis, all the communication light emitted by the transmitting optical terminal can pass through the micro-aperture diaphragm. Under this micro-aperture diaphragm aperture, the simulation of the capture field of view angle of inter-satellite laser communication can be realized.

[0067] The aperture of microaperture diaphragm A109 and microaperture diaphragm B209 is calculated by the formula: d=f·θ, where d represents the aperture of microaperture diaphragm A109 or microaperture diaphragm B209, f represents the focal length of the collimating lens of microaperture diaphragm A109 or microaperture diaphragm B209, and θ represents the beam divergence angle of the emitted light beam.

[0068] The wavelength splitter A103, the wavelength splitter B203, the energy splitter A104, the energy splitter B204, the quick reflector A110 and the quick reflector B210 are all placed at an angle of 45° to the horizontal plane.

[0069] like Figure 1 As shown, the device further includes: an azimuth-tilt platform A111 and an azimuth-tilt platform B211;

[0070] The azimuth and tilting platform A111 is used to connect to the optical terminal A101 to be tested;

[0071] The azimuth and tilt platform B211 is used to connect to the optical terminal B201 to be tested.

Claims

1. An intersatellite laser communication link simulation device based on energy characteristic inversion, characterized in that: The device comprises: a transmitting optical terminal, a receiving optical terminal, a communication attenuation simulation module and a computer; The transmitting optical terminal transmits a communication light beam along the communication attenuation optical path A or the communication attenuation optical path B. After the communication attenuation is dynamically simulated by the communication attenuation simulation module, the light beam is emitted into the receiving optical terminal. The computer is used to control the communication attenuation simulation module to dynamically simulate communication attenuation, specifically: S1, the communication attenuation simulation module sends the incident light spot position information to the computer; S2. The computer uses the formula: Calculate the light intensity I received by the receiving optical terminal when there is a pointing error in the inter-satellite laser communication on orbit z , where z represents the communication distance between the transmitting optical terminal and the receiving optical terminal, (x, y) represents the position coordinates of the incident light spot, ω(z) represents the beam radius of the Gaussian beam at the propagation distance z, λ represents the wavelength of the communication beam, (x1, y1) represents the position coordinates within the aperture of the transmitting optical terminal, circ(x′, y′) represents the aperture function of the receiving optical terminal, (x′, y′) represents the position coordinates within the aperture of the receiving optical terminal, and A represents the amplitude of the communication transmitted light; S3. Computer Feedback I z To the communication attenuation simulation module; S4, the communication attenuation simulation module attenuates the intensity of the received communication beam to I z , and obtain the attenuated communication beam.

2. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 1 is characterized in that: The communication attenuation simulation module includes: a communication attenuation simulation module A and a communication attenuation simulation module B; The optical terminal A (101) to be tested and the optical terminal B (201) to be tested are both used to represent a transmitting optical terminal or a receiving optical terminal; The communication attenuation optical path A comprises: an optical terminal to be tested A (101), a telescopic antenna A (102), a communication attenuation simulation module A, a fast reflection mirror A (110), a telescopic antenna B (202) and an optical terminal to be tested B (201); In the communication attenuation optical path A, after the communication light beam is emitted from the optical terminal A (101) to be tested, it passes through the telescope antenna A (102) and the wavelength splitter A (103) in sequence, and then enters the communication attenuation simulation module A for dynamic attenuation. After the attenuated communication light beam is emitted from the communication attenuation simulation module A, it passes through the fast reflection mirror A (110) and the telescope antenna B (202) in sequence, and then enters the optical terminal B (201) to be tested. The communication attenuation optical path B comprises: an optical terminal to be tested B (201), a telescopic antenna B (202), a communication attenuation simulation module B, a fast reflection mirror B (210), a wavelength splitter A (103) and a telescopic antenna A (102); In the communication attenuation optical path B, after the communication light beam is emitted from the optical terminal B (201) to be tested, it passes through the telescope antenna B (202) and the wavelength splitter B (203) in sequence, and then enters the communication attenuation simulation module B for dynamic attenuation. After the attenuated communication light beam is emitted from the communication attenuation simulation module B, it passes through the fast reflection mirror B (210) and the telescope antenna A (102) in sequence, and then enters the optical terminal A (101) to be tested.

3. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 2, characterized in that: The communication attenuation simulation module A includes: an energy beam splitter A (104), an infrared camera collimating lens A (105), an infrared camera A (106), a controllable attenuation A (107), a micro-aperture diaphragm collimating lens A (108) and a micro-aperture diaphragm A (109); In the communication attenuation simulation module A, the incident light beam is split into two light beams at a ratio of 1:9 by the energy beam splitter A (104). One light beam passes through the infrared camera collimating lens A (105) and then enters the infrared camera A (106); the other light beam passes through the controllable attenuation A (107), the micro-aperture diaphragm collimating lens A (108) and the micro-aperture diaphragm A (109) and then exits.

4. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 3 is characterized in that: The communication attenuation simulation module B includes: an energy beam splitter B (204), an infrared camera collimating lens B (205), an infrared camera B (206), a controllable attenuation B (207), a micro-aperture diaphragm collimating lens B (208) and a micro-aperture diaphragm B (209); In the communication attenuation simulation module B, the incident light beam is split into two light beams at a ratio of 1:9 by the energy beam splitter B (204). One light beam passes through the infrared camera collimating lens B (205) and then enters the infrared camera B (206) to obtain the position information of the incident light spot; the other light beam passes through the controllable attenuation B (207), the micro-aperture diaphragm collimating lens B (208) and the micro-aperture diaphragm B (209) and then exits.

5. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 4 is characterized in that: The computer is in communication connection with the infrared camera A (106), the infrared camera B (206), the quick-reflection mirror A (110) and the quick-reflection mirror B (210) respectively; The computer receives the incident light spot position information sent by infrared camera A (106) and infrared camera B (206), and sends I z Give controllable attenuation A (107) and controllable attenuation B (207); The quick-reflection mirror A (110) and the quick-reflection mirror B (210) are both used to simulate satellite micro-vibration. Specifically, a computer sends NASDA vibration spectra to the quick-reflection mirror A (110) and the quick-reflection mirror B (210), respectively, and performs disturbance processing on the communication attenuated light beams incident on the quick-reflection mirror A (110) and the quick-reflection mirror B (210).

6. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 5, characterized in that: The aperture of the micro-aperture stop A (109) and the micro-aperture stop B (209) is calculated by the formula: d = f·θ, wherein d represents the aperture of the micro-aperture stop A (109) or the micro-aperture stop B (209), f represents the focal length of the collimating lens of the micro-aperture stop A (109) or the micro-aperture stop B (209), and θ represents the beam divergence angle of the emitted light beam.

7. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 6, characterized in that: The wavelength splitter A (103), the wavelength splitter B (203), the energy splitter A (104), the energy splitter B (204), the quick reflector A (110) and the quick reflector B (210) are all placed at an angle of 45 degrees to the horizontal plane.

8. The intersatellite laser communication link simulation device based on energy characteristic inversion according to claim 7, characterized in that: The device further comprises: an azimuth-tilt platform A (111) and an azimuth-tilt platform B (211); The azimuth and elevation platform A (111) is used for connecting to the optical terminal A (101) to be tested; The azimuth and elevation platform B (211) is used for connecting to the optical terminal B (201) to be tested.

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