Testing system and method for avoiding sun-sun in inter-satellite laser communication

Abstract

The invention discloses an inter-satellite laser communication sun-sun avoidance test system, which comprises a two-dimensional rotary table used for simulating an in-orbit movement track of a satellite body. And the solar simulation laser is arranged on one side of the two-dimensional turntable and is used for simulating a light source which has similar beam divergence angle and energy with sunlight. And the laser communication terminal is arranged on the two-dimensional turntable and is used for simulating communication equipment to be linked. And the camera is arranged on the laser communication terminal and is used for measuring the included angle of the solar simulation laser relative to the laser communication terminal. The upper computer is respectively connected with the laser communication terminal and the two-dimensional turntable, and is used for providing initial track information for the laser communication terminal and providing corner information for the two-dimensional turntable; and the two-dimensional turntable rotates according to the rotation angle information provided by the upper computer. According to the invention, the reliability of the laser communication terminal for carrying out on-orbit sunshine avoidance is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of space laser communication, and in particular to a testing system and method for avoiding solar eclipse in inter-satellite laser communication. Background Art

[0002] The successful establishment of a large-scale constellation Internet requires long-term and stable intersatellite laser communication links, but the laser communication terminals in orbit are always inevitably affected by the sun. The energy of the solar spectrum near 1550nm can always enter the laser communication terminal working in the C band, which makes it impossible for the terminal to accurately identify the signal, resulting in signal tracking loss, link interruption, etc. In severe cases, it can also cause damage to the terminal detector and cannot be restored.

[0003] In order to avoid the influence of the sun and reduce the pressure of ground control, the onboard terminal needs to make avoidance predictions autonomously, and use the extrapolation algorithm to calculate the angle between the sun vector and the link establishment direction after a period of time, as a basis for judging whether avoidance measures need to be taken in advance. At present, the accuracy of the extrapolation algorithm is usually verified by numerical simulation, and there is a lack of actual test systems. In order to improve the accuracy of the solar transit avoidance prediction of the laser communication terminal in orbit, a test system and method for solar transit avoidance in intersatellite laser communication is designed. Summary of the invention

[0004] The purpose of the present invention is to provide a test system and method for avoiding solar eclipses in intersatellite laser communications, which are used to accurately determine whether it is necessary to take measures to avoid solar eclipses in advance and to improve the reliability of solar eclipse avoidance by laser communication terminals in orbit.

[0005] In order to achieve the above objectives, the present invention is implemented by the following technical solutions:

[0006] A test system for intersatellite laser communication to avoid solar eclipses, comprising: a two-dimensional turntable for simulating the motion trajectory of a satellite body in orbit. A solar simulation laser, arranged on one side of the two-dimensional turntable, for simulating a light source with a similar beam divergence angle and energy to sunlight. A laser communication terminal, arranged on the two-dimensional turntable, for simulating a communication device to be linked. A camera, arranged on the laser communication terminal, for measuring the angle between the solar simulation laser and the laser communication terminal. A host computer, respectively connected to the laser communication terminal and the two-dimensional turntable, for providing initial orbit information for the laser communication terminal and providing angle information for the two-dimensional turntable; the two-dimensional turntable rotates according to the angle information provided by the host computer.

[0007] Optionally, the laser communication terminal takes measures to avoid solar eclipse based on the angle between the solar simulation laser and the laser communication terminal measured by the camera and the angle between the link establishment direction calculated by the extrapolation algorithm and the solar simulation laser vector; the link establishment direction is the direction of signal transmission between the two satellites to be linked.

[0008] Optionally, the laser communication terminal includes: a two-dimensional rotation mechanism. A transceiver optical system is arranged on the two-dimensional rotation mechanism, and is used to transmit and receive communication optical signals. The two-dimensional rotation mechanism is used to turn the transceiver optical system to the link establishment direction and simulate the motion trajectory of the transceiver optical system in orbit link establishment. An information processing unit is arranged on the two-dimensional rotation mechanism, and is used to receive the initial orbit information provided by the host computer and perform link calculation, angle conversion and orbit extrapolation.

[0009] Optionally, the laser communication terminal and the camera have the same optical axis, and the camera has a field of view angle of more than 10°.

[0010] Optionally, the initial angle of the solar simulation laser relative to the laser communication terminal is obtained by decomposing the angle of the solar simulation laser vector relative to the satellite body vector at the initial moment provided by STK, which is used to determine the initial placement position of the solar simulation laser relative to the laser communication terminal.

[0011] On the other hand, the present invention also provides a test method for intersatellite laser communication to avoid solar eclipse, which is implemented by using the test system for intersatellite laser communication to avoid solar eclipse as described above, and the method comprises:

[0012] Step S1: The laser communication terminal obtains initial orbit information through the host computer. The initial orbit information is the six orbit numbers of the two satellites used to establish the link provided by STK at the initial time t0. Step S2: The laser communication terminal calculates the position vector x of the two satellites required to establish the link at time t0 based on the initial orbit information and the orbit formula 01 and x 02 , and calculate the initial link direction x of the laser communication terminal 03 =x 02 -x 01 Step S3: The laser communication terminal uses an angle conversion formula to point the initial link to x. 03 The laser communication terminal is converted into a first azimuth pitch angle that needs to be rotated so that the laser communication terminal points to the link establishment direction; and the laser communication terminal is controlled to rotate according to the first azimuth pitch angle. Step S4, the laser communication terminal uses the Runge-Kutta extrapolation algorithm to calculate the link direction x of the laser communication terminal after time t t3 =x t2 -xt1 , and the link of the laser communication terminal after time t is directed to x through the angle conversion formula t3 The laser communication terminal is converted into a second azimuth pitch angle that needs to be rotated so as to point to the link establishment direction; and the laser communication terminal is controlled to rotate according to the second azimuth pitch angle. Step S5, the host computer calculates the solar simulation laser vector s after time t using the Runge-Kutta extrapolation algorithm t , and calculate the link direction x of the laser communication terminal after time t t3 and the solar simulation laser vector s t The first angle α t1 Step S6: The host computer converts the satellite body vector provided by the STK after time t into rotation angle information, and controls the two-dimensional turntable to rotate according to the rotation angle information. Step S7: Starting from t0, the camera is used to measure the angle between the solar simulation laser and the laser communication terminal to obtain a second angle α t2 , and the first angle α t1 and the second angle α t2 The comparison result is obtained by comparing the angle with the sun avoidance angle, and measures for avoiding the solar eclipse are taken according to the comparison result.

[0013] Optionally, the step S7 comprises: t1 and the second angle α t2 The difference Δ=αt2-αt1 is calculated and judged: when Δ is greater than the preset value, the two-dimensional rotation mechanism is ordered to stop rotating and the cause is checked; if the first angle α t1 and the second angle α t2 If both are smaller than the solar avoidance angle, measures to avoid solar eclipse are taken.

[0014] Optionally, the initial orbit information is six orbital numbers of the two satellites used for link establishment provided by STK at the initial time t0. The six orbital numbers include: orbital semi-major axis α, orbital eccentricity e, orbital inclination i, ascending node right ascension Ω, perigee argument ω and true anomaly f.

[0015] Optionally, the information processing unit of the laser communication terminal calculates the link orientation using the following orbit formula:

[0016] The link calculation is obtained through position vector calculation, and the calculation formula is:

[0017]

[0018] Where P and Q both represent coordinate transformation matrices; R0 and V0 are the position vector and velocity vector in the geocentric coordinate system, respectively, both of which are 3×1 column vectors; M represents the mean-near-ground angle, and the transformation relationship between M and f is:

[0019]

[0020] Substitute the six orbital elements (α1, e1, i1, Ω1, ω1, f1) and (α2, e2, i2, Ω2, ω2, f2) of the two satellites to be linked into the coordinate transformation matrices P and Q for calculation, and then substitute P and Q into the position vector formula R0 for calculation, and the position vectors x of the two satellites to be linked can be obtained respectively. 01 and x 02 , then the relative position between the two satellites, that is, the initial link point x 03 =x 02 -x 01 , the six orbital numbers are generally provided for the entire star.

[0022] Optionally, the rotation angle information is obtained by decomposing the local satellite position vector provided by STK, where the local satellite refers to the satellite where the laser communication terminal is located. At any time, the local satellite position vector is (x Lb ,y Lb , z Lb ), then the rotation angles of the azimuth and pitch axes are decomposed into:

[0023]

[0024] In the formula, θ EL represents the azimuth, θ AZ Indicates the pitch angle.

[0025] The present invention has at least one of the following technical effects:

[0026] The test system of the present invention can autonomously avoid solar eclipses according to satellite operation conditions, thereby improving the operation capability of laser communication terminals and improving the reliability of laser communication terminals in avoiding solar eclipses on orbit.

[0027] The laser communication terminal of the present invention avoids solar eclipse according to the first angle and the angle between the link establishment direction and the solar simulation laser vector, thereby improving the reliability of the laser communication terminal in avoiding solar eclipse in orbit.

[0028] The present invention uses an extrapolation algorithm to predict the sun avoidance angle and uses a camera to measure the sun avoidance angle for comparison, which can fully verify the accuracy of the extrapolation algorithm and actually measure the sun avoidance angle, thereby improving the reliability of the laser communication terminal in orbit to avoid solar eclipses.

[0029] The present invention can autonomously avoid solar eclipses according to satellite operation conditions, improve the operation capability of laser communication terminals, reduce the workload of ground operation and control systems, and reduce operation and maintenance costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic diagram of the structure of a test system for intersatellite laser communication to avoid solar eclipse provided by an embodiment of the present invention;

[0031] Figure 2 A flow chart of a test method for avoiding solar eclipse in intersatellite laser communication provided by an embodiment of the present invention;

[0032] Figure 3 A detailed process diagram of a test method for avoiding solar eclipse in intersatellite laser communication provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0033] The following is a further detailed description of a test system and method for intersatellite laser communication to avoid solar eclipse proposed by the present invention in combination with the accompanying drawings and specific embodiments. According to the following description, the advantages and features of the present invention will be clearer. It should be noted that the drawings are in a very simplified form and use non-precise proportions, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention. In order to make the purposes, features and advantages of the present invention more obvious and easy to understand, please refer to the accompanying drawings. It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no technical substantive significance. Any structural modification, change in proportional relationship or adjustment of size, without affecting the effects that can be produced by the present invention and the purposes that can be achieved, should still fall within the scope of the technical content disclosed by the present invention.

[0034] Figure 1 A schematic diagram of a test system for intersatellite laser communication to avoid solar eclipse is provided for one embodiment of the present invention. Figure 1As shown, this embodiment provides a test system for intersatellite laser communication to avoid solar eclipse, including: a two-dimensional turntable 200, used to simulate the motion trajectory of the satellite body in orbit. A solar simulation laser 400, arranged on one side of the two-dimensional turntable 200, is used to simulate a light source with a similar beam divergence angle and energy to sunlight. A laser communication terminal 100, arranged on the two-dimensional turntable 200, is used to simulate a communication device to be established. A camera 300, arranged on the laser communication terminal 100, is used to measure the angle of the solar simulation laser 400 relative to the laser communication terminal 100. A host computer 500, respectively connected to the laser communication terminal 100 and the two-dimensional turntable 200, is used to provide initial orbit information for the laser communication terminal 100, and to provide angle information for the two-dimensional turntable 200; the two-dimensional turntable 200 rotates according to the angle information provided by the host computer 500.

[0035] The test system of this embodiment can autonomously avoid solar eclipses according to the satellite operation conditions, thereby improving the operation capability of the laser communication terminal 100 and improving the reliability of the laser communication terminal 100 in avoiding solar eclipses while in orbit.

[0036] In this embodiment or some other embodiments, when operating in orbit, the laser communication terminal 100 takes measures to avoid solar eclipses based on the angle between the solar simulation laser 400 and the laser communication terminal 100 measured by the camera 300 and the angle between the link establishment direction calculated by the extrapolation algorithm and the solar simulation laser vector; the link establishment direction is the direction of signal transmission between the two satellites to be linked.

[0037] In this embodiment or some other embodiments, the laser communication terminal 100 includes: a two-dimensional rotation mechanism 103. The transceiver optical system 102 is arranged on the two-dimensional rotation mechanism 103, and is used to transmit and receive communication optical signals. The two-dimensional rotation mechanism 103 is used to turn the transceiver optical system 102 to the link establishment direction and simulate the motion trajectory of the transceiver optical system 102 in orbit link establishment. The information processing unit 101 is arranged on the two-dimensional rotation mechanism 103, and is used to receive the orbit information provided by the host computer 500 and perform link calculation, angle conversion and orbit extrapolation.

[0038] In this embodiment or some other embodiments, the laser communication terminal 100 and the camera 300 have the same optical axis, and the camera 300 has a field of view of more than 10°. This can ensure the accuracy of the camera 300 in measuring the angle between the solar simulation laser 400 and the laser communication terminal 100.

[0039] In this embodiment or some other embodiments, the initial angle of the solar simulation laser 400 relative to the laser communication terminal 100 is obtained by decomposing the angle of the solar simulation laser vector relative to the satellite body vector at the initial moment provided by STK (Satellite Tool Kit), which is used to determine the initial placement position of the solar simulation laser 400 relative to the laser communication terminal 100.

[0040] On the other hand, this embodiment also provides a test method for avoiding solar eclipse in intersatellite laser communication, which is implemented by the test system for avoiding solar eclipse in intersatellite laser communication as described above, and the method includes: step S1, the laser communication terminal 100 obtains initial orbit information through the host computer 500. The initial orbit information is the six orbital numbers of the two satellites used for link establishment provided by STK at the initial time t0.

[0041] Step S2: The laser communication terminal 100 calculates the position vector x of the two satellites to be linked at time t0 according to the initial orbit information and the orbit formula. 01 、x 02 , and calculate the initial link direction x of the laser communication terminal 100 03 =x 02 -x 01 .

[0042] Step S3: The laser communication terminal 100 directs the initial link to x by using an angle conversion formula. 03 Converting into a first azimuth and elevation angle that the laser communication terminal 100 needs to rotate to point to the link establishment direction; and controlling the laser communication terminal 100 to rotate according to the first azimuth and elevation angle.

[0043] Step S4: The laser communication terminal 100 uses the Runge-Kutta extrapolation algorithm to calculate the link direction x of the laser communication terminal 100 after time t. t3 =x t2 -x t1 , and the link direction of the laser communication terminal 100 after time t is directed to x through the angle conversion formula t3 Converting the laser communication terminal 100 to a second azimuth and elevation angle that needs to be rotated in the direction of link establishment; and controlling the laser communication terminal 100 to rotate according to the second azimuth and elevation angle.

[0044] Step S5: The host computer 500 uses the Runge-Kutta extrapolation algorithm to calculate the solar simulation laser vector s after time t. t , and calculate the link direction x of the laser communication terminal 100 after time t t3 and the sun-simulating laser vector s t The first angle αt1 .

[0045] Step S6: The host computer 500 converts the position vector of the satellite body after time t into rotation angle information, and controls the two-dimensional turntable 200 to rotate according to the rotation angle information.

[0046] Step S7: Starting from t0, the camera 300 is used to measure the angle between the solar simulation laser 400 and the laser communication terminal 100 to obtain a second angle α. t2 , and the first angle α t1 and the second angle α t2 The comparison result is obtained by comparing the angle with the sun avoidance angle, and measures for avoiding the solar eclipse are taken according to the comparison result.

[0047] In this embodiment or some other embodiments, the step S7 includes: adjusting the first angle α t1 and the second angle α t2 The difference Δ=αt2-αt1 is calculated and judged:

[0048] When Δ is greater than a preset value, the two-dimensional rotation mechanism 103 is commanded to stop rotating and the cause is checked.

[0049] If the first angle α t1 and the second angle α t2 If both are smaller than the solar avoidance angle, measures to avoid solar eclipse are taken.

[0050] Specifically, step S2 includes: the information processing unit 101 of the laser communication terminal 100 calculates the position vector x of the two satellites required to establish a link at time t0 according to the orbit formula 01 、x 02 , and calculate the initial link direction x of the laser communication terminal 100 03 =x 02 -x 01 .

[0051] The step S3 includes: the information processing unit 101 of the laser communication terminal 100 uses the angle conversion formula to convert the link at time t0 to x 03 Convert it into the azimuth and elevation angles that the laser communication terminal 100 needs to rotate to point in the link establishment direction; and control the two-dimensional rotation mechanism 103 of the laser communication terminal 100 to rotate according to this angle.

[0052] The step S4 includes: the information processing unit 101 of the laser communication terminal 100 uses the Runge-Kutta extrapolation algorithm to calculate the link direction x of the laser communication terminal 100 after time t. t3 =x t2 -x t1The information processing unit 101 of the laser communication terminal 100 uses the angle conversion formula to direct the link to x after time t. t3 The azimuth and elevation angles that need to be rotated for the laser communication terminal 100 to point to the link establishment direction are converted into the azimuth and elevation angles that need to be rotated; and the two-dimensional rotation mechanism 103 of the laser communication terminal 100 is controlled to rotate according to this angle. It should be noted that the orbit formula is a formula for calculating the position vector based on the six numbers at the current moment, but if the position vector after time t is to be calculated in advance, the Runge-Kutta extrapolation algorithm needs to be used.

[0053] In this embodiment or some other embodiments, the initial orbit information includes: orbit semi-major axis α, orbit eccentricity e, orbit inclination i, ascending node right ascension Ω, perigee argument ω and true anomaly f.

[0054] In this embodiment or some other embodiments, the information processing unit 101 uses the following orbital formulas (1)-(3) to calculate the position vectors of the local satellite and the opponent satellite.

[0055] Specifically, the orbit information is the six orbital numbers in the geocentric coordinate system, which are the orbital semi-major axis α, orbital eccentricity e, orbital inclination i, ascending node right ascension Ω, perigee argument ω and true anomaly f. The initial six orbital numbers are obtained through STK simulation software.

[0056] The link calculation is obtained through position vector calculation, and the calculation formula is:

[0057]

[0058] Where P and Q both represent coordinate transformation matrices; α represents the semi-major axis of the orbit; R0 and V0 are the position vector and velocity vector in the geocentric coordinate system, respectively, both of which are 3×1 column vectors; M represents the mean-near-earth angle, and the transformation relationship between M and f is:

[0059]

[0060] Where, f represents the true near-earth angle; M represents the mean near-earth angle. The position vectors x of the two satellites to be linked are calculated using the calculation formula of the position vector R0 in the geocentric coordinate system. 01 and x 02 , obtain the initial link pointing to x 03 =x 02 -x 01 Of the two satellites that need to establish a link, the satellite where the laser communication terminal is located is called the local satellite, and the other is called the counterpart satellite.

[0061] Substitute the six orbital elements (α1, e1, i1, Ω1, ω1, f1) and (α2, e2, i2, Ω2, ω2, f2) of the two satellites to be linked into the coordinate transformation matrices P and Q for calculation, and then substitute P and Q into the position vector formula R0 for calculation, and the position vectors x of the two satellites to be linked can be obtained respectively. 01 and x 02 , then the relative position between the two satellites, that is, the initial link point x 03 =x 02 -x 01 , the six orbital numbers are generally provided for the entire star.

[0062] The rotation angle information is obtained by decomposing the local satellite position vector provided by STK. The local satellite refers to the satellite where the laser communication terminal is located. Assume that the local satellite position vector at any time is (x Lb ,y Lb , z Lb ), then the rotation angles of the azimuth and pitch axes are decomposed into:

[0063]

[0064] In the formula, θ EL Indicates the azimuth angle; θ AZ Indicates the pitch angle.

[0065] Specifically, step S7 includes: starting from t0, using the camera 300 to measure the angle α of the solar simulation laser 400 t2 , and with α t1 For comparison; if α t2 -α t1 is a small value, the link orientation after time t is continuously calculated, and the link orientation is converted into angle information, and the two-dimensional rotation mechanism 103 is controlled to rotate according to this angle. t2 -α t1 If it is a large value, stop the two-dimensional rotating mechanism and find out the cause.

[0066] Determine the angle α t1 , α t2 The angle α is the angle of avoidance of the sun (typical value is 3°). t1 , α t2 If the angle α is smaller than the sun avoidance angle, an avoidance strategy is adopted; t1 , α t2 If the angle is greater than the sun avoidance angle, the link direction after time t is continued to be calculated, and the link direction is converted into angle information, and the two-dimensional rotation mechanism 103 is controlled to rotate according to this angle.

[0067] In summary, the present invention uses an extrapolation algorithm to predict the solar avoidance angle and uses the camera 300 to measure the solar avoidance angle for comparison, which can fully verify the accuracy of the extrapolation algorithm and actually measure the solar avoidance angle, thereby improving the reliability of the laser communication terminal 100 in performing solar eclipse avoidance in orbit.

[0068] It should be noted that, in this article, relational terms such as first and second, etc. 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] In the description of the present invention, it should be understood that the terms "center", "height", "thickness", "up", "down", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the 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 orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0070] In the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", and "fixed" 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0071] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0072] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

Claims

1. A test system for intersatellite laser communication to avoid solar eclipse, characterized in that: include: A two-dimensional turntable is used to simulate the motion trajectory of the satellite body in orbit; A solar simulation laser, arranged on one side of the two-dimensional turntable, for simulating a light source having a beam divergence angle and energy similar to that of sunlight; A laser communication terminal is arranged on the two-dimensional turntable and is used to simulate the communication equipment to be linked; A camera, arranged on the laser communication terminal, for measuring an angle between the solar simulation laser and the laser communication terminal; The host computer is connected to the laser communication terminal and the two-dimensional turntable respectively, and is used to provide initial orbit information for the laser communication terminal and provide angle information for the two-dimensional turntable; the two-dimensional turntable rotates according to the angle information provided by the host computer.

2. The intersatellite laser communication test system for avoiding solar eclipse according to claim 1, characterized in that: The laser communication terminal takes measures to avoid solar eclipse based on the angle between the solar simulation laser and the laser communication terminal measured by the camera and the angle between the link establishment direction calculated by the extrapolation algorithm and the solar simulation laser vector; the link establishment direction is the direction of signal transmission between the two satellites to be linked.

3. The intersatellite laser communication test system for avoiding solar eclipse according to claim 1, characterized in that: The laser communication terminal comprises: Two-dimensional rotation mechanism; A transceiver optical system, arranged on the two-dimensional rotating mechanism, for transmitting and receiving communication optical signals; The two-dimensional rotation mechanism is used to turn the transceiver optical system to the link building direction and simulate the motion trajectory of the transceiver optical system in on-track link building; An information processing unit is arranged on the two-dimensional rotation mechanism, and is used to receive the initial orbit information provided by the host computer and perform link calculation, angle conversion and orbit extrapolation.

4. The intersatellite laser communication test system for avoiding solar eclipse according to claim 1, characterized in that: include: The laser communication terminal and the camera have the same optical axis, and the camera has a field of view angle of more than 10°.

5. The intersatellite laser communication test system for avoiding solar eclipse according to claim 1, characterized in that: The initial angle of the solar simulation laser relative to the laser communication terminal is obtained by decomposing the angle of the solar simulation laser vector relative to the satellite body vector at the initial moment provided by STK, which is used to determine the initial placement position of the solar simulation laser relative to the laser communication terminal.

6. A test method for intersatellite laser communication to avoid solar eclipse, characterized in that: The method is implemented by using the test system for avoiding solar eclipse in intersatellite laser communication as claimed in any one of claims 1 to 5, and the method comprises: Step S1, the laser communication terminal obtains initial orbit information through the host computer; The initial orbit information is the six orbital numbers of the two satellites used to establish the link provided by STK at the initial time t0; Step S2: The laser communication terminal calculates the position vector x of the two satellites to be linked at time t0 according to the initial orbit information and the orbit formula. 01 and x 02 , and calculate the initial link direction x of the laser communication terminal 03 =x 02 -x 01 ; Step S3: The laser communication terminal points the initial link to x through an angle conversion formula. 03 Converting into a first azimuth pitch angle required for the laser communication terminal to rotate to point to the link establishment direction; and controlling the laser communication terminal to rotate according to the first azimuth pitch angle; Step S4: The laser communication terminal uses the Runge-Kutta extrapolation algorithm to calculate the link direction x of the laser communication terminal after time t. t3 =x t2 -x t1 , and the link of the laser communication terminal after time t is directed to x through the angle conversion formula t3 Converting into a second azimuth pitch angle required for the laser communication terminal to rotate to point to the link establishment direction; and controlling the laser communication terminal to rotate according to the second azimuth pitch angle; Step S5: The host computer uses the Runge-Kutta extrapolation algorithm to calculate the solar simulation laser vector s after time t. t , and calculate the link direction x of the laser communication terminal after time t t3 and the solar simulation laser vector s t The first angle α t1 ; Step S6, the host computer converts the satellite body vector provided by the STK after time t into rotation angle information, and controls the two-dimensional turntable to rotate according to the rotation angle information; Step S7: Starting from t0, use the camera to measure the angle between the solar simulation laser and the laser communication terminal to obtain a second angle α. t2 , and the first angle α t1 and the second angle α t2 The comparison result is obtained by comparing the angle with the sun avoidance angle, and measures for avoiding the solar eclipse are taken according to the comparison result.

7. The test method for avoiding solar eclipse in intersatellite laser communication according to claim 6, characterized in that: The step S7 comprises: The first angle α t1 and the second angle α t2 The difference Δ=αt2-αt1 is calculated and judged: When Δ is greater than a preset value, the two-dimensional rotation mechanism is commanded to stop rotating and the cause is checked; If the first angle α t1 and the second angle α t2 If both are smaller than the solar avoidance angle, measures to avoid solar eclipse are taken.

8. The test method for avoiding solar eclipse in intersatellite laser communication according to claim 6, characterized in that: The initial orbit information is the six orbital numbers of the two satellites used to establish the link provided by STK at the initial time t0; The six orbital parameters include: orbital semi-major axis α, orbital eccentricity e, orbital inclination i, ascending node right ascension Ω, perigee argument ω and true anomaly f.

9. The test method for avoiding solar eclipse in intersatellite laser communication according to claim 8, characterized in that: The information processing unit of the laser communication terminal uses the following orbit formula to calculate the link orientation: The link calculation is obtained through position vector calculation, and the calculation formula is: Where P and Q both represent coordinate transformation matrices; R0 and V0 are the position vector and velocity vector in the geocentric coordinate system, respectively, both of which are 3×1 column vectors; M represents the mean-near-ground angle, and the transformation relationship between M and f is: Substitute the six orbital elements (α1, e1, i1, Ω1, ω1, f1) and (α2, e2, i2, Ω2, ω2, f2) of the two satellites to be linked into the coordinate transformation matrices P and Q for calculation, and then substitute P and Q into the position vector formula R0 for calculation, and the position vectors x of the two satellites to be linked can be obtained respectively. 01 and x 02 , then the relative position between the two satellites, that is, the initial link point x 03 =x 02 -x 01 , the six orbital numbers are generally provided for the entire star.

10. The test method for avoiding solar eclipse in intersatellite laser communication according to claim 6, characterized in that: The rotation angle information is obtained by decomposing the local satellite position vector provided by STK. The local satellite refers to the satellite where the laser communication terminal is located. At any time, the local satellite position vector is (x Lb ,y Lb , z Lb ), then the rotation angles of the azimuth and pitch axes are decomposed into: In the formula, θ EL represents the azimuth, θ AZ Indicates the pitch angle.

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