A portable space laser communication link establishment testing device and testing method

Abstract

The application discloses a kind of portable space laser communication link establishment test device, comprising: beam expander subassembly, signal light receiving module, signal light emitting module, light splitter, dichroic filter, piezoelectric ceramic fast mirror, piezoelectric controller, monitoring camera, communication machine and industrial computer;Beam expander subassembly, light splitter, dichroic filter, piezoelectric ceramic fast mirror are sequentially coaxial interval arrangement;Signal light emitting module emits light sequentially through piezoelectric ceramic fast mirror light splitter, dichroic filter and beam expander subassembly;The measured space laser communication load is set on satellite.The application is integrated into a whole device by each unit used, directly powered on when using, convenient to use, improves test efficiency.The structure is simple, and the measured space laser communication load can be tracked performance test, increase the functionality and comprehensiveness of test device.

Description

Technical Field

[0001] This invention relates to the field of satellite integrated testing technology, and in particular to a portable space laser communication link establishment testing device and testing method. Background Technology

[0002] When using Global Navigation Satellite System (GNSS) satellites for navigation and positioning, the instantaneous position and velocity of the satellite are first calculated. The position and velocity of a GNSS satellite in orbit are expressed using ephemeris data. GNSS satellites broadcast ephemeris data to users, who then use the received broadcast ephemeris data to calculate the GNSS satellite's position and velocity using formulas. Similarly, receiving users receive ephemeris information from transmitting GNSS satellites via broadcast, and then calculate the initial pointing of the space laser communication payload.

[0003] Before a space laser communication payload can be put into use, its performance needs to be tested. Existing testing equipment is complex in structure, each test unit needs to be installed and used separately, which is very complicated and makes it impossible to perform performance tracking tests. Summary of the Invention

[0004] To address the aforementioned problems in the existing technology, this invention provides a portable space laser communication link establishment testing device and method. The technical problem to be solved by this invention is achieved through the following technical solution:

[0005] The first aspect of this invention provides a portable space laser communication link establishment test device, comprising: a beam expander, a signal light receiving module, a signal light emitting module, a relay optical path assembly, a piezoelectric ceramic fast reflector, a piezoelectric controller, a monitoring camera, a communication device, and an industrial control computer; the relay optical path assembly comprises: a beam splitter and a dichroic separator;

[0006] The beam expander, the beam splitter, the dichroic separator, and the piezoelectric ceramic fast-reflecting mirror are arranged coaxially and at intervals in sequence.

[0007] The space light emitted by the space laser communication payload under test passes sequentially through the beam expander and the beam splitter, then enters the dichroic divider, and is reflected by the dichroic divider before entering the signal light receiving module; wherein, the space light entering the beam splitter through the beam expander is also reflected by the beam splitter before entering the monitoring camera.

[0008] The light emitted by the signal light emitting module passes sequentially through the piezoelectric ceramic fast reflector, the dichroic filter, the beam splitter, and the beam expander.

[0009] The piezoelectric controller is connected to the piezoelectric ceramic fast-reflecting mirror;

[0010] The piezoelectric ceramic fast-reflecting mirror is used to adjust the emission direction of the signal light emitting module and to add interference to the emitted light of the signal light emitting module;

[0011] The signal receiving end of the communication device is connected to the output end of the signal optical receiving module, and the signal transmitting end of the communication device is connected to the input end of the signal optical transmitting module.

[0012] The communication device and the monitoring camera are electrically connected to the industrial control computer;

[0013] The space laser communication payload under test is mounted on the satellite.

[0014] In one embodiment of the present invention, it further includes:

[0015] A first camera lens and a second camera lens are sequentially disposed between the beam splitter and the monitoring camera.

[0016] In one embodiment of the present invention, it further includes:

[0017] A first receiving lens and a second receiving lens are sequentially disposed between the color separator and the signal light receiving module.

[0018] In one embodiment of the present invention, it further includes: a first emitting lens and a second emitting lens sequentially disposed between the piezoelectric ceramic fast reflector and the signal light emitting module.

[0019] In one embodiment of the present invention, the signal light receiving module is a multimode receiving module; the signal light transmitting module is a single-mode transmitting module.

[0020] In one embodiment of the present invention, the maximum aperture of the beam expander is 120 mm, and the maximum effective aperture of the space laser communication payload under test is 80 mm.

[0021] The maximum distance between the azimuth pitch rotation center of the measured space laser communication payload and the horizontal rotation center of the beam expander assembly is 1.5m.

[0022] In one embodiment of the present invention, the monitoring camera is a CCD camera.

[0023] A second aspect of this invention provides a portable space laser communication link establishment testing method, applied to the testing device provided in the first aspect of this invention, comprising the following steps:

[0024] Turn on the space laser communication payload under test, adjust the position of the space laser communication payload under test and the test device until a light spot appears in the monitoring camera and outputs the centroid data to the industrial control computer, then turn off the space laser communication payload under test.

[0025] Turn on the piezoelectric ceramic fast-reflecting mirror, flip the beam splitter, flip the monitoring camera, and adjust the position of the signal light transmitting module until the difference between the centroid coordinates of the corrected emitted light of the signal light transmitting module and the corrected emitted light of the signal light receiving module is less than or equal to the correction threshold.

[0026] Reset the beam splitter and monitoring camera, and rotate the piezoelectric ceramic fast reflector by 10 milliradians in any direction.

[0027] Power on the space laser communication payload under test, start the acquisition mode until stable tracking, and acquire multiple centroid coordinates within a preset time period;

[0028] Repeat the process of turning off the space laser communication payload under test and rotating the piezoelectric ceramic fast reflector by 10 milliradians in any direction multiple times, then turning on the space laser communication payload under test, starting the capture mode until stable tracking, acquiring multiple centroid coordinates within a preset time period, and obtaining the test results.

[0029] The beneficial effects of this invention are:

[0030] This invention integrates all the necessary units into a single device, which is easy to use and can be turned on directly, thus improving testing efficiency. Furthermore, its simple structure and ability to perform tracking performance tests on the space laser communication payload under test enhance the functionality and comprehensiveness of the testing apparatus.

[0031] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the written description, claims, and drawings.

[0032] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0033] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0034] Figure 1 This is a schematic diagram of a portable space laser communication link establishment test device provided in an embodiment of the present invention. Detailed Implementation

[0035] The present invention will be further described in detail below with reference to specific embodiments, but the implementation of the present invention is not limited thereto.

[0036] Explanation of the working process of space laser communication payload:

[0037] Initial pointing refers to resolving the relative position and relative motion relationship between the receiver and transmitter based on the ephemeris information of the other end, and then controlling the tracking actuator (such as a two-dimensional turntable or fast reflector) of the space laser communication payload based on the ephemeris of the local end to point to the target position. Its closed-loop method is mostly code disk closed-loop or strain gauge closed-loop.

[0038] Uncertainty refers to the initial pointing error caused by a combination of factors such as target position calculation, platform micro-vibration, and platform attitude instability. To compensate for this error, one end of the transmitter or receiver is fixed on the target, while the other end scans the uncertain region relative to the fixed end according to a specific pattern to achieve scanning and acquisition.

[0039] Scan capture refers to the process where the staring end maintains its initial pointing gaze, while the scanning end scans the uncertain area according to a specific pattern until the communication light from the staring end appears on the detector of the scanning end, thus entering the capture and tracking phase.

[0040] Acquisition and tracking refers to the process where, after scanning is completed, a light spot appears on the detector. Based on the centroid / center of the light spot, the actual relative position and relative motion of the transmitting and receiving ends are reflected. Then, the tracking actuator is guided according to the position of the light spot to guide the beam from the other end into the communication field of view.

[0041] Stable tracking refers to using a tracking actuator to keep the laser beam within the communication field of view for an extended period, with the received power exceeding the minimum communication requirements, thereby enabling space laser communication.

[0042] like Figure 1 As shown, a first aspect of this invention provides a portable space laser communication link establishment test device, comprising: a beam expander 11, a signal light receiving module 12, a signal light transmitting module 13, a relay optical path assembly, a piezoelectric ceramic fast reflector 16, a piezoelectric controller, a monitoring camera 17, a communication unit, and an industrial control computer. The relay optical path assembly includes: a beam splitter 14 and a dichroic separator 15.

[0043] The beam expander 11, beam splitter 14, dichroic filter 15, and piezoelectric ceramic fast reflector 16 are arranged coaxially at intervals in sequence. The beam expander 11 is used to compress the divergence angle and increase the receiving aperture.

[0044] The space light emitted by the space laser communication payload under test passes sequentially through the beam expander 11 and the beam splitter 14, then enters the dichroic filter 15, and is reflected by the dichroic filter 15 before entering the signal light receiving module 12. Here, the light incident on the dichroic filter 15 and the beam splitter 14 is partially transmitted and partially reflected by the dichroic filter 15 and the beam splitter 14.

[0045] Among them, the spatial light entering the beam splitter 14 through the beam expander 11 is also reflected by the beam splitter 14 and enters the monitoring camera 17; the beam splitter 14 is used to separate a part of the incident light to the monitoring camera 17 to calculate the centroid coordinates, and the other part passes through the beam splitter 14 and enters the color separator 15. The color separator 15 is used to separate the signal receiving and emission light, which are C46 and C18 respectively.

[0046] The light emitted by the signal light emitting module 13 passes sequentially through the piezoelectric ceramic fast reflector 16, the dichroic filter 15, the beam splitter 14, and the beam expander 11, forming spatial light after beam expansion. Here, the light incident on the dichroic filter 15 and the beam splitter 14 is transmitted through them. The piezoelectric controller is connected to the piezoelectric ceramic fast reflector 16. The piezoelectric ceramic fast reflector 16 is used to adjust the emission direction of the signal light emitting module 13 and to add interference to the emitted light of the signal light emitting module 13, simulating the jitter caused by the micro-vibration of the tested end on the light position. Rotating the piezoelectric ceramic fast reflector 16 by a certain arc can simulate an uncertain region. Here, the satellite will vibrate in the sky, causing the light emitted by the laser communication payload to jitter. However, during the test, the satellite on the ground will not experience vibration in the sky. Therefore, the piezoelectric ceramic fast reflector 16 adds perturbation to the light emitted by the signal light emitting module 13, causing the light position to jitter, which is equivalent to the jitter of the emitted light of the tested space laser communication payload.

[0047] The signal receiving end of the communication unit is connected to the output end of the signal optical receiving module 12, and the signal transmitting end of the communication unit is connected to the input end of the signal optical transmitting module 13; both the communication unit and the monitoring camera 17 are electrically connected to the industrial control computer. The industrial control computer is used to analyze ephemeris information, add random disturbances, monitor analog quantities, and perform other related control and analysis of the testing process.

[0048] The beam expander 11 is used to emit collimated light emitted from the signal light emission path as approximately parallel light with a larger aperture, so as to sufficiently illuminate the entire tracking field of view of the payload under test; the space laser communication payload under test is set on the satellite.

[0049] In this embodiment, after the space laser communication payload under test and the test device are aligned coaxially, the test begins. The centroid coordinates of the light spots generated by the signal light receiving module 12 and the signal light emitting module 13 are monitored by the monitoring camera 17. The tracking capability and anti-interference capability of the space laser communication payload under test are obtained by analyzing the centroid coordinates.

[0050] A first camera lens and a second camera lens are sequentially arranged between the beam splitter 14 and the monitoring camera 17. A first receiving lens and a second receiving lens are sequentially arranged between the color separator 15 and the signal light receiving module 12. A first transmitting lens and a second transmitting lens are sequentially arranged between the piezoelectric ceramic fast-reflecting mirror 16 and the signal light transmitting module 13. The signal light receiving module 12 is a multi-mode receiving module; the signal light transmitting module 13 is a single-mode transmitting module. The monitoring camera 17 is a CCD camera.

[0051] When the distance between the azimuth elevation rotation center of the space laser communication payload under test and the horizontal rotation center of the beam expander 11 is less than 1.5m, the maximum aperture of the beam expander 11 can reach 120mm, and the maximum effective aperture of the space laser communication payload under test can reach 80mm. In this case, the light emitted by the space laser communication payload under test within the range of 0.5°-4.2° after alignment can enter the test device and be received. Here, the rotation of 0.5°-4.2° can simulate the uncertain region of 10mrad under poor link establishment environment.

[0052] After the multimode receiving optical path and the beam expander 11 are integrated, the overall F-number is approximately 4.75, resulting in a high coupling efficiency after adjustment. The coupling efficiency can be changed by adjusting the flange at the fiber connection, thereby simulating the spatial attenuation caused by different communication distances. The test device in this embodiment is for ground-based testing and can use a wide range of piezoelectric materials, allowing the piezoelectric ceramic fast reflector 16 to cover various micro-vibration conditions, such as the NASDA vibration spectrum.

[0053] A second aspect of this invention provides a portable space laser communication link establishment testing method, applied to the testing apparatus of the first aspect of this invention, comprising the following steps:

[0054] Step 201: After the space laser communication payload under test is assembled and integrated with the satellite, the signal light transmission module 13 (single-mode signal light transmission module) is connected to the laser of the corresponding wavelength, and the monitoring camera 17 is turned on.

[0055] Step 202: Power on the space laser communication payload under test, adjust the position of the space laser communication payload under test and the test device until a light spot appears in the monitoring camera 17 and outputs the centroid data to the industrial control computer, and then power off the space laser communication payload under test.

[0056] In this step, the emitted light of the space laser communication payload under test is adjusted to be coaxial with the beam expander 11 until a light spot appears in the monitoring camera 17, and the receiving relative zero position is adjusted. Specifically, a power meter is connected to the signal light receiving module 12, and the centroid coordinates of the point with the strongest optical power of the signal light receiving module 12 are calibrated as the receiving relative zero position.

[0057] Step 203: Turn on the piezoelectric ceramic fast-reflecting mirror 16 and flip the beam splitter 14. Here, with... Figure 1 Using the center direction as a reference, flip the camera left and right, and rotate the monitoring camera 17 180 degrees. Here, using... Figure 1 Using the center direction as a reference, flip upwards and adjust the position of the signal light transmitting module 13 until the difference between the centroid coordinates of the corrected emitted light of the signal light transmitting module 13 and the corrected emitted light of the signal light receiving module 12 is less than or equal to the correction threshold.

[0058] In this step, after the beam splitter 14 is flipped, an incident light is received from the signal light receiving module 12 as the correction emission light, the centroid coordinates of the correction emission light are obtained, and then the centroid coordinates of the emission light of the signal light emitting module 13 are obtained. The position of the signal light emitting module 13 is adjusted until the difference between the two centroid coordinates is less than or equal to the correction threshold. At this time, the emission zero position of the test device is calibrated.

[0059] Step 204: Reset the beam splitter 14 and the monitoring camera 17, and rotate the piezoelectric ceramic fast reflector 16 by 10 milliradians in any direction to simulate the uncertain area under poor link establishment environment.

[0060] Step 205: Power on the space laser communication payload under test, emit beacon light (space light), and activate the acquisition mode until stable tracking is achieved, acquiring multiple centroid coordinates within a preset time period. The preset time period is the tracking period itself; the centroid coordinates within this period allow for the acquisition of the jitter (displacement) of the tracking spot.

[0061] Step 206: Power off the space laser communication payload under test, and repeat steps 204-205.

[0062] Step 207: Repeat step 206 to obtain the test results.

[0063] In this embodiment, tracking accuracy and anti-interference capability can be obtained based on the jitter. For example, whether the displacement of the centroid coordinates exceeds 5 microradians can determine the tracking accuracy and anti-interference capability.

[0064] A third aspect of this invention provides a portable space laser communication link establishment testing method, using two testing devices from the first aspect of this invention and two space laser communication payloads under test, namely a first testing device and a second testing device, a first space laser communication payload under test and a second space laser communication payload under test. However, in this embodiment, no industrial control computer or communication device is required; the test results are obtained from the satellite and the space laser communication payload under test. The testing equipment used in this embodiment includes the following steps:

[0065] Step 301: The signal light receiving module 12 of the first test device is connected to the signal light transmitting module 13 of the second test device, and the signal light transmitting module 13 of the first test device is connected to the signal light receiving module 12 of the second test device.

[0066] Step 302: Power on the first space laser communication payload under test, adjust the positions of the first space laser communication payload under test and the first test device until a light spot appears in the monitoring camera 17 and the centroid data is output to the industrial control computer, then power off the first space laser communication payload under test. The second space laser communication payload under test and the second test device are adjusted in the same way.

[0067] In this step, the emitted light of the space laser communication payload under test is adjusted to be coaxial with the beam expander 11 until a light spot appears in the monitoring camera 17, and the receiving relative zero position is adjusted. Specifically, a power meter is connected to the signal light receiving module 12, and the centroid coordinates of the point with the strongest optical power of the signal light receiving module 12 are calibrated as the receiving relative zero position.

[0068] Step 303: Activate the first and second space laser communication payloads under test to begin simulating a communication mode with space optical transmission.

[0069] Step 304: Using the piezoelectric ceramic fast reflector 16 to simulate the micro-vibration of the satellite platform, repeat step 303 to obtain test results such as communication error rate, continuous working time, and communication rate from the satellite and the space laser communication payload under test.

[0070] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0071] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0072] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0073] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0074] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0075] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A portable space laser communication link establishment test device, characterized by, For ground detection use, comprising: a beam expander assembly, a signal light receiving module, a signal light emitting module, a relay light path assembly, a piezoelectric ceramic fast mirror, a piezoelectric controller, a monitoring camera, a communication machine and an industrial computer; the relay light path assembly comprises: a light splitting sheet and a color separation sheet; The beam expander assembly, the light splitting sheet, the color separation sheet and the piezoelectric ceramic fast mirror are coaxially and sequentially arranged; The space light emitted by the measured space laser communication load sequentially passes through the beam expander assembly and the light splitting sheet, enters the color separation sheet, and is reflected by the color separation sheet to enter the signal light receiving module; wherein the space light entering the light splitting sheet through the beam expander assembly is also reflected by the light splitting sheet to enter the monitoring camera; The light emitted by the signal light emitting module sequentially passes through the piezoelectric ceramic fast mirror, the color separation sheet, the light splitting sheet and the beam expander assembly; The piezoelectric controller is connected with the piezoelectric ceramic fast mirror; The piezoelectric ceramic fast mirror is used for adjusting the emission direction of the signal light emitting module and adding interference to the emitted light of the signal light emitting module; wherein the piezoelectric ceramic fast mirror is rotated by a certain radian to simulate an uncertain area, the satellite does not vibrate in the sky during testing on the ground, the piezoelectric ceramic fast mirror adds interference to the light emitted by the signal light emitting module at this end, so that the light position is jittered, which is equivalent to the jitter of the emitted light of the measured space laser communication load; The signal receiving end of the communication machine is connected with the output end of the signal light receiving module, and the signal sending end of the communication machine is connected with the input end of the signal light emitting module; The communication machine and the monitoring camera are electrically connected with the industrial computer; The measured space laser communication load is arranged on the satellite.

2. The apparatus of claim 1, wherein, Further comprising: A first camera lens and a second camera lens are sequentially arranged between the light splitting sheet and the monitoring camera.

3. The apparatus of claim 2, wherein, Further comprising: A first receiving lens and a second receiving lens are sequentially arranged between the color separation sheet and the signal light receiving module.

4. The apparatus of claim 2, wherein, Further comprising: A first emitting lens and a second emitting lens are sequentially arranged between the piezoelectric ceramic fast mirror and the signal light emitting module.

5. The apparatus of claim 1, wherein, The signal light receiving module is a multimode receiving module, and the signal light emitting module is a single-mode emitting module.

6. The apparatus of claim 1, wherein, The maximum aperture of the beam expander assembly is 120mm, and the maximum effective aperture of the measured space laser communication load is 80mm; The maximum distance between the azimuth and pitch rotation center of the measured space laser communication load and the horizontal rotation center of the beam expander assembly is 1.5m.

7. The apparatus of claim 1, wherein, The monitoring camera is a CCD camera.

8. A portable space laser communication link establishment test method, characterized by, The application is applied to the testing device of claim 1, comprising the following steps: The measured space laser communication load is turned on, the positions of the measured space laser communication load and the testing device are adjusted until a light spot appears in the monitoring camera, and the centroid data is output to the industrial computer, and then the measured space laser communication load is turned off; The piezoelectric ceramic fast mirror is turned on, the light splitting sheet is turned over, the monitoring camera is turned over, and the position of the signal light emitting module is adjusted until the difference between the centroid coordinates of the corrected emission light of the signal light emitting module and the corrected emission light of the signal light receiving module is less than or equal to the correction threshold value; Resetting the light splitting plate and the monitoring camera, rotating the piezoelectric ceramic fast mirror to any direction by 10 milliradians; Turning on the space laser communication load to be measured, starting the acquisition mode until stable tracking, and obtaining multiple centroid coordinates within a preset time period; Repeating the process of turning off the space laser communication load to be measured, rotating the piezoelectric ceramic fast mirror to any direction by 10 milliradians, turning on the space laser communication load to be measured, starting the acquisition mode until stable tracking, and obtaining multiple centroid coordinates within a preset time period, and obtaining the test result.

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