Portable space laser communication link establishment testing device and testing method

Abstract

The invention discloses a portable space laser communication link building testing device which comprises a beam expanding assembly, a signal light receiving module, a signal light emitting module, a light splitting piece, a color separation piece, a piezoelectric ceramic fast reflecting mirror, a piezoelectric controller, a monitoring camera, a communication machine and an industrial personal computer. The beam expanding assembly, the light splitting piece, the color separation piece and the piezoelectric ceramic fast reflecting mirror are sequentially and coaxially arranged at intervals. Light emitted by the signal light emitting module sequentially passes through the piezoelectric ceramic fast reflecting mirror light splitting piece, the color separation piece and the beam expanding assembly; the measured space laser communication load is arranged on a satellite. According to the invention, all the used units are integrated into a whole device, and the device can be directly started for use during use, so that the device is convenient to use, and the test efficiency is improved. The structure is simple, the tracking performance test can be carried out on the tested space laser communication load, and the functionality and the comprehensiveness of the test device are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite integrated testing, and in particular to a portable space laser communication link building testing device and a testing method. Background Art

[0002] When using the satellites of the Global Navigation Satellite System (GNSS) for navigation and positioning, the instantaneous position and velocity of the satellite are calculated first. The position and velocity of the GNSS satellite in orbit are represented by ephemeris. The GNSS satellite broadcasts the ephemeris data to the user, and the user uses the received broadcast ephemeris data to calculate the position and velocity of the GNSS satellite according to the formula. In the same way, the receiving end user obtains the ephemeris information of the transmitting end GNSS satellite in the form of broadcast, and then solves and the initial pointing of the space laser communication payload.

[0003] The performance of space laser communication payloads needs to be tested before they are officially used. The existing test equipment has a complex structure, and each test unit needs to be installed and used separately. The installation and use are very complicated, and it is impossible to perform tracking performance tests. Summary of the invention

[0004] In order to solve the above problems existing in the prior art, the present invention provides a portable space laser communication link establishment test device and test method. The technical problem to be solved by the present invention is achieved through the following technical solutions:

[0005] A first aspect of an embodiment of the present invention provides a portable space laser communication link building test device, comprising: a beam expansion component, a signal light receiving module, a signal light transmitting module, a relay optical path component, a piezoelectric ceramic fast reflection mirror, a piezoelectric controller, a monitoring camera, a communication machine and an industrial computer; the relay optical path component comprises: a beam splitter and a color separation plate;

[0006] The beam expansion component, the beam splitter, the color separation plate, and the piezoelectric ceramic fast reflector are coaxially arranged in sequence and spaced apart;

[0007] The spatial light emitted by the measured spatial laser communication payload passes through the beam expansion component and the beam splitter in sequence and enters the color separation plate, and then is reflected by the color separation plate and enters the signal light receiving module; wherein the spatial light passing through the beam expansion component and entering the beam splitter is also reflected by the beam splitter and enters the monitoring camera;

[0008] The light emitted by the signal light emitting module passes through the piezoelectric ceramic fast reflection mirror, the color separation plate, the beam splitter and the beam expansion component in sequence;

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

[0010] The piezoelectric ceramic fast reflection mirror is used to adjust the emission direction of the signal light transmitting module and add interference to the emission light of the signal light transmitting module;

[0011] The signal receiving end of the communication machine is connected to the output end of the signal light receiving module, and the signal sending end of the communication machine is connected to the input end of the signal light transmitting module;

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

[0013] The measured space laser communication payload is arranged on a satellite.

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

[0017] A first receiving lens and a second receiving lens are sequentially arranged between the color separation plate 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 which are sequentially arranged between the piezoelectric ceramic fast reflection mirror and the signal light emitting module.

[0019] In one embodiment of the present invention, the signal light receiving module is a multi-mode receiving module; and 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 expansion assembly is 120 mm, and the maximum effective aperture of the measured space laser communication payload is 80 mm;

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

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

[0023] A second aspect of an embodiment of the present invention provides a portable space laser communication link establishment test method, which is applied to the test device provided by the first aspect of an embodiment of the present invention, and includes the following steps:

[0024] The space laser communication payload under test is turned on, and the positions of the space laser communication payload under test and the test device are adjusted until a light spot appears in the monitoring camera, and the centroid data is output to the industrial computer, and the space laser communication payload under test is turned off;

[0025] Turn on the piezoelectric ceramic fast mirror, flip the beam splitter, flip the surveillance camera, and adjust the position of the signal light transmitting module until the difference between the centroid coordinates of the calibrated emission light of the signal light transmitting module and the calibrated emission light of the signal light receiving module is less than or equal to the calibration threshold;

[0026] Reset the beam splitter and the surveillance camera, and rotate the piezoelectric ceramic fast mirror by 10 milliradians in any direction;

[0027] Turn on the space laser communication payload to be tested, start the capture mode until stable tracking, and obtain multiple center of mass coordinates within a preset time period;

[0028] Repeatedly shut down the space laser communication payload under test and rotate the piezoelectric ceramic fast reflection mirror 10 milliradians in any direction, turn on the space laser communication payload under test, start the capture mode until stable tracking, obtain multiple center of mass coordinates within the preset time period, and obtain the test results.

[0029] Beneficial effects of the present invention:

[0030] The present invention integrates the various units used into an integral device, which can be directly turned on and used, is convenient to use, and improves the test efficiency. At the same time, the structure is simple, and the tracking performance test of the tested space laser communication load can be performed, which increases the functionality and comprehensiveness of the test device.

[0031] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures particularly pointed out in the written description, claims, and drawings.

[0032] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0034] Figure 1 A schematic diagram of the structure of a portable space laser communication link establishment test device provided in an embodiment of the present invention. DETAILED DESCRIPTION

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

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

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

[0038] The uncertainty area refers to the initial pointing error caused by comprehensive factors such as target position solution, platform micro-vibration, and platform attitude instability. To compensate for this error, one end of the transmitter or receiver stares, and the other end scans according to a specific pattern in the uncertainty area relative to the staring end to achieve scanning capture;

[0039] Scanning capture means that the staring end maintains the initial pointing gaze, and the scanning end scans in the uncertain area according to a specific pattern until the staring end communication light appears on the scanning end detector, entering the capture and tracking stage;

[0040] Capture tracking means that after the scan is completed, a light spot appears on the detector, and the actual relative position and relative movement of the transmitter and receiver are reflected based on the centroid / centroid of the light spot, and then the tracking actuator is guided according to the position of the light spot to guide the beam of the other end into the communication field of view;

[0041] Stable tracking means using a tracking actuator to control the light beam within the communication field of view for a long time, with the received power higher than the minimum communication condition, thereby conducting space laser communication.

[0042] like Figure 1 As shown, the first aspect of the embodiment of the present invention provides a portable space laser communication link building test device, including: a beam expansion component 11, a signal light receiving module 12, a signal light transmitting module 13, a relay optical path component, a piezoelectric ceramic fast reflection mirror 16, a piezoelectric controller, a monitoring camera 17, a communication machine and an industrial computer. The relay optical path component includes: a beam splitter 14 and a color separation plate 15.

[0043] The beam expansion component 11, the beam splitter 14, the color separation plate 15, and the piezoelectric ceramic fast reflector 16 are coaxially arranged in sequence and spaced apart. The beam expansion component 11 is used to compress the divergence angle and increase the receiving aperture.

[0044] The spatial light emitted by the measured spatial laser communication payload passes through the beam expansion component 11 and the beam splitter 14 in sequence and enters the color separation plate 15, and then is reflected by the color separation plate 15 and enters the signal light receiving module 12. Here, the light incident on the color separation plate 15 and the beam splitter 14 is semi-transmitted and semi-reflected by the color separation plate 15 and the beam splitter 14.

[0045] Among them, the spatial light enters the beam splitter 14 through the beam expander 11 and is also reflected by the beam splitter 14 to enter 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 center of mass coordinates, and the other part passes through the beam splitter 14 into the color separation plate 15, and the color separation plate 15 is used to separate the signal receiving and emitting light, which are C46 and C18 respectively.

[0046] The light emitted by the signal light transmitting module 13 passes through the piezoelectric ceramic quick reflection mirror 16, the color separation plate 15, the beam splitter 14 and the beam expansion component 11 in sequence, and forms spatial light after beam expansion. Here, the light incident on the color separation plate 15 and the beam splitter 14 is transmitted by the color separation plate 15 and the beam splitter 14. The piezoelectric controller is connected to the piezoelectric ceramic quick reflection mirror 16. The piezoelectric ceramic quick reflection mirror 16 is used to adjust the emission direction of the signal light transmitting module 13 and add interference to the emission light of the signal light transmitting module 13, and when adding interference, it simulates the jitter of the light position caused by the micro-vibration of the measured end. The piezoelectric ceramic quick reflection mirror 16 rotates a certain arc to simulate the uncertain area. Here, the satellite will vibrate in the sky, so that the light emitted by the laser communication payload will shake, and the satellite will basically not vibrate in the sky on the ground during the test. Therefore, relatively speaking, the piezoelectric ceramic quick reflection mirror 16 adds disturbance to the light emitted from this end of the signal light transmitting module 13, so that the light position shakes, which is equivalent to the emission light of the measured space laser communication payload shaking.

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

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

[0049] In this embodiment, after the tested space laser communication load and the test device are adjusted to be coaxial, the test is started. The center of mass coordinates of the light spots generated by the signal light receiving module 12 and the signal light transmitting module 13 are monitored by the monitoring camera 17. By analyzing the center of mass coordinates, the test results such as the tracking capability and anti-interference capability of the tested space laser communication load are obtained.

[0050] Among them, the first camera lens and the second camera lens are arranged in sequence between the beam splitter 14 and the monitoring camera 17. The first receiving lens and the second receiving lens are arranged in sequence between the color separation plate 15 and the signal light receiving module 12. The first transmitting lens and the second transmitting lens are arranged in sequence between the piezoelectric ceramic fast 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 and pitch rotation centers of the space laser communication payload under test and the horizontal rotation center of the beam expander assembly 11 is less than 1.5m, the maximum aperture of the beam expander assembly 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 when it is rotated 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 uncertainty area of ​​10mrad in the case of poor link construction environment.

[0052] After the multi-mode receiving optical path is integrated with the beam expansion component 11, the overall F number is about 4.75, so that the adjusted coupling efficiency is relatively high. The flange can be adjusted at the optical fiber connection to change the coupling efficiency, thereby simulating the spatial attenuation caused by different communication distances. The test device of this embodiment is used for ground detection, and a wide range of piezoelectrics can be used, so that the piezoelectric ceramic fast mirror 16 can cover a variety of micro-vibration conditions, such as the NASDA vibration spectrum.

[0053] A second aspect of an embodiment of the present invention provides a portable space laser communication link establishment test method, which is applied to the test device of the first aspect of the embodiment of the present invention, and includes the following steps:

[0054] Step 201 , after the space laser communication payload to be tested is integrated with the satellite assembly, the signal light transmitting module 13 (single-mode signal light transmitting module) is connected to a laser of a corresponding wavelength, and the monitoring camera 17 is turned on.

[0055] Step 202, the space laser communication load under test is turned on, and the positions of the space laser communication load under test and the test device are adjusted until a light spot appears in the monitoring camera 17, and the centroid data is output to the industrial computer, and the space laser communication load under test is turned off.

[0056] In this step, the emission light of the measured space laser communication payload is adjusted to be coaxial with the beam expansion component 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 power in the optical path of the signal light receiving module 12 are calibrated as the receiving relative zero position.

[0057] Step 203, turn on the piezoelectric ceramic quick reflector 16 and flip the beam splitter 14. Figure 1 The monitoring camera 17 is flipped 180 degrees. Figure 1 The signal light transmitting module 13 is flipped upward according to the middle direction, and the position of the signal light transmitting module 13 is adjusted 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 spectrometer 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 transmitting module 13 are obtained, and the position of the signal light transmitting 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 mirror 16 by 10 milliradians in any direction to simulate an uncertain area in a poor link building environment.

[0060] In step 205, the space laser communication payload to be tested is turned on, beacon light (space light) is emitted, and the capture mode is turned on until stable tracking is achieved, and multiple centroid coordinates within a preset time period are obtained. The preset time period is a tracking period, and the jitter (displacement) of the tracking spot can be obtained based on the centroid coordinates within the tracking time period.

[0061] Step 206, shut down the space laser communication payload under test, and repeat steps 204 to 205.

[0062] Step 207, repeat step 206 to obtain the test result.

[0063] In this embodiment, the tracking accuracy and anti-interference ability can be obtained according to the jitter condition. For example, whether the displacement of the center of mass coordinate exceeds 5 micro-radians can be used to determine the tracking accuracy and anti-interference ability.

[0064] A third aspect of an embodiment of the present invention provides a portable space laser communication link establishment test method, using two test devices of the first aspect of the embodiment of the present invention and two tested space laser communication payloads, namely a first test device and a second test device, a first tested space laser communication payload and a second tested space laser communication payload. However, in this embodiment, there is no need to use an industrial computer and a communication machine, and the test results are obtained from a satellite and a tested space laser communication payload. The test 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: The first measured space laser communication load is turned on, and the positions of the first measured space laser communication load and the first test device are adjusted until a light spot appears in the monitoring camera 17, and the centroid data is output to the industrial computer, and the first measured space laser communication load is turned off. The second measured space laser communication load and the second test device are adjusted in the same manner.

[0067] In this step, the emission light of the measured space laser communication payload is adjusted to be coaxial with the beam expansion component 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 power in the optical path of the signal light receiving module 12 are calibrated as the receiving relative zero position.

[0068] Step 303, start the first measured space laser communication load and the second measured space laser communication load to start simulating a communication mode with space optical transmission.

[0069] Step 304, using the piezoelectric ceramic fast reflection mirror 16 to simulate the micro-vibration of the satellite platform, repeating step 303, and obtaining test results such as communication bit error rate, continuous working time, and communication rate from the satellite and the space laser communication payload under test.

[0070] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0071] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0072] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like 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.

[0073] 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.

[0074] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0075] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A portable space laser communication link building test device, characterized in that: include: Beam expansion components, signal light receiving modules, signal light transmitting modules, relay optical path components, piezoelectric ceramic fast-reflecting mirrors, piezoelectric controllers, surveillance cameras, communication machines and industrial computers; The relay optical path component includes: a beam splitter and a color splitter; The beam expansion component, the beam splitter, the color separation plate, and the piezoelectric ceramic fast reflector are coaxially arranged in sequence and spaced apart; The spatial light emitted by the measured spatial laser communication payload passes through the beam expansion component and the beam splitter in sequence and enters the color separation plate, and then is reflected by the color separation plate and enters the signal light receiving module; wherein the spatial light passing through the beam expansion component and entering the beam splitter is also reflected by the beam splitter and enters the monitoring camera; The light emitted by the signal light emitting module passes through the piezoelectric ceramic fast reflection mirror, the color separation plate, the beam splitter and the beam expansion component in sequence; The piezoelectric controller is connected to the piezoelectric ceramic fast reflection mirror; The piezoelectric ceramic fast reflection mirror is used to adjust the emission direction of the signal light transmitting module and add interference to the emission light of the signal light transmitting module; The signal receiving end of the communication machine is connected to the output end of the signal light receiving module, and the signal sending end of the communication machine is connected to the input end of the signal light transmitting module; The communication machine and the monitoring camera are electrically connected to the industrial computer; The measured space laser communication payload is arranged on a satellite.

2. The device according to claim 1, characterized in that Also includes: A first camera lens and a second camera lens are sequentially disposed between the beam splitter and the monitoring camera.

3. The device according to claim 2, characterized in that Also includes: A first receiving lens and a second receiving lens are sequentially arranged between the color separation plate and the signal light receiving module.

4. The device according to claim 2, characterized in that Also includes: A first emitting lens and a second emitting lens are sequentially arranged between the piezoelectric ceramic fast reflection mirror and the signal light emitting module.

5. The device according to claim 1, characterized in that The signal light receiving module is a multi-mode receiving module; the signal light transmitting module is a single-mode transmitting module.

6. The device according to claim 1, characterized in that The maximum aperture of the beam expansion assembly is 120 mm, and the maximum effective aperture of the measured space laser communication payload is 80 mm; The maximum distance between the azimuth and elevation rotation centers of the measured space laser communication payload and the horizontal rotation center of the beam expansion assembly is 1.5 m.

7. The device according to claim 1, characterized in that The monitoring camera is a CCD camera.

8. A portable space laser communication link building test method, characterized in that: The test device as claimed in claim 1 comprises the following steps: The space laser communication payload under test is turned on, and the positions of the space laser communication payload under test and the test device are adjusted until a light spot appears in the monitoring camera, and the centroid data is output to the industrial computer, and the space laser communication payload under test is turned off; Turn on the piezoelectric ceramic fast mirror, flip the beam splitter, flip the surveillance camera, and adjust the position of the signal light transmitting module until the difference between the centroid coordinates of the calibrated emission light of the signal light transmitting module and the calibrated emission light of the signal light receiving module is less than or equal to the calibration threshold; Reset the beam splitter and the surveillance camera, and rotate the piezoelectric ceramic fast mirror by 10 milliradians in any direction; Turn on the space laser communication payload to be tested, start the capture mode until stable tracking, and obtain multiple center of mass coordinates within a preset time period; Repeatedly shut down the space laser communication payload under test and rotate the piezoelectric ceramic fast reflection mirror 10 milliradians in any direction, turn on the space laser communication payload under test, start the capture mode until stable tracking, obtain multiple center of mass coordinates within the preset time period, and obtain the test results.

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