Semi-physical simulation device and method for dynamic capture and tracking test of laser load

Abstract

A novel semi-physical simulation device and method for dynamic tracking test of laser payloads belongs to the field of space laser communication technology. The beam divergence angle of space laser communication payloads is small, and it is difficult to establish and maintain a space bidirectional laser link. It requires extremely high pointing accuracy, dynamic capture capability and tracking capability, and accurate and effective simulation needs to be carried out on the ground. Based on the characteristics of on-orbit tracking and link establishment of current space laser communication payloads, the present invention realizes the simulation of the ephemeris, attitude change, orbit positioning error, attitude error, and time synchronization error of the dual-satellite link of the intersatellite dual-end satellite platform. And through the focal plane self-collimation and fiber drive system, the micro-vibration simulation and the elimination of the environmental disturbance of the simulation platform are realized. At the same time, the dynamic simulation of the visible star map of the laser payload is carried out based on the satellite orbit and attitude changes. The present invention realizes the effective simulation of the intersatellite bidirectional narrow beam laser scanning tracking process on the ground, and ensures the reliability of the dynamic test environment of the laser communication payload and the interface injection data simulation. The device and related methods can be applied to the ground tracking simulation verification and semi-physical simulation of space laser payloads such as dynamic tracking test of space laser communication, link establishment of dual-satellite laser communication, and laser ATP.

Description

Technical Field

[0001] The invention relates to the technical field of space laser communication, in particular to a semi-physical simulation device and method for dynamic capture and tracking test of laser load. Background Art

[0002] Due to the advantages of large communication capacity, low resource consumption and good confidentiality, space laser communication technology has developed rapidly in the past two decades. The United States, Europe, Russia, Japan and my country have all carried out on-orbit technical tests. In recent years, with the construction of satellite Internet, the demand for space laser communication has become more urgent. Compared with microwave communication and ground optical fiber communication, the main difficulty of space laser communication technology is the difficulty of laser link capture and tracking. Since the beam angle of the laser beam is only a few to a dozen arc seconds, in order to establish a laser link between satellites thousands or even tens of thousands of kilometers apart, the pointing and tracking accuracy of the laser payload is required to be extremely high. Since the satellite platform moves with the orbit and has variable acceleration motion with attitude, the angular velocity of relative motion between satellites reaches several thousand arc seconds / s. To establish an intersatellite link, the laser payload has high requirements for the ephemeris prediction value, attitude measurement value and time value input by the platform. Before launching, the laser payload needs to carry out sufficient ground capture and tracking test verification according to the specific characteristics of the satellite platform. It is necessary to establish a high-stability test simulation platform on the ground to eliminate external environmental interference and have simulation functions such as platform dynamic motion trajectory, attitude error, and time error input. Summary of the invention

[0003] The purpose of the present invention is to provide a semi-physical simulation device and method for dynamic tracking test of laser payload, suppress the influence of environmental vibration under ground semi-physical simulation conditions, simulate the motion trajectory, attitude error, time error, etc. of the space satellite moving platform, and study the long-distance dynamic tracking and link establishment process of laser payload with narrow beam angle.

[0004] To solve the above problems, the technical solutions of the present invention are as follows:

[0005] On the one hand, the present invention provides a semi-physical simulation device for dynamic capture and tracking test of laser load, which is characterized in that it includes: a signal laser, a focal plane fiber transmitter, a beam splitter, a collimator, a monitoring camera, a piezoelectric fiber controller, a two-dimensional turntable for placing the laser load and a reference prism, a star sensor arranged on the laser load rotation mechanism, a dynamic star model, a slip ring interface, a star model controller, a load control simulator, and a turntable controller;

[0006] The signal laser injects a light beam into the focal plane fiber transmitter, and the light beam emitted by the focal plane fiber transmitter is incident on the collimator through the beam splitter, and then converted into parallel light and incident on the laser load and the reference prism, wherein the reflected light reflected by the reference prism returns along the original path and is incident on the monitoring camera to generate a self-collimated light spot, and the position change of the light spot minus the current micro-vibration simulation amount is the external environmental disturbance to the simulation device;

[0007] The monitoring camera is located at the focal plane of the collimator, and is used to capture the light spot position information of the tracking link, and analyze and feed back the light spot position jitter to the piezoelectric optical fiber controller;

[0008] The piezoelectric optical fiber controller is used to drive the optical fiber end face position of the focal plane optical fiber transmitter to achieve beam pointing correction;

[0009] The laser payload is used to simulate the dynamic changes of the satellite platform, and through the stellar orientation effect of the star sensor, the pointing accuracy of the laser payload is improved, and the installation coordinate system error of the laser payload and the satellite platform and the rotation mechanism error of the laser payload are corrected;

[0010] The dynamic star model is fixed at the optical entrance of the star sensor and is used to simulate a dynamically changing star map;

[0011] The external cables of the laser load and the dynamic star model are respectively connected to the external star model controller and the load control simulator through the slip ring interface of the two-dimensional turntable;

[0012] The turntable controller is connected to the two-dimensional turntable and the star model controller respectively;

[0013] The payload control simulator injects the turntable trajectory into the turntable controller according to the satellite orbit change and attitude change, and the turntable controller controls the two-dimensional turntable to simulate the on-orbit dynamic changes of the satellite platform;

[0014] The star model controller receives the platform dynamic change trajectory input by the load control simulator, generates a star map corresponding to the dynamic change, and inputs it to the dynamic star model. The dynamic star model generates a corresponding star map on the focal plane of its internal optical system, converts it into parallel light output through the optical system, and is received by the star sensor;

[0015] The timing controller provides unified timing for the star model controller, payload control simulator and turntable controller, and provides 1PPS second pulse as a reference to achieve simulation of the unified time system of the satellite platform.

[0016] The star-sensing device of the laser payload observes dynamic star images that are consistent with on-orbit changes, providing pointing input information for tracking and link building of the laser payload.

[0017] The piezoelectric fiber controller can drive the position of the focal plane fiber transmitter by injecting specified power spectrum data. The position change of the fiber end face on the focal plane of the collimator is converted into a change in the pointing angle of the external parallel light, thereby simulating the micro-vibration of the satellite platform.

[0018] On the other hand, the present invention also provides a semi-physical simulation method for dynamic capture and tracking test of laser payload, which is characterized in that two sets of semi-physical simulation devices for dynamic capture and tracking test of laser payload described above are used, and the two sets of focal plane fiber optic transmitters are connected by optical fiber to perform dynamic capture and tracking link building model between two satellites.

[0019] Furthermore, a common timing controller is used to control the timing errors of two sets of star model controllers, payload control simulators and turntable controllers respectively, so as to simulate the on-orbit time synchronization errors of the two satellites, thereby verifying the adaptability of the inter-satellite tracking function of the laser payload to different satellite time synchronization errors.

[0020] Compared with the prior art, the technical effects of the present invention are:

[0021] 1) Adopting focal plane self-collimation and benchmark real-time monitoring correction, the piezoelectric fiber drive system is used to compensate for the change of the optical axis benchmark in real time, eliminate the environmental interference of the simulation platform, and ensure the accuracy of the test input conditions;

[0022] 2) The payload control simulator injects the turntable trajectory into the turntable controller according to the satellite orbit change and attitude change, so that the two-dimensional turntable simulates the dynamic changes of the satellite platform on orbit. On this basis, the payload controller superimposes the orbit positioning error and platform attitude control error on the ideal motion curve to verify the adaptability of the laser payload's tracking performance to different platform conditions on orbit.

[0023] 3) The star model controller receives the platform dynamic change trajectory input by the payload controller, generates a star map corresponding to the dynamic change, and inputs it to the dynamic star model. The dynamic star model generates a corresponding star map on the focal plane of its internal optical system, which is converted into parallel light output through the optical system and received by the star sensor. Thus, the star sensor of the laser payload observes a dynamic star image consistent with the on-orbit change, providing pointing input information for the tracking and link establishment of the laser payload.

[0024] 4) The piezoelectric fiber controller can drive the position of the optical fiber transmitter on the focal plane by injecting the specified power spectrum data. As for the position change of the optical fiber end face on the focal plane of the collimator, it converts the pointing angle change of the external parallel light into the change, thereby simulating the micro-vibration of the satellite platform;

[0025] 5) Connect the focal plane fiber transmitters of the two devices through optical fiber, and then the dual-satellite dynamic tracking and link building simulation can be performed. The two sets of semi-physical simulation devices for the dynamic tracking test of the laser payload share a timing controller, which controls the timing time error of the star model controller, payload control simulator and turntable controller in the two sets of devices, and can simulate the on-orbit time synchronization error of the two satellites, thereby verifying the adaptability of the inter-satellite tracking function of the laser payload to different satellite time synchronization errors. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of a semi-physical simulation device for the dynamic tracking test of the laser load of the present invention. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the scheme of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0028] See also Figure 1 , Figure 1 It is a semi-physical simulation device and method for dynamic capture and tracking test of laser loads of the present invention. As can be seen from the figure, a semi-physical simulation device and method for dynamic capture and tracking test of laser loads includes a signal laser 1, a focal plane fiber transmitter 2, a beam splitter 3, a collimator 4, a monitoring camera 5, a piezoelectric fiber controller 6, a two-dimensional turntable 8 for placing the laser load 7, a star sensor 9 arranged on the rotating mechanism of the laser load 7, a dynamic star model 10, a slip ring interface 11, a star model controller 12, a load control simulator 13 and a turntable controller 14;

[0029] The signal laser 1 injects a light beam into the focal plane fiber transmitter 2. The emitted light beam enters the collimator 4 through the beam splitter 3. There is also a monitoring camera 5 on the focal plane of the collimator 4 to capture and analyze the light spot position characteristics of the link. The light spot position information of the monitoring camera 5 can be fed back to the piezoelectric fiber controller 6 for driving the fiber end face position of the focal plane fiber transmitter 2. The emitted light beam is converted into parallel light by the collimator 4 and received by the laser payload 7. The device is installed on the two-dimensional turntable 8 and is used to simulate the dynamic changes of the satellite platform. The laser payload 7 is installed with a star sensor 9. The star sensor 9 is different from the star sensor on the conventional satellite platform. Instead, it is an independent star sensor installed on the rotating mechanism of the laser payload 7. The star orientation effect of the star sensor 9 can greatly improve the pointing accuracy of the laser payload 7, and correct the installation coordinate system error of the laser payload 7 and the satellite platform and the rotation mechanism error of the laser payload 7. A dynamic star module 10 is installed at the optical entrance of the star sensor 9. The device is used to simulate the dynamically changing star map. The external cables of the laser payload 7 and the dynamic star model 10 are connected to the external star model controller 12 and the load control simulator 13 respectively through the slip ring interface 11 on the two-dimensional turntable 8. The control of the two-dimensional turntable 8 is realized by the external turntable controller 14. The timing controller 15 performs unified timing for the star model controller 12, the load control simulator 13 and the turntable controller 14, and provides 1PPS second pulse as a reference to realize the simulation of the unified time system of the satellite platform. The tracking and link building effect of the laser payload 7 under the dynamic input environment generated by the above equipment is judged and counted by the position of the load emission spot on the monitoring camera 5. At the same time, the focal plane fiber transmitter 2 on the monitoring camera 5 emits the self-collimated return light of the reference prism 16. The position calculation of the self-collimated return light spot can obtain the jitter of the simulation platform, and the jitter of the light spot position is fed back to the piezoelectric fiber controller 6 to correct the jitter error of the simulation platform.

[0030] The payload control simulator 13 injects the turntable trajectory into the turntable controller 14 according to the satellite orbit change and attitude change, so that the two-dimensional turntable 8 simulates the dynamic change of the satellite platform on orbit. On this basis, the turntable controller 14 superimposes the orbit positioning error and the platform attitude control error on the ideal motion curve, thereby verifying the adaptability of the tracking performance of the laser payload 7 to different working conditions of the platform on orbit.

[0031] The star model controller 12 receives the platform dynamic change trajectory input by the turntable controller 14, generates a star map corresponding to the dynamic change, and inputs it to the dynamic star model 10. The dynamic star model 10 generates a corresponding star map on the focal plane of its internal optical system, converts it into parallel light output through the optical system, and is received by the star sensor 9. Thus, the star sensor 9 of the laser payload 7 observes a dynamic star image consistent with the on-orbit change, providing pointing input information for the tracking and link establishment of the laser payload 7.

[0032] The piezoelectric fiber controller 6 can drive the position of the focal plane fiber transmitter 2 by injecting the specified power spectrum data. As for the position change of the fiber end face on the focal plane of the collimator 4, it converts the pointing angle change of the external parallel light into the change, thereby simulating the micro-vibration of the satellite platform.

[0033] The emitted light of the focal plane fiber optic transmitter 2 passes through the collimator 4 and is incident on the reference prism 16 fixed on the base of the two-dimensional turntable 8. The reflected light on its surface returns to the monitoring camera 5 along the original path, generating a self-collimated light spot. The position change of the light spot minus the current micro-vibration simulation represents the external environmental disturbance to the entire simulation device. Since it is reflected light, the light spot is very sensitive to external disturbances. The light spot position jitter is fed back to the piezoelectric fiber optic controller 6 to control the focal plane fiber optic transmitter 2 to correct the beam pointing, thereby compensating for the external environmental disturbance.

[0034] The above two sets of semi-physical simulation devices for dynamic tracking test of laser payload are operated simultaneously, and the focal plane fiber transmitters 2 of the two sets of devices are connected through optical fiber, so that the dual-satellite dynamic tracking and link establishment simulation can be performed. The two sets of semi-physical simulation devices for dynamic tracking test of laser payload share a timing controller 15, which controls the timing time error of the star model controller 12, the payload control simulator 13 and the turntable controller 14 in the two sets of devices, and can simulate the on-orbit time synchronization error of the two satellites, so as to test the adaptability of the inter-satellite tracking function of the laser payload 7 to the time synchronization error of different satellites.

[0035] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A semi-physical simulation device for dynamic capture and tracking test of laser load, characterized by: It comprises a signal laser (1), a focal plane fiber transmitter (2), a beam splitter (3), a collimator (4), a monitoring camera (5), a piezoelectric fiber controller (6), a two-dimensional turntable (8) for placing a laser load (7) and a reference prism (16), a star sensor (9) arranged on a rotating mechanism of the laser load (7), a dynamic star model (10), a slip ring interface (11), a star model controller (12), a load control simulator (13), and a turntable controller (14); The signal laser (1) injects a light beam into the focal plane fiber transmitter (2), and the light beam emitted by the focal plane fiber transmitter (2) is transmitted through the beam splitter (3) and incident on the collimator (4), and then converted into parallel light and incident on the laser load (7) and the reference prism (16), wherein the reflected light reflected by the reference prism (16) returns along the original path and is incident on the monitoring camera (5), generating a self-collimated light spot, and the position change of the light spot minus the current micro-vibration simulation amount is the external environmental disturbance to which the simulation device is subjected; The monitoring camera (5) is located at the focal plane of the collimator (4) and is used to capture the light spot position information of the tracking link, analyze and feed back the light spot position jitter to the piezoelectric optical fiber controller (6); The piezoelectric optical fiber controller (6) is used to drive the optical fiber end face position of the focal plane optical fiber transmitter (2) to achieve beam pointing correction; The laser payload (7) is used to simulate the dynamic changes of the satellite platform, and through the star orientation effect of the star sensor (9), the pointing accuracy of the laser payload (7) is improved, and the installation coordinate system error of the laser payload (7) and the satellite platform and the rotation mechanism error of the laser payload (7) are corrected; The dynamic star model (10) is fixed at the optical entrance of the star sensor (9) and is used to simulate a dynamically changing star map; The external cables of the laser load (7) and the dynamic star model (10) are respectively connected to an external star model controller (12) and a load control simulator (13) through a slip ring interface (11) of the two-dimensional turntable (8); The turntable controller (14) is connected to the two-dimensional turntable (8) and the star model controller (12) respectively; The payload control simulator (13) injects a turntable trajectory into a turntable controller (14) according to satellite orbit changes and attitude changes, and the turntable controller (14) controls the two-dimensional turntable (8) to simulate the on-orbit dynamic changes of the satellite platform; The star model controller (12) receives the platform dynamic change trajectory input by the load control simulator (13), generates a star map corresponding to the dynamic change, and inputs it to the dynamic star model (10). The dynamic star model (10) generates a corresponding star map on the focal plane of its internal optical system, converts it into parallel light output through the optical system, and is received by the star sensor (9); The timing controller (15) provides unified timing for the star model controller (12), the load control simulator (13) and the turntable controller (14), and provides 1PPS second pulse as a reference to achieve simulation of the unified time system of the satellite platform.

2. The semi-physical simulation device for dynamic capture and tracking test of laser load according to claim 1 is characterized in that: The star sensor (9) of the laser payload (7) observes a dynamic star image that is consistent with the on-orbit changes, and provides pointing input information for tracking and link building of the laser payload (7).

3. The semi-physical simulation device for dynamic capture and tracking test of laser load according to claim 1, characterized in that: The piezoelectric optical fiber controller (6) can drive the position of the focal plane optical fiber transmitter (2) by injecting designated power spectrum data. The position change of the optical fiber end face on the focal plane of the collimator (4) is converted into a change in the pointing angle of the external parallel light, thereby simulating the micro-vibration of the satellite platform.

4. A semi-physical simulation method for dynamic capture and tracking test of laser load, characterized in that: Two sets of semi-physical simulation devices for dynamic capture and tracking test of laser payloads as described in any one of claims 1 to 3 are used, and two sets of focal plane optical fiber transmitters (2) are connected via optical fibers to perform dynamic capture and tracking link building model between two satellites.

5. The semi-physical simulation method for dynamic capture and tracking test of laser load according to claim 4 is characterized in that: A common timing controller (15) is used to control the timing errors of two sets of star model controllers (12), payload control simulators (13) and turntable controllers (14) respectively, so as to simulate the on-orbit time synchronization errors of two satellites, thereby testing the adaptability of the inter-satellite tracking function of the laser payload (7) to different satellite time synchronization errors.

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