CN115173920A - Semi-physical simulation device and method for dynamic capture tracking test of laser load - Google Patents
Semi-physical simulation device and method for dynamic capture tracking test of laser load Download PDFInfo
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- CN115173920A CN115173920A CN202210706289.3A CN202210706289A CN115173920A CN 115173920 A CN115173920 A CN 115173920A CN 202210706289 A CN202210706289 A CN 202210706289A CN 115173920 A CN115173920 A CN 115173920A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/50—Transmitters
- H04B10/501—Structural aspects
- H04B10/503—Laser transmitters
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/30—Monitoring; Testing of propagation channels
- H04B17/391—Modelling the propagation channel
- H04B17/3912—Simulation models, e.g. distribution of spectral power density or received signal strength indicator [RSSI] for a given geographic region
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04J—MULTIPLEX COMMUNICATION
- H04J3/00—Time-division multiplex systems
- H04J3/02—Details
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- H04J3/0638—Clock or time synchronisation among nodes; Internode synchronisation
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Abstract
A novel semi-physical simulation device and method for dynamic capture and tracking test of laser load belong to the technical field of space laser communication. The space laser communication load beam divergence angle is small, the difficulty of establishing and maintaining a space bidirectional laser link is high, extremely high pointing precision, dynamic capturing capability and tracking capability are required, and accurate and effective simulation needs to be carried out on the ground. The method is based on the characteristics of on-orbit acquisition and link establishment of the current space laser communication load, and can be used for simulating ephemeris, attitude change, orbit positioning error, attitude error and double-intersatellite link time synchronization error of the intersatellite double-end satellite platform. And the elimination of the micro-vibration simulation and the environmental disturbance of the simulation platform is realized through the focal plane self-collimation and the optical fiber driving system. And simultaneously, the dynamic simulation of the laser load visual star atlas is carried out based on the satellite orbit and attitude change. The invention realizes effective simulation of the inter-satellite bidirectional narrow-beam laser scanning capture and tracking process on the ground, and ensures the reliability of dynamic test environment of laser communication load and simulation of interface injection data. The device and the related method can be suitable for dynamic capture and tracking test of space laser communication, double-intersatellite laser communication link establishment, ground capture and tracking simulation verification and semi-physical simulation of space laser loads such as laser ATP and the like.
Description
Technical Field
The invention relates to the technical field of space laser communication, in particular to a semi-physical simulation device and method for dynamic capture tracking test of laser load.
Background
Since the space laser communication technology has the advantages of large communication capacity, low resource consumption, good confidentiality and the like, the space laser communication technology is rapidly developed in the last two decades, and on-track technical tests are developed in the United states, europe, russia, japan and China. In recent years, with the construction of satellite internet, the demand for space laser communication is more urgent. Compared with microwave communication and ground optical fiber communication, the main difficulty of the space laser communication technology is that the laser link is difficult to capture and track. Since the beam angle of the laser beam is only a few to a dozen angular seconds, extremely high pointing and tracking accuracy of the laser load is required to establish a laser link between satellites distant from several kilometers or even tens of kilometers. Because the satellite platform moves along with the orbit and moves with the attitude variable acceleration, the inter-satellite relative movement angular velocity reaches thousands of angular seconds/s, and the laser load has higher requirements on ephemeris forecast values, attitude measurement values and time values input by the platform when an inter-satellite link is established. The laser load needs to be fully verified by ground tracking tests according to the specific characteristics of the satellite platform before being transmitted, a high-stability test simulation platform needs to be established on the ground, external environment interference is eliminated, and the simulation functions of platform dynamic motion track, attitude error, time error input and the like are achieved.
Disclosure of Invention
The invention aims to provide a semi-physical simulation device and a semi-physical simulation method for a laser load dynamic capture and tracking test, which are used for inhibiting the influences of environmental vibration and the like under the ground semi-physical simulation condition, simulating the motion track, attitude error, time error and the like of a space satellite moving platform and researching the laser load remote dynamic capture and tracking link building process with a narrow beam angle.
In order to solve the above problems, the technical solution of the present invention is as follows:
on one hand, the invention provides a semi-physical simulation device for dynamic capture tracking test of laser load, which is characterized in that: the system comprises a signal laser, a focal plane optical fiber transmitter, a beam splitter, a collimator, a monitoring camera, a piezoelectric optical fiber controller, a two-dimensional turntable for placing a laser load and a reference prism, a star sensor, a dynamic star model, a slip ring interface, a star model controller, a load control simulator and a turntable controller, wherein the star sensor, the dynamic star model, the slip ring interface, the star model controller, the load control simulator and the turntable controller are arranged on a laser load rotating mechanism;
the signal laser injects light beams into the focal plane optical fiber transmitter, the light beams transmitted by the focal plane optical fiber transmitter are converted into parallel light after penetrating through a light splitter and then are injected into the collimator, the parallel light is injected into the laser load and the reference prism, wherein reflected light reflected by the reference prism returns to the monitoring camera along the original path to generate a self-collimating light spot, and the position change of the light spot deducts the current micro-vibration analog quantity, namely the external environment disturbance received by the simulation device;
the monitoring camera is positioned on the focal plane of the collimator and is used for capturing the light spot position information of the link, analyzing and feeding back the light spot position jitter amount to the piezoelectric optical fiber controller;
the piezoelectric optical fiber controller is used for driving the optical fiber end face position of the focal plane optical fiber emitter to realize beam pointing correction;
the laser load is used for simulating the dynamic change of the satellite platform, improving the pointing accuracy of the laser load through the fixed star orientation effect of the star sensor, and correcting the laser load, the error of an installation coordinate system of the satellite platform and the error of a rotating mechanism of the laser load;
the dynamic star model is fixed at an optical inlet of the star sensor and used for simulating a dynamically changed fixed star map;
the laser load and the external cables of the dynamic star model are respectively connected with an external star model controller and a load control simulator through a slip ring interface of the two-dimensional rotary table;
the turntable controller is respectively connected with the two-dimensional turntable and the star model controller;
the load control simulator injects a rotary table track into the rotary table controller according to the satellite track change and the attitude change, and the rotary table controller controls the two-dimensional rotary table to simulate the on-orbit dynamic change of the satellite platform;
the star model controller receives the platform dynamic change track input by the load control simulator, generates a fixed star diagram corresponding to dynamic change, and inputs the fixed star diagram to the dynamic star model, and the dynamic star model generates a corresponding fixed star diagram on the focal plane of an internal optical system of the dynamic star model, converts the fixed star diagram into parallel light through the optical system, outputs the parallel light and receives the parallel light by the star sensor;
the time service controller is used for carrying out unified time service on the satellite model controller, the load control simulator and the rotary table controller, and providing 1PPS (pulse per second) as a reference, so that the satellite platform is simulated uniformly and uniformly.
The star sensor of the laser load observes a dynamic star image consistent with the on-orbit change, and provides directional input information for capturing, following and building a link of the laser load.
The piezoelectric optical fiber controller can realize the driving of the position of the focal plane optical fiber emitter by injecting specified power spectrum data, and the change of the position of the optical fiber end surface on the focal plane of the collimator converts the change of the pointing angle of non-outward parallel light, thereby simulating the micro-vibration of a satellite platform.
On the other hand, the invention also provides a semi-physical simulation method for the dynamic capture tracking test of the laser load, which is characterized in that two sets of semi-physical simulation devices for the dynamic capture tracking test of the laser load are adopted, and two sets of focal plane optical fiber transmitters are connected through optical fibers to carry out dynamic capture and link building between two satellites.
Furthermore, one shared time service controller is adopted to respectively control the time service errors of the two sets of the satellite mode controller, the load control simulator and the rotary table controller, so that the on-orbit time synchronization errors of two satellites are simulated, and the adaptability of the inter-satellite tracking function of the laser load to different satellite time synchronization errors is tested.
Compared with the prior art, the invention has the technical effects that:
1) Focal plane self-collimation and reference real-time monitoring correction are adopted, the change of the optical axis reference is compensated in real time through a piezoelectric optical fiber driving system, the environmental interference on a simulation platform is eliminated, and the accuracy of test input conditions is guaranteed;
2) And the load control simulator injects a turntable track into the turntable controller according to the satellite orbit change and the attitude change, so that the two-dimensional turntable simulates the on-orbit dynamic change of the satellite platform. On the basis, the load controller superposes a track positioning error and a platform attitude control error on an ideal motion curve, so that the adaptability of the tracking performance of the laser load to different working conditions of the platform on the track is verified.
3) The star model controller receives the platform dynamic change track input by the load controller, generates a star map corresponding to dynamic change, inputs the star map to the dynamic star model, generates a corresponding star map on the focal plane of an internal optical system of the dynamic star model, converts the star map into parallel light through the optical system, and outputs the parallel light to be received by the star sensor. Therefore, the star sensor of the laser load observes a dynamic star image consistent with the on-orbit change, and directional input information is provided for capturing, following and building a link of the laser load.
4) The piezoelectric optical fiber controller can realize the driving of the position of the focal plane optical fiber emitter by injecting specified power spectrum data, and the change of the position of the optical fiber end surface on the focal plane of the collimator is converted into the change of the pointing angle of non-outward parallel light, so that the micro-vibration of the satellite platform is simulated;
5) The focal plane optical fiber emitters of the two sets of devices are connected through optical fibers, and then dynamic capturing, tracking and chain building simulation between double stars can be carried out. The two sets of laser load dynamic capturing and testing semi-physical simulation devices share one time service controller, the time service controller controls time service errors of the satellite model controllers, the load control simulator and the turntable controller in the two sets of devices, and the on-orbit time synchronization errors of two satellites can be simulated, so that the adaptability of the inter-satellite capturing and tracking function of the laser load to different satellite time synchronization errors is tested.
Drawings
FIG. 1 is a schematic diagram of a semi-physical simulation device for a dynamic capture and tracking test of laser load.
Detailed Description
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, fig. 1 is a diagram illustrating a semi-physical simulation apparatus and method for a laser load dynamic capture tracking test according to the present invention. It can be seen from the figure that a semi-physical simulation device and method for dynamic capture tracking test of laser load comprises a signal laser 1, a focal plane optical fiber emitter 2, a beam splitter 3, a collimator 4, a monitoring camera 5, a piezoelectric optical fiber controller 6, a two-dimensional turntable 8 for placing a laser load 7, 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 light beams into the focal plane optical fiber transmitter 2, the emitted light beams enter the collimator 4 through the light splitter 3, a monitoring camera 5 is arranged on the focal plane of the collimator 4 to analyze the spot position characteristics of the capturing link, and the spot position information of the monitoring camera 5 can be fed back to the piezoelectric optical fiber controller 6 to drive the optical fiber end face position of the focal plane optical fiber transmitter 2. The emitted light beams are converted into parallel light through the collimator 4 and received by a laser load 7, and the device is installed on a two-dimensional rotary table 8 and used for simulating the dynamic change of a satellite platform. The laser load 7 is provided with a star sensor 9, and the star sensor 9 is different from a star sensor on a conventional satellite platform, but is an independent star sensor arranged on a rotating mechanism of the laser load 7. The pointing accuracy of the laser load 7 can be greatly improved through the fixed star orientation effect of the star sensor 9, and the errors of the laser load 7, the installation coordinate system of the satellite platform and the rotating mechanism of the laser load 7 are corrected. At the optical entrance of the star sensor 9 is mounted a dynamic star model 10, which is used to simulate a dynamically changing star atlas. The laser load 7 and the external cables of the dynamic star model 10 are respectively connected with an external star model controller 12 and a load control simulator 13 through a slip ring interface 11 on the two-dimensional rotary table 8. The two-dimensional turntable 8 is controlled by an external turntable controller 14. The time service controller 15 performs unified time service on the satellite model controller 12, the load control simulator 13 and the turntable controller 14, and provides 1PPS (pulse per second) as a reference, so that unified and unified simulation on the satellite platform is realized. The capturing, tracking and chain building effects of the laser load 7 under the dynamic input environment generated by the equipment are interpreted and counted by monitoring the position of a load emission light spot on the camera 5. Meanwhile, the monitoring camera 5 is also provided with a focal plane optical fiber emitter 2 which emits auto-collimation return light which passes through a reference prism 16, the jitter amount of the simulation platform can be obtained by calculating the position of an auto-collimation return light spot, and the jitter amount of the light spot position is fed back to the piezoelectric optical fiber controller 6 to correct the jitter error of the simulation platform.
The load control simulator 13 injects a turntable track into the turntable controller 14 according to the satellite orbit change and the attitude change, so that the two-dimensional turntable 8 simulates the on-orbit dynamic change of a satellite platform. On the basis, the turntable controller 14 superimposes a track positioning error and a platform attitude control error on an ideal motion curve, so that the adaptability of the tracking performance of the laser load 7 to different working conditions of the platform on the track is verified.
The star model controller 12 receives the platform dynamic change track input by the turntable controller 14, generates a star map corresponding to dynamic change, inputs the star map to the dynamic star model 10, and the dynamic star model 10 generates the corresponding star map on the focal plane of the internal optical system thereof, converts the star map into parallel light through the optical system, and outputs the parallel light which is received by the star sensor 9. Therefore, the star sensor 9 of the laser load 7 observes a dynamic star image consistent with the on-orbit change, and provides directional input information for capturing, tracking and building a chain of the laser load 7.
The piezoelectric optical fiber controller 6 can realize the driving of the position of the focal plane optical fiber emitter 2 by injecting specified power spectrum data, and the change of the position of the optical fiber end surface on the focal plane of the collimator 4 converts the change of the pointing angle of non-outward parallel light so as to simulate the micro-vibration of a satellite platform;
the emitted light of the focal plane optical fiber emitter 2 is incident to a reference prism 16 fixed on a base of a two-dimensional turntable 8 after passing through a collimator 4, and the surface reflected light returns to a monitoring camera 5 in the original way to generate auto-collimation light spots; the change of the position of the light spot deducts the current micro-vibration analog quantity, and represents the external environment disturbance of the whole simulation device. The light spot is sensitive to external disturbances due to the reflected return light. The spot position jitter amount is fed back to the piezoelectric optical fiber controller 6, and the focal plane optical fiber emitter 2 is controlled to perform beam pointing correction, so that external environment disturbance is compensated.
The two sets of laser load dynamic trapping and testing semi-physical simulation devices work simultaneously, and focal plane optical fiber transmitters 2 of the two sets of devices are connected through optical fibers, so that double-intersatellite dynamic trapping and link building simulation can be carried out. The two sets of laser load dynamic capturing and testing semi-physical simulation devices share one time service controller 15, the time service controller 15 controls time service errors of the star model controller 12, the load control simulator 13 and the rotary table controller 14 in the two sets of devices, and the on-orbit time synchronization errors of two satellites can be simulated, so that the adaptability of the inter-satellite capturing and testing function of the laser load 7 to different satellite time synchronization errors is tested.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (5)
1. A semi-physical simulation device for dynamic capture tracking test of laser load is characterized in that: the device comprises a signal laser (1), a focal plane optical fiber transmitter (2), a beam splitter (3), a collimator (4), a monitoring camera (5), a piezoelectric optical 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 light beams into the focal plane optical fiber transmitter (2), the light beams transmitted by the focal plane optical fiber transmitter (2) penetrate through the light splitter (3) and are then transmitted into the collimator (4) and then are converted into parallel light to be transmitted into 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 transmitted into the monitoring camera (5) to generate a self-collimating light spot, and the position change of the light spot deducts the current micro-vibration analog quantity, namely the external environment disturbance of the simulation device;
the monitoring camera (5) is positioned on the focal plane of the collimator (4) and is used for capturing the light spot position information of the link, analyzing and feeding back the light spot position jitter amount to the piezoelectric optical fiber controller (6);
the piezoelectric optical fiber controller (6) is used for driving the optical fiber end face position of the focal plane optical fiber emitter (2) to realize beam pointing correction;
the laser load (7) is used for simulating the dynamic change of a satellite platform, improving the pointing accuracy of the laser load (7) through the fixed star directional action of the star sensor (9), and correcting the installation coordinate system errors of the laser load (7) and the satellite platform and the rotating mechanism error of the laser load (7);
the dynamic star model (10) is fixed at an optical inlet of the star sensor (9) and is used for simulating a dynamically changed star map;
the laser load (7) and an external cable of the dynamic star model (10) are respectively connected with an external star model controller (12) and a load control simulator (13) through a slip ring interface (11) of the two-dimensional rotary table (8);
the turntable controller (14) is respectively connected with the two-dimensional turntable (8) and the star model controller (12);
the load control simulator (13) injects a turntable track into the turntable controller (14) according to the satellite orbit change and the attitude change, and the turntable controller (14) controls the two-dimensional turntable (8) to simulate the on-orbit dynamic change of a satellite platform;
the star model controller (12) receives the platform dynamic change track input by the load control simulator (13), generates a star map corresponding to dynamic change, inputs the star map to the dynamic star model (10), and the dynamic star model (10) generates a corresponding star map on the focal plane of an internal optical system of the dynamic star model, converts the star map into parallel light through the optical system and outputs the parallel light to be received by the star sensor (9);
the time service controller (15) is used for carrying out unified time service on the satellite model controller (12), the load control simulator (13) and the rotary table controller (14), and providing 1PPS (pulse per second) as a reference, so that unified and unified simulation of the satellite platform is realized.
2. The semi-physical simulation device for the dynamic capture tracking test of the laser load according to claim 1, wherein the star sensor (9) of the laser load (7) observes a dynamic star image consistent with the on-orbit change and provides directional input information for the capture, tracking and construction of the laser load (7).
3. The semi-physical simulation device for the laser load dynamic acquisition tracking test according to claim 1, wherein the piezoelectric fiber controller (6) can drive the position of the focal plane fiber emitter (2) by injecting specified power spectrum data, and the change of the position of the fiber end surface on the focal plane of the collimator (4) converts the change of the pointing angle of the non-outward parallel light, so as to simulate the micro-vibration of the satellite platform.
4. A semi-physical simulation method for a laser load dynamic capture tracking test is characterized in that two sets of semi-physical simulation devices for the laser load dynamic capture tracking test according to any one of claims 1 to 3 are adopted, and two sets of focal plane optical fiber transmitters (2) are connected through optical fibers to perform double-intersatellite dynamic capture and link building.
5. The semi-physical simulation method for the dynamic capture and tracking test of the laser load according to claim 4 is characterized in that one shared time service controller (15) is adopted to respectively control the time service errors of two sets of the satellite mode controller (12), the load control simulator (13) and the turntable controller (14), so that the on-orbit time synchronization errors of two satellites are simulated, and the adaptability of the inter-satellite capture and tracking function of the laser load (7) to different satellite time synchronization errors is tested.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210706289.3A CN115173920A (en) | 2022-06-21 | 2022-06-21 | Semi-physical simulation device and method for dynamic capture tracking test of laser load |
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| CN202210706289.3A CN115173920A (en) | 2022-06-21 | 2022-06-21 | Semi-physical simulation device and method for dynamic capture tracking test of laser load |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115765854A (en) * | 2022-10-26 | 2023-03-07 | 长光卫星技术股份有限公司 | Satellite-borne laser communication load ground fixed star calibration test system and test method |
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2022
- 2022-06-21 CN CN202210706289.3A patent/CN115173920A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115765854A (en) * | 2022-10-26 | 2023-03-07 | 长光卫星技术股份有限公司 | Satellite-borne laser communication load ground fixed star calibration test system and test method |
| CN115765854B (en) * | 2022-10-26 | 2024-03-08 | 长光卫星技术股份有限公司 | Satellite-borne laser communication load ground constant star calibration test system and test method |
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