Optical fiber array direct injection type optical guidance control semi-physical simulation system and method

Abstract

The application provides a kind of optical fiber array direct injection type optical guidance control semi-physical simulation system and method, including the following: laser connects optical fiber shunt; Optical fiber shunt connects energy control module; Energy control module connects optical fiber array integrator; Optical fiber array integrator is installed on the focal plane of collimating optical lens by optical fiber joint; Collimating optical lens is installed in front of the optical system of test optical guidance control system; Test optical guidance control system is installed on flight turntable; Flight turntable connects real-time simulation control system; Real-time simulation control system connects scene generation computer; Scene generation computer and energy control module drive connection; Laser source, optical fiber shunt, energy control module, optical fiber array integrator, real-time simulation control system and scene generation computer are located below flight turntable. The application adopts directly test optical guidance control system before installing large field of view optical target simulator, compact structure, and carries out semi-physical simulation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of optical guidance control semi-physical simulation, in particular to a kind of optical fiber array direct injection type optical guidance control semi-physical simulation system and method. BACKGROUND

[0002] With the fusion development of computer and photoelectric technology, optical guidance control technology has become an important development direction in the field of photoelectric detection. Most of the existing optical guidance control semi-physical simulation methods adopt a scene projection scheme of five-axis turntable (three-axis flight turntable + two-axis target arm) + target simulator. The three-axis flight turntable is used to simulate the attitude of the projectile, and the two-axis target arm is used to simulate the target motion information. In order to ensure a large motion range and not to interfere with the structure, the distance between the two axes of the target arm and the rotation center of the flight turntable is usually far, about 0.6m-1m. This requires the optical target simulator to have a long exit pupil distance, a large exit pupil diameter, a large field of view and a large collimating lens aperture. Under the constraints of the exit pupil distance and the exit pupil diameter and the collimating lens aperture, it is difficult for the optical target simulator to cover the field of view of the optical guidance control system under test, which cannot meet the simulation requirements.

[0003] Chinese patent document with publication number CN114545790A discloses an optical guidance control semi-physical simulation system and method. The infrared target simulator is fixed to the three-axis turntable together with the seeker. The three-axis turntable is used to simulate the attitude of the projectile, and the infrared target simulator is used to simulate the infrared thermal image of the target scene, to realize the optical guidance control semi-physical simulation. This method reduces the exit pupil distance and the field of view angle of the optical system of the infrared target simulator, and to a certain extent, reduces the volume and weight of the infrared target simulator.

[0004] For the related technology in the above, the inventors believe that this method still needs to install the entire infrared target simulator on the turntable. The infrared target simulator usually includes essential parts such as illumination light source, light modulator, collimating optical lens, environmental control system and structural parts, which are heavy and will greatly affect the dynamic performance of the turntable when installed in the inner frame of the turntable. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide an optical fiber array direct injection type optical guidance control semi-physical simulation system and method.

[0006] According to the optical fiber array direct injection type optical guidance control semi-physical simulation system provided by the present application, it comprises a laser source, a fiber splitter, an energy control module, a fiber array integrator, a collimating optical lens, a flight turntable, a test optical guidance control system, a real-time simulation control system and a scene generation computer.

[0007] The laser is connected to one end of the fiber splitter.

[0008] The other end of the fiber splitter is connected to one end of an energy control module;

[0009] One end of the energy control module is connected to one end of a fiber array integrator;

[0010] The other end of the fiber array integrator is mounted on the focal plane of a collimating optical lens through a fiber joint;

[0011] The collimating optical lens is mounted in front of the optical system of a subject optical guidance control system;

[0012] The subject optical guidance control system is mounted on a flight turntable;

[0013] The flight turntable is connected to a real-time simulation control system;

[0014] The real-time simulation control system is connected to a scene generation computer;

[0015] The scene generation computer and the energy control module are drivenly connected;

[0016] The laser source, the fiber splitter, the energy control module, the fiber array integrator, the real-time simulation control system and the scene generation computer are located below the flight turntable.

[0017] Preferably, the system comprises a mounting structure;

[0018] The collimating optical lens is fixedly mounted in front of the optical system of the subject optical guidance control system through the mounting structure.

[0019] Preferably, the system further comprises a posture adjustment mechanism;

[0020] The posture adjustment mechanism adjusts the posture of the collimating optical lens to ensure that the subject optical guidance control system coincides with the optical axis of the collimating optical lens.

[0021] Preferably, the laser source emits a laser beam;

[0022] The fiber splitter divides the emitted laser beam into multiple beams;

[0023] The energy control module independently controls the attenuation and on-off of each beam.

[0024] Preferably, the real-time simulation control system drives the flight turntable to simulate the attitude change of the missile body according to the attitude information of the missile body, and sends the position and attitude information of the missile to the scene generation computer;

[0025] The scene generation computer completes scene rendering according to the position and posture information of the projectile and missile, and drives the energy control module to control laser beam attenuation and on-off according to the rendered scene to form corresponding scene images, simulating the change of the line-of-sight angular velocity of the projectile and missile;

[0026] The optical fiber array integrator integrates the light beams after energy control and transmits to the optical fiber interface;

[0027] The collimating optical lens receives the integrated light beams and emits collimating optical radiation signals of the corresponding scene;

[0028] The subject optical guidance control system detects and processes the collimating optical radiation signals to form tracking instructions to control the movement of the tracking target, realizing the closure of the semi-physical simulation loop.

[0029] Preferably, the laser beams include infrared light, ultraviolet light and visible light.

[0030] Preferably, the energy control module includes an attenuation control module.

[0031] The attenuation control module includes a driver and a plurality of attenuators.

[0032] The driver drives the attenuators.

[0033] The attenuators independently control the attenuation and on-off of each laser beam.

[0034] Preferably, the interface form of the optical fiber interface includes a square array, a circular array, a linear array or a single point.

[0035] Preferably, the flight turntable includes a three-axis flight turntable.

[0036] According to the optical fiber array direct injection type optical guidance control semi-physical simulation method provided by the application, the optical fiber array direct injection type optical guidance control semi-physical simulation system is applied, the real-time simulation control system drives the flight turntable to move according to the posture information of the projectile body to simulate the change of the posture of the missile body, and simultaneously sends the position and posture information of the projectile and missile to the scene generation computer;

[0037] The scene generation computer completes scene rendering according to the position and posture information of the projectile and missile, and drives the energy control module to control laser beam attenuation and on-off according to the rendered scene to form corresponding scene images, simulating the change of the line-of-sight angular velocity of the projectile and missile;

[0038] The optical fiber array integrator integrates and transmits the light beams after energy control.

[0039] The collimating optical lens receives the integrated light beams and emits collimating optical radiation signals of the corresponding scene;

[0040] The subject optical guidance control system detects and processes collimated optical radiation signals, forms tracking instruction to control tracking target movement, and realizes the closure of the semi-physical simulation loop.

[0041] Compared with the prior art, the present application has the following beneficial effects:

[0042] 1. In the present application, the light source of the target simulation uses laser source, which has stronger energy and wider dynamic range, compared with the blackbody illumination in the conventional optical target simulator.

[0043] 2. In the present application, only the collimating optical lens and the corresponding mounting and adjusting structure are mounted on the turntable, and other parts are all located below the turntable, so that the upper part of the turntable has small volume and weight, has little influence on the dynamic characteristics of the turntable, and can complete the semi-physical simulation with higher dynamic characteristics, and is easier to debug, replace and maintain.

[0044] 3. The present application adopts the method of directly mounting the large field of view optical target simulator in front of the subject optical guidance control system, and has compact structure, and can realize the semi-physical simulation of the large field of view strapdown optical guidance control system on the three-axis flight turntable. BRIEF DESCRIPTION OF DRAWINGS

[0045] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments with reference to the attached drawings:

[0046] Figure 1 A structure schematic diagram of a fiber array direct injection type optical guidance control semi-physical simulation system is provided in the present application. DETAILED DESCRIPTION

[0047] The present application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0048] The present application discloses a fiber array direct injection type optical guidance control semi-physical simulation system, as shown in Figure 1 The present application discloses a fiber array direct injection type optical guidance control semi-physical simulation system, as shown in

[0049] The one end of the laser is connected with the one end of the fiber splitter; the other end of the fiber splitter is connected with the one end of the energy control module; the one end of the energy control module is connected with the one end of the fiber array integrator; the other end of the fiber array integrator is installed on the focal plane of the collimating optical lens through the fiber joint; the collimating optical lens is installed in front of the optical system of the optical guidance control system; the optical guidance control system is installed on the flight turntable; the flight turntable is connected with the real-time simulation control system; the real-time simulation control system is connected with the scene generation computer; the scene generation computer and the energy control module are driven to be connected; the laser source, the fiber splitter, the energy control module, the fiber array integrator, the real-time simulation control system and the scene generation computer are located below the flight turntable.

[0050] The light beam emitted by the laser source is divided into multiple paths through the fiber splitter and integrated through the fiber array integrator, and transmitted to the fiber interface; the laser beam can include infrared, ultraviolet, visible light and other wave bands.

[0051] Each laser can independently control the strength and on-off of the energy through the energy modulation module. The attenuation control module is composed of N attenuators and drivers, and each laser can independently control the attenuation and on-off through the attenuation control module.

[0052] The fiber array interface can be installed on the focal plane of the collimating optical lens, and the interface form can be a square array, a circular array, a linear array or a single point.

[0053] The collimating optical lens can be fixedly installed in front of the optical system of the optical guidance control system through the mounting structure, and then the collimating optical lens is integrally installed on the three-axis flight turntable. The collimating optical lens is fixedly connected with the measured guidance control system, and the collimating optical radiation signal emitted by the collimating optical lens can be detected and received by the optical guidance control system.

[0054] The attitude of the collimating optical lens can be adjusted through the attitude adjustment mechanism to ensure that the optical axis of the optical guidance control system coincides with the optical axis of the collimating optical lens.

[0055] During the simulation process, the optical axes of the large field of view optical target simulator and the optical guidance control system always coincide and are relatively static, and the target simulator (fiber array) scene change simulates the relative line-of-sight motion of the missile and the target according to the missile attitude information and the target scene information.

[0056] During the simulation process, the optical axes of the collimating optical lens and the optical guidance control system always coincide and are relatively static, and the attenuation and on-off control of the light beams in the fiber array (different regions) simulate the scene change of the relative line-of-sight motion of the missile and the target according to the missile attitude information and the target scene information.

[0057] The application is a method for simulating target scene changes by driving light beam attenuation and on-off of different regions of a fiber array. The specific working process is as follows: in a simulation frame period, a real-time simulation control system drives a three-axis flight turntable to move according to body attitude information to simulate the attitude change of a missile body, and sends target characteristic parameters and body attitude information (missile position and attitude information) to a scene generation computer, the scene generation computer completes scene rendering according to the current missile position and attitude information, drives an energy control module to control laser attenuation and on-off to form a corresponding scene image to simulate the change of the line-of-sight angular velocity of the missile. The three-axis flight turntable moves according to the output missile attitude to generate the motion physical effect of the tested optical guidance control system, the optical axis of the collimating optical lens is always coincident with the optical axis of the tested optical guidance control system, the corresponding scene radiation information is generated and detected and processed by the tracking loop of the optical guidance control system, the tracking command is formed to control the tested optical guidance control system to track the target motion, and the closure of the semi-physical simulation loop is realized.

[0058] The application also discloses a fiber array direct injection type optical guidance control semi-physical simulation method and system, the real-time simulation control system drives a flight turntable to move according to body attitude information to simulate the attitude change of a missile body, and sends missile position and attitude information to a scene generation computer; the scene generation computer completes scene rendering according to the missile position and attitude information, and drives an energy control module to control the attenuation and on-off of each light beam according to the rendered scene to form a corresponding scene image to simulate the change of the line-of-sight angular velocity of the missile; a fiber array integrator integrates and transmits the energy-controlled light beams; a collimating optical lens receives the integrated light beams and emits corresponding collimating optical radiation signals; a tested optical guidance control system detects and processes the collimating optical radiation signals, forms a tracking command to control the tracking of the target motion, and realizes the closure of the semi-physical simulation loop. The real-time simulation system sends motion instructions to the turntable according to the body attitude and receives feedback information (the turntable feedback is the response of the instructions) of the turntable, and transmits the missile position and attitude information and the feedback information of the turntable to the scene generation computer.

[0059] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0060] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. A fiber optic array direct-projection optical guidance and control hardware-in-the-loop simulation system, characterized in that, It includes a laser source, fiber optic splitter, energy control module, fiber optic array integrator, collimating optical lens, flight turntable, test optical guidance control system, real-time simulation control system, and scene generation computer; The laser source is connected to one end of the fiber optic splitter; The other end of the fiber optic splitter is connected to one end of the energy control module; One end of the energy control module is connected to one end of the fiber optic array integrator; The other end of the fiber array integrator is mounted on the focal plane of the collimating optical lens via a fiber optic connector. The collimating optical lens is installed in front of the optical system of the tested optical guidance and control system; The tested optical guidance and control system was installed on the flight turntable; The flight turntable is connected to a real-time simulation control system; The real-time simulation control system is connected to the scene generation computer; The scene generation computer and energy control module are connected. The laser source, fiber optic splitter, energy control module, fiber optic array integrator, real-time simulation control system, and scene generation computer are located under the flight turntable; The system includes an installation structure; The collimating optical lens is fixedly mounted in front of the optical system of the tested optical guidance and control system via a mounting structure. The system also includes an attitude adjustment mechanism; The attitude adjustment mechanism adjusts the attitude of the collimating optical lens to ensure that the optical guidance and control system under test is aligned with the optical axis of the collimating optical lens. The laser source emits a laser beam; The fiber optic splitter divides the emitted laser beam into multiple beams; The energy control module independently controls the attenuation and on / off state of each beam; The energy control module includes an attenuation control module; The attenuation control module includes a driver and multiple attenuators; The driver drives the attenuator; The attenuator independently controls the attenuation and switching on / off of each laser path.

2. The fiber optic array direct-projection optical guidance and control hardware-in-the-loop simulation system according to claim 1, characterized in that, The real-time simulation control system drives the flight turntable to simulate the attitude changes of the missile body based on the missile body attitude information, and at the same time sends the missile target position attitude information to the scene generation computer. The scene generation computer completes scene rendering based on the projectile's position and attitude information, and drives the energy control module to control laser attenuation and switching to form a corresponding scene image, simulating the change in the projectile's line-of-sight angular velocity. The fiber array integrator integrates multiple energy-controlled beams and transmits them to the fiber optic interface; The collimating optical lens receives the integrated light beam and emits collimated optical radiation signals corresponding to the scene. The tested optical guidance and control system detects and processes collimated optical radiation signals, generates tracking commands to control the movement of the tracking target, and realizes the closure of the semi-physical simulation loop.

3. The fiber optic array direct-projection optical guidance and control hardware-in-the-loop simulation system according to claim 1, characterized in that, The laser beam includes infrared light, ultraviolet light, and visible light.

4. The fiber optic array direct-projection optical guidance and control hardware-in-the-loop simulation system according to claim 1, characterized in that, The fiber optic interface can be in the form of a square array, a circular array, a linear array, or a single point.

5. The fiber optic array direct-projection optical guidance and control hardware-in-the-loop simulation system according to claim 1, characterized in that, The flight turntable includes a three-axis flight turntable.

6. A hardware-in-the-loop simulation method for direct-projection optical guidance and control of fiber optic arrays, characterized in that, The fiber array direct-projection optical guidance and control hardware-in-the-loop simulation system described in any one of claims 1-5 is used in which the real-time simulation control system drives the flight turntable to move according to the missile body attitude information to simulate the attitude change of the missile body, and at the same time sends the missile target position attitude information to the scene generation computer. The scene generation computer completes scene rendering based on the projectile and target position and attitude information, and drives the energy control module to control the attenuation and switching of each beam to form a corresponding scene image, simulating the change of the projectile and target line-of-sight angular velocity. The fiber array integrator integrates and transmits multiple energy-controlled beams; The collimating optical lens receives the integrated light beam and emits collimated optical radiation signals corresponding to the scene. The tested optical guidance and control system detects and processes collimated optical radiation signals, generates tracking commands to control the movement of the tracking target, and realizes the closure of the semi-physical simulation loop.

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