A hollow laser beam riding guidance simulation method

Abstract

The present application belongs to the field of photoelectric guidance, and particularly relates to a hollow laser beam riding guidance simulation method. In order to study the guidance law of a missile in a hollow laser beam, the present application proposes a hollow laser beam riding guidance simulation method, which adopts a two-axis turntable to simulate the pitch and azimuth motion adjustment of the missile, adopts a television monitor to obtain the tracking performance of the missile on a target, adopts a terminal control display platform to obtain the control signal of the missile in real time, and displays the guidance law characteristics of the missile in the hollow laser information field. The present application has the following advantages: the control signal of the real-time hollow laser beam riding guidance missile is obtained, the video information of the head of the missile is obtained in real time, the control signal and the video information are verified in real time, the method is simple to operate, and the method can meet the needs of indoor and outdoor simulation tests of the hollow beam riding guidance weapon.

Description

Technical Field

[0001] This invention belongs to the field of optoelectronic guidance, specifically relating to a hollow laser beam riding guidance simulation method, which can simulate the guidance law of a missile in a hollow laser beam, and can intuitively display the simulated attitude of the missile in real time, and collect missile control commands from the onboard computer in real time. Background Technology

[0002] Laser beam-riding guided weapons, due to their rearward laser signal reception, can prevent decoy interference and have strong anti-jamming capabilities. They are suitable for individual soldier, vehicle-mounted, and airborne launch, making them extremely important in dealing with large numbers of armored targets. This has been fully demonstrated in modern local wars, and they are already widely deployed both domestically and internationally. To counter the threat posed by laser beam-riding guided weapons, laser warning systems have been developed, posing a serious threat to these weapons.

[0003] To prevent weapon systems from being alerted or attacked, they need to be stealthy, depriving the enemy of the conditions and opportunities to issue warnings. This should be the direction and survival condition for the continued development of laser-guided weapons. To improve the stealthy attack capability of laser beam-riding guided weapons, a hollow laser beam-riding guided weapon simulation method has been innovatively proposed based on the existing solid laser beam-riding guidance. Previous laser beam-riding guided weapon simulations were all based on solid lasers, which could not realistically simulate the flight control methods within a hollow laser beam. To improve the development methods of hollow laser beam-riding guided weapons and ensure the accuracy and authenticity of experimental verification, constructing a hollow laser beam-riding guidance simulation system that is basically consistent with the guidance laws and characteristics of actual missiles is the basic platform condition for the early research, development, testing, and evaluation of hollow laser beam-riding guided weapon systems. Summary of the Invention

[0004] (a) Technical problems to be solved

[0005] The present invention aims to solve three technical problems: first, in order to realistically simulate the guidance characteristics of a missile in a hollow laser beam, it is necessary to accurately acquire and process the hollow laser information field; second, the mutual matching of the missile's control commands and the two-axis turntable control; and third, the real-time display and acquisition of the missile's spatial attitude relative to the target, which intuitively simulates the missile's guidance characteristics.

[0006] (II) Technical Solution

[0007] To address the aforementioned technical problems, this invention provides a hollow laser beam-riding guidance simulation method, which is used to simulate the guidance law of an anti-tank missile in a hollow laser beam.

[0008] The equipment used to implement the method includes a simulated missile device, a two-axis turntable, a support frame, a television monitoring and acquisition unit, a turntable controller, and a control computer, in order to realize the simulation of hollow laser beam riding guidance.

[0009] In the method described, a missile simulation device simulates receiving laser information and calculating control commands in real time; a two-axis turntable executes the control commands output by the missile, performing azimuth and pitch movements; a support frame supports the two-axis turntable and the missile simulation device; a television monitoring and acquisition unit is installed at the missile warhead position to monitor the changes in the missile's spatial position relative to the target in real time and save image data; a turntable controller controls the two-axis turntable; and a control computer displays and processes the image data, realizing the simulation of hollow laser beam riding guidance.

[0010] In this case, the center of the hollow laser beam of the guidance device is aligned with the center of the target plate.

[0011] The simulated missile device consists of an onboard laser receiver and an onboard computer. When the simulated missile is placed in a hollow laser beam, the onboard laser receiver receives the hollow laser beam-riding guidance command, which includes modulation position and energy information, emitted by the guidance instrument. After photoelectric conversion, the command is pre-amplified, decoded, filtered, and amplified before being input to the onboard computer. The onboard computer performs high-speed real-time calculations on the hollow laser beam-riding guidance command according to the mathematical model of the control system software, converting the hollow laser beam-riding guidance command into a flight control command, and then transmitting the flight control command to the control computer in real time.

[0012] The flight control signal is converted into a two-axis turntable control signal by the control computer, and the turntable controller controls the two-axis turntable to perform corresponding pitch and azimuth movements.

[0013] The television monitoring and acquisition unit is installed at the head of the simulated missile device. It uses real-time measurement of the position (angle) deviation between the target and the line of sight to achieve the purpose of television angle measurement. It displays the missile guidance and control performance through video and can complete the acquisition of image information. It has the characteristics of being intuitive and easy to operate.

[0014] While the simulated missile follows the two-axis turntable to make corresponding pitch and azimuth movements, the television monitoring and acquisition unit installed on the head of the simulated missile observes the corresponding position changes on the target plate in real time, and obtains the spatial attitude change of the simulated missile relative to the target based on image processing.

[0015] The control computer displays the monitoring images acquired by the television monitoring and acquisition unit, and simultaneously calculates and displays the missile's coordinate position in the hollow laser information field based on the flight control signals from the onboard computer.

[0016] The two-axis turntable provides a support platform for the missile simulation device, including two independent rotating devices for azimuth and pitch, which can simulate the azimuth and pitch attitude movements of a missile during controlled flight.

[0017] In the two-axis turntable, the pitch frame is mounted on the azimuth frame via the pitch axis system, and the azimuth frame is mounted on the base via the azimuth axis system. The azimuth frame rotates relative to the base in azimuth, and the pitch frame rotates relative to the base in pitch. Each axis system is controlled by an independent servo control unit. The control loop of each axis system includes a control and drive circuit, a stepper motor, and a frame angle sensor.

[0018] The simulated missile is an anti-tank missile.

[0019] (III) Beneficial Effects

[0020] Compared with the prior art, the beneficial effects of the present invention are reflected in the following two aspects:

[0021] (1) The hollow laser beam-riding guidance simulation method is mainly used to simulate the flight attitude and guidance characteristics of missiles in hollow laser beams. It provides the necessary conditions for establishing the missile control model in hollow laser beams and simulating the missile guidance and control performance. Through simulation experiments on hollow laser information fields at different distances, it provides the necessary conditions for the early design and verification of hollow laser beam-riding guidance weapon systems.

[0022] (2) It can improve the research and development methods of hollow laser beam-riding guided weapons, ensure the accuracy and authenticity of test verification, and construct a simulation that is basically consistent with the actual missile flight control characteristics. This simulation method can simulate the flight control characteristics of missiles at different guidance distances in a more realistic way, so as to make up for the deficiencies of the current test conditions and environment, and provide the necessary conditions for the design, research, test and evaluation of hollow laser beam-riding guided weapon systems. Attached Figure Description

[0023] Figure 1 This is a block diagram of the equipment composition of the hollow laser beam riding guidance simulation method of the present invention.

[0024] Figure 2 This is a block diagram illustrating the principle of a hollow laser beam-riding guidance simulation method. Detailed Implementation

[0025] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0026] To address the aforementioned technical problems, this invention provides a hollow laser beam-riding guidance simulation method, which is used to simulate the guidance law of an anti-tank missile in a hollow laser beam.

[0027] The equipment used to implement the method includes a simulated missile device, a two-axis turntable, a support frame, a television monitoring and acquisition unit, a turntable controller, and a control computer, in order to realize the simulation of hollow laser beam riding guidance.

[0028] In the method described, a missile simulation device simulates receiving laser information and calculating control commands in real time; a two-axis turntable executes the control commands output by the missile, performing azimuth and pitch movements; a support frame supports the two-axis turntable and the missile simulation device; a television monitoring and acquisition unit is installed at the missile warhead position to monitor the changes in the missile's spatial position relative to the target in real time and save image data; a turntable controller controls the two-axis turntable; and a control computer displays and processes the image data, realizing the simulation of hollow laser beam riding guidance.

[0029] In this case, the center of the hollow laser beam of the guidance device is aligned with the center of the target plate.

[0030] The simulated missile device consists of an onboard laser receiver and an onboard computer. When the simulated missile is placed in a hollow laser beam, the onboard laser receiver receives the hollow laser beam-riding guidance command, which includes modulation position and energy information, emitted by the guidance instrument. After photoelectric conversion, the command is pre-amplified, decoded, filtered, and amplified before being input to the onboard computer. The onboard computer performs high-speed real-time calculations on the hollow laser beam-riding guidance command according to the mathematical model of the control system software, converting the hollow laser beam-riding guidance command into a flight control command, and then transmitting the flight control command to the control computer in real time.

[0031] The flight control signal is converted into a two-axis turntable control signal by the control computer, and the turntable controller controls the two-axis turntable to perform corresponding pitch and azimuth movements.

[0032] The television monitoring and acquisition unit is installed at the head of the simulated missile device. It uses real-time measurement of the position (angle) deviation between the target and the line of sight to achieve the purpose of television angle measurement. It displays the missile guidance and control performance through video and can complete the acquisition of image information. It has the characteristics of being intuitive and easy to operate.

[0033] While the simulated missile follows the two-axis turntable to make corresponding pitch and azimuth movements, the television monitoring and acquisition unit installed on the head of the simulated missile observes the corresponding position changes on the target plate in real time, and obtains the spatial attitude change of the simulated missile relative to the target based on image processing.

[0034] The control computer displays the monitoring images acquired by the television monitoring and acquisition unit, and simultaneously calculates and displays the missile's coordinate position in the hollow laser information field based on the flight control signals from the onboard computer.

[0035] The two-axis turntable provides a support platform for the missile simulation device, including two independent rotating devices for azimuth and pitch, which can simulate the azimuth and pitch attitude movements of a missile during controlled flight.

[0036] In the two-axis turntable, the pitch frame is mounted on the azimuth frame via the pitch axis system, and the azimuth frame is mounted on the base via the azimuth axis system. The azimuth frame rotates relative to the base in azimuth, and the pitch frame rotates relative to the base in pitch. Each axis system is controlled by an independent servo control unit. The control loop of each axis system includes a control and drive circuit, a stepper motor, and a frame angle sensor.

[0037] The simulated missile is an anti-tank missile.

[0038] Example 1

[0039] The equipment components for the hollow laser beam-riding guidance simulation method are shown in the attached figure. Figure 1 The working principle is as follows: Figure 2 The specific workflow is as follows: The center of the hollow laser beam is aligned with the center of the target plate. After the simulated missile is placed in the hollow laser beam, the onboard laser receiver receives the hollow laser field information and calculates the flight control commands through the onboard computer. The flight control signals are converted into two-axis turntable control signals by the control computer. The turntable controller controls the turntable to perform corresponding pitch and azimuth movements. While the simulated missile is performing these movements, a small television monitor installed on the nose of the simulated missile can observe the corresponding positional changes on the target plate in real time. Based on the image processing of the small television monitor, the spatial attitude change of the simulated missile relative to the target can be obtained. While displaying the monitoring images, the control computer, based on the flight control signals from the onboard computer, completes the calculation and synchronous display of the missile's coordinate position in the hollow laser information field.

[0040] The two-axis turntable for missile motion simulation provides a support platform for the simulated missile and is one of the main components of the method. It consists of two independent rotation devices for azimuth and pitch, which can simulate the azimuth and pitch attitude movements of a missile during controlled flight. The two-axis turntable mainly consists of two parts: the turntable mechanical components and the simulation control. The pitch frame is mounted on the azimuth frame via a pitch axis system, and the azimuth frame is mounted on the system base via an azimuth axis system. The azimuth frame rotates relative to the base in azimuth, and the pitch frame rotates relative to the base in pitch. Each axis system is controlled by an independent servo control unit. The control loop of each axis system consists of control and drive circuits, stepper motors, frame angle sensors, etc.

[0041] After the control command signal output by the onboard computer is processed by the circuit, it can complete the signal matching of the two-axis turntable. The control signal is then transmitted to the turntable servo control system, which controls the axis motor to rotate, thereby achieving the purpose of beam riding guidance simulation.

[0042] The real-time display and acquisition of the missile's attitude relative to the target is mainly accomplished by the control computer. This computer acquires video images from a small television monitor and deviation signals relative to the target, exchanges information with the onboard computer, and stores and displays this information. The test control computer mainly consists of a host computer, image acquisition card, multi-serial port card, I / O card, and programs for displaying the monitoring image, processing deviations relative to the target, and processing and displaying the missile's coordinate position in a hollow laser information field. These components visually simulate the missile's guidance characteristics.

[0043] In summary, this invention belongs to the field of optoelectronic guidance, specifically relating to a hollow laser beam-riding guidance simulation method. This method is mainly used to simulate the guidance characteristics of anti-tank missiles in a hollow laser beam. It provides a necessary technical foundation for the development of hollow laser beam-riding guided weapon systems, the study of guidance laws, and simulation experiments. The guidance performance of the missile can be evaluated by observing changes in the position of the hollow laser information field. It also provides necessary technical support for the early design and verification of hollow laser beam-riding guided weapon systems. This hollow laser beam-riding guidance simulation method can simulate the elevation and azimuth control functions of a missile, and can provide real-time video feedback on the guidance laws of the hollow beam-riding guided missile in the laser information field through a small television monitor on the missile's simulated warhead.

[0044] Laser beam-riding guided weapons are the primary means of attacking armored vehicles. However, the development of warning technology has reduced the effectiveness of these weapon systems. Hollow laser beam-riding guided weapons, by using a hollow laser beam to illuminate the target, provide a degree of concealment, thereby improving their survivability, penetration capability, and combat effectiveness. To study the guidance laws of missiles within a hollow laser beam, this invention proposes a hollow laser beam-riding guidance simulation method. This method uses a two-axis turntable to simulate the missile's pitch and azimuth movements, employs a small television monitor to acquire the missile's target tracking performance, and uses a terminal control display platform to acquire the missile's control signals in real time and display the missile's guidance characteristics within the hollow laser information field.

[0045] The key advantages of this invention are that it can acquire control signals of hollow laser beam-riding guided missiles in real time, acquire video information of the missile head in real time, and verify the control signals and video information in real time. Moreover, the method is simple to operate and can meet the needs of indoor and outdoor simulation tests of hollow beam-riding guided weapons.

[0046] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A hollow laser beam-riding guidance simulation method, characterized in that, The method is used to simulate the guidance law of anti-tank missiles in hollow laser beams; The equipment used to implement the method includes a simulated missile device, a two-axis turntable, a support frame, a television monitoring and acquisition unit, a turntable controller, and a control computer, in order to realize the simulation of hollow laser beam riding guidance. In the method, a missile simulation device is used to simulate a missile receiving laser information and calculating control commands in real time; a two-axis turntable is used to execute the control commands output by the missile to perform azimuth and pitch movements; and a support frame supports the two-axis turntable and the missile simulation device. The television monitoring and acquisition unit is installed at the simulated missile warhead position to monitor the missile's spatial position relative to the target in real time and save image data. The turntable controller controls the two-axis turntable; the control computer displays and processes image data to simulate hollow laser beam riding guidance. In this case, the center of the hollow laser beam of the guidance device is aligned with the center of the target plate; The simulated missile device consists of an onboard laser receiver and an onboard computer. When the simulated missile is placed in a hollow laser beam, the onboard laser receiver receives the hollow laser beam-riding guidance command, which includes modulation position and energy information, emitted by the guidance instrument. After photoelectric conversion, the command is pre-amplified, decoded, filtered, and amplified before being input to the onboard computer. The onboard computer performs real-time calculations on the hollow laser beam-riding guidance command, converting it into flight control command, and then transmits the flight control command to the control computer in real time. Among them, the flight control signal is converted into a two-axis turntable control signal by the control computer, and the turntable controller controls the two-axis turntable to perform corresponding pitch and azimuth movements. The television monitoring and acquisition unit is installed at the head of the simulated missile device, and uses real-time measurement of the positional deviation between the target and the line of sight to achieve the purpose of television angle measurement. While the simulated missile follows the two-axis turntable to make corresponding pitch and azimuth movements, the television monitoring and acquisition unit installed on the head of the simulated missile observes the corresponding position changes on the target plate in real time, and obtains the spatial attitude change of the simulated missile relative to the target based on image processing.

2. The hollow laser beam-riding guidance simulation method as described in claim 1, characterized in that, While displaying the monitoring images acquired by the television monitoring and acquisition unit, the control computer calculates and synchronously displays the missile's coordinate position in the hollow laser information field based on the flight control signals from the onboard computer.

3. The hollow laser beam-riding guidance simulation method as described in claim 2, characterized in that, The two-axis turntable provides a support platform for the missile simulation device, including two independent rotating devices for azimuth and pitch, which can simulate the azimuth and pitch attitude movements of a missile during controlled flight.

4. The hollow laser beam-riding guidance simulation method as described in claim 2, characterized in that, In the two-axis turntable, the pitch frame is mounted on the azimuth frame via the pitch axis system, and the azimuth frame is mounted on the base via the azimuth axis system. The azimuth frame rotates relative to the base in azimuth, and the pitch frame rotates relative to the base in pitch. Each axis system is controlled by an independent servo control unit. Each axis system control loop includes a control and drive circuit, a stepper motor, and a frame angle sensor.

5. The hollow laser beam-riding guidance simulation method as described in claim 4, characterized in that, The simulated missile is an anti-tank missile.

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