Laser ablation countering unmanned aerial vehicle internal temperature field analysis test method and device

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a laser ablation countering unmanned aerial vehicle internal temperature field analysis test method and device. The test method comprises the following steps: preparing a test device image; carrying out a laser ablation countering unmanned aerial vehicle test; performing finite element simulation on the laser ablation countering unmanned aerial vehicle test; adjusting the grid size of finite element simulation and COMSOL software parameters to enable the test temperature-time curve to be matched with the simulation temperature-time curve, and exporting a temperature-time simulation curve of key points in the fuselage; and combining a laser ablation countering unmanned aerial vehicle test and finite element simulation to analyze the relationship between the heat flow field in the unmanned aerial vehicle body and the flight attitude. According to the method, a laser ablation countering unmanned aerial vehicle test and finite element simulation are combined, the effectiveness of a finite element technology is verified through test and simulation comparison, and analysis of a heat flow field in a complex fuselage is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a laser ablation countermeasure unmanned aerial vehicle internal temperature field analysis test method and device. Background Art

[0002] In recent years, with the rapid development of the low-altitude economy, the application of drones has become increasingly common, but the abuse of drones has also brought many problems such as wounding and voyeurism. At present, there are methods such as radio interference, netting and high-energy laser strikes to achieve drone countermeasures. Among them, high-energy laser strikes are a hard kill method that is not affected by drone communication methods and has received widespread attention in the engineering community. How to evaluate the flight performance of drones after laser ablation is an important issue that affects the effectiveness of countering lasers to counter drones.

[0003] When the laser causes damage to the outer shell, the heat carried by the laser will enter the fuselage. When the drone is still in flight, air will enter the fuselage from the outside, causing hot air to flow inside the fuselage, which may further damage other parts of the fuselage. The temperature field inside the drone fuselage can be used as a method and indicator to evaluate the damage effectiveness of laser weapons.

[0004] Although there are some methods and indicators for evaluating the destructive effectiveness of laser weapons, the following problems still exist: 1. Due to the limited internal space of the fuselage, the internal air field is difficult to measure, and it is difficult to obtain internal temperature field and flow field change data using experimental means alone; 2. The laser ablation temperature is high. When using traditional optical measurement methods based on visible light, it will be displayed as a white spot on the screen, and the temperature of the entire field cannot be accurately obtained; 3. Laser ablation UAV technology involves multiple basic disciplines such as mechanics, materials, and optics. Each discipline has many evaluation indicators. It is necessary to optimize the existing indicators and propose evaluation indicators and plans that are convenient for engineering use.

[0005] Therefore, it is necessary to design a laser ablation countermeasure UAV internal temperature field analysis test method. Summary of the invention

[0006] The purpose of the present invention is to solve at least one of the technical problems existing in the prior art and to provide a laser ablation countermeasure UAV internal temperature field analysis test method and device.

[0007] To achieve the above purpose, the technical solution adopted by the present invention is as follows: a laser ablation countermeasure UAV internal temperature field analysis test method, comprising the following steps: Step 1, preparing a test device: the test device includes a drone, a Bluetooth accelerometer, a high-energy laser emission component, a large-range thermal imager, and a high-speed camera; the Bluetooth accelerometer is bonded to the drone, a high-energy laser is emitted to the drone through the high-energy laser emission component, an infrared thermal image video of the drone is captured through the large-range thermal imager, and a test image is captured through the high-speed camera; Step 2, conducting a laser ablation countermeasure UAV test: remotely controlling the UAV to fly within the laser strike range of the high-energy laser emitting assembly, and when the high-energy laser emitting assembly emits a high-energy laser to the UAV for ablation, recording the flight speed and acceleration of the UAV, the high-speed camera captures the flight posture image of the UAV during the laser ablation, the wide-range thermal imager obtains the infrared thermal image video of the UAV during the laser ablation, and derives the temperature-time curve of the surface of the ablated part of the UAV from the infrared thermal image video; Step 3, perform finite element simulation on the laser ablation counter-UAV test: import the two-dimensional image of the UAV into COMSOL software, add the fluid heat transfer physical field and the turbulence physical field, set the simulation parameters in the fluid heat transfer physical field and the turbulence physical field according to the test parameters in step 2, set the mesh size of the finite element simulation and the COMSOL software parameters, simulate the process of laser ablation counter-UAV, and derive the temperature-time simulation curve of the surface of the ablated part; Step 4, adjust the mesh size of the finite element simulation and the parameters of the COMSOL software so that the experimental temperature-time curve and the simulated temperature-time curve are consistent, export the simulated thermal flow field change image inside the fuselage of the drone, select the key points inside the fuselage, and export the temperature-time simulation curve of the key points inside the fuselage; Step 5, combining the laser ablation counter-UAV test and finite element simulation, based on the relationship between the UAV flight attitude parameters and the temperature-time simulation curve of the key points inside the fuselage, and the UAV internal thermal flow field formula, analyze the relationship between the UAV fuselage internal thermal flow field and the flight attitude.

[0008] Furthermore, in step 1, the high-energy laser emitting assembly includes a high-energy laser, a freely rotating gimbal, a sight, and a radiator. The high-energy laser is used to emit a high-energy laser, the freely rotating gimbal is used to drive the high-energy laser to rotate to adjust the emission direction, the sight is used to emit an aiming laser, and the radiator is used to dissipate heat from the high-energy laser.

[0009] Furthermore, in step 3, the two-dimensional space dimension is selected in the model wizard in COMSOL, the material of the domain is set to air, and a transient study is selected; in the fluid heat transfer physics field and the turbulence physics field, the ablated part of the drone is set as the air inlet and outlet.

[0010] Furthermore, in step 3, According to the flight speed of the drone recorded in step 2 , set the wind speed at the air inlet in the turbulence physics field to ; In the fluid heat transfer physical field, the air temperature at the air inlet is set to the temperature obtained in step 2, and the initial temperature of the air is set to the initial real temperature of the test area; Record the total time range of laser ablation of the drone in step 2, determine the time unit in transient research based on the total time range in step 2, and set the total calculation time and time step.

[0011] Furthermore, in step 5, the UAV flight attitude parameters include pitch angle, yaw angle, roll angle, and acceleration.

[0012] Furthermore, in step 5, the thermal flow field formula inside the UAV fuselage specifically includes: The thermal flow field inside the UAV fuselage satisfies the law of conservation of fluid momentum. equation: ; In the formula, For time; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; is the fluid density; is the fluid pressure; for Increment; is the dynamic viscosity; is the acceleration due to gravity; There is an axial balance between the incoming and outgoing mass flows: ; The fluid properties are related to temperature, and the coupling formula with the energy conservation equation is as follows: ; In the formula, is the specific heat capacity; is temperature; is the thermal conductivity; is the Stanton number.

[0013] The present invention also provides a laser ablation countermeasure UAV internal temperature field analysis test device, comprising a UAV, a Bluetooth accelerometer, a high-energy laser emitting component, a large-range thermal imager, and a high-speed camera; the Bluetooth accelerometer is bonded to the UAV, the high-energy laser emitting component is arranged in a test area for emitting high-energy laser to the UAV, the large-range thermal imager is arranged in the test area for shooting infrared thermal imaging video of the UAV, and the high-speed camera is arranged in the test area for shooting test images.

[0014] Furthermore, the high-energy laser emitting assembly includes a high-energy laser, a free-rotating gimbal, a sight, and a radiator. The high-energy laser and the sight are arranged on the free-rotating gimbal. The high-energy laser is used to emit a high-energy laser. The free-rotating gimbal is used to drive the high-energy laser to rotate to adjust the emission direction. The sight is used to emit an aiming laser. The radiator is arranged on the high-energy laser to dissipate heat from the high-energy laser.

[0015] Furthermore, it also includes a plurality of light sources, which are arranged in the test area to illuminate the test area.

[0016] It can be seen from the above description of the present invention that, compared with the prior art, the laser ablation countermeasure UAV internal temperature field analysis test method and device of the present invention include at least one of the following beneficial effects: 1. The present invention uses a large-range thermal imager to achieve full-field temperature measurement during laser ablation of UAVs, solving the problem that the detection head may be ablated in traditional contact measurement; 2. The present invention has developed a method combining laser ablation to counter UAV tests and finite element simulations, verified the effectiveness of finite element technology through test and simulation comparison, and realized the thermal flow field analysis inside the complex fuselage; 3. The present invention establishes the relationship between the external flight posture of the UAV and the internal flow field of the fuselage, and proposes a method for deriving the changes in the internal thermal flow field of the fuselage based on flight mechanics parameters, so as to simplify the evaluation indicators of the strike efficiency of the laser ablation UAV and simplify the engineering use indicators. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a flow chart of the steps of a laser ablation countermeasure UAV internal temperature field analysis test method in a preferred embodiment of the present invention; Figure 2 It is a structural schematic diagram of a laser ablation countermeasure UAV internal temperature field analysis test device in a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of a high-energy laser emission component in a preferred embodiment of the present invention; Explanation of the numbers in the figure: 1 UAV, 2 Bluetooth accelerometer, 3 high-energy laser emission component, 4 large-range thermal imager, 5 high-speed camera, 6 light source, 301 high-energy laser, 302 free-rotating gimbal, 303 aimer, 304 radiator. DETAILED DESCRIPTION

[0018] The technical scheme in the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiment of the present invention. Obviously, the described embodiment is only a part of the embodiment of the present invention, not all of the embodiments. Based on the embodiment 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.

[0019] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top / bottom" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] Reference Figure 1 As shown, a preferred embodiment of the present invention is a laser ablation countermeasure UAV internal temperature field analysis test method, comprising the following steps: Step 1, preparing a test device: the test device includes a drone 1, a Bluetooth accelerometer 2, a high-energy laser emission component 3, a large-range thermal imager 4, and a high-speed camera 5; the Bluetooth accelerometer 2 is bonded to the drone 1, a high-energy laser emission component 3 is used to emit a high-energy laser to the drone 1, an infrared thermal image video of the drone 1 is taken by the large-range thermal imager 4, and a test image is taken by the high-speed camera 5; Step 2, conducting a laser ablation counter-drone test: remotely controlling the drone 1 to fly within the laser strike range of the high-energy laser emitting assembly 3, and when the high-energy laser emitting assembly 3 emits a high-energy laser to the drone 1 for ablation, recording the flight speed and acceleration of the drone 1, the high-speed camera 5 captures the flight posture image of the drone 1 during the laser ablation, the wide-range thermal imager obtains the infrared thermal image video of the drone 1 during the laser ablation, and derives the temperature-time curve of the surface of the ablated part of the drone 1 from the infrared thermal image video; Step 3, perform finite element simulation on the laser ablation counter-UAV test: import the two-dimensional image of the UAV 1 into the COMSOL software, add the fluid heat transfer physical field and the turbulence physical field, set the simulation parameters in the fluid heat transfer physical field and the turbulence physical field according to the test parameters in step 2, set the mesh size of the finite element simulation and the COMSOL software parameters, simulate the process of laser ablation counter-UAV 1, and derive the temperature-time simulation curve of the surface of the ablated part; Step 4, adjusting the mesh size of the finite element simulation and the parameters of the COMSOL software so that the experimental temperature-time curve and the simulated temperature-time curve are consistent, exporting the simulated thermal flow field change image inside the fuselage of the UAV 1, selecting the key points inside the fuselage, and exporting the temperature-time simulation curve of the key points inside the fuselage; Step 5, combining the laser ablation counter-UAV test and finite element simulation, based on the relationship between the flight attitude parameters of UAV 1 and the temperature-time simulation curve of the key points inside the fuselage, and the formula for the internal thermal flow field of UAV 1 fuselage, analyze the relationship between the internal thermal flow field of UAV 1 fuselage and the flight attitude.

[0022] As a preferred embodiment of the present invention, it may also have the following additional technical features: In this embodiment, in step 1, the high-energy laser emitting assembly 3 includes a high-energy laser 301, a freely rotating gimbal 302, a sight 303, and a radiator 304. The high-energy laser 301 is used to emit a high-energy laser, the freely rotating gimbal 302 is used to drive the high-energy laser 301 to rotate to adjust the emission direction, the sight 303 is used to emit an aiming laser, and the radiator 304 is used to dissipate heat for the high-energy laser 301.

[0023] In this embodiment, in step 3, a two-dimensional space dimension is selected in the model wizard in COMSOL, the material of the domain is set to air, and a transient study is selected; in the fluid heat transfer physics field and the turbulence physics field, the ablated part of the drone 1 is set as an air inlet and an air outlet.

[0024] In this embodiment, in step 3, According to the flight speed of the UAV 1 recorded in step 2 , set the wind speed at the air inlet in the turbulence physics field to ; In the fluid heat transfer physical field, the air temperature at the air inlet is set to the temperature obtained in step 2, and the initial temperature of the air is set to the initial real temperature of the test area; The total time range of laser ablation of the UAV 1 in step 2 is recorded, and the time unit in transient research is determined according to the total time range in step 2, and the total calculation time and time step are set.

[0025] In this embodiment, in step 5, the flight attitude parameters of the UAV 1 include pitch angle, yaw angle, roll angle, and acceleration.

[0026] In this embodiment, in step 5, the thermal flow field formula inside the fuselage of the drone 1 specifically includes: The thermal flow field inside the fuselage of UAV 1 satisfies the law of conservation of fluid momentum. equation: ; In the formula, For time; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; is the fluid density; is the fluid pressure; for Increment; is the dynamic viscosity; is the acceleration due to gravity; There is an axial balance between the incoming and outgoing mass flows: ; The fluid properties are related to temperature, and the coupling formula with the energy conservation equation is as follows: ; In the formula, is the specific heat capacity; is temperature; is the thermal conductivity; is the Stanton number.

[0027] Reference Figure 2 and Figure 3As shown, the present invention also provides a laser ablation countermeasure UAV internal temperature field analysis test device, including a UAV 1, a Bluetooth accelerometer 2, a high-energy laser emitting component 3, a large-range thermal imager 4, and a high-speed camera 5; the Bluetooth accelerometer 2 is bonded to the UAV 1, the high-energy laser emitting component 3 is arranged in the test area for emitting high-energy laser to the UAV 1, the large-range thermal imager 4 is arranged in the test area for shooting infrared thermal imaging video of the UAV 1, and the high-speed camera 5 is arranged in the test area for shooting test images.

[0028] In this embodiment, the high-energy laser emitting assembly 3 includes a high-energy laser 301, a free-rotating gimbal 302, a sight 303, and a radiator 304. The high-energy laser 301 and the sight 303 are arranged on the free-rotating gimbal 302. The high-energy laser 301 is used to emit a high-energy laser. The free-rotating gimbal 302 is used to drive the high-energy laser 301 to rotate to adjust the emission direction. The sight 303 is used to emit an aiming laser. The radiator 304 is arranged on the high-energy laser 301 to dissipate heat for the high-energy laser 301.

[0029] In this embodiment, a plurality of light sources 6 are further included, and the light sources 6 are arranged in the test area to illuminate the test area.

[0030] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and improved concepts of the present invention within the technical scope disclosed by the present invention, and they should be covered by the protection scope of the present invention.

Claims

1. A laser ablation countermeasure UAV internal temperature field analysis test method, characterized in that: The following steps are involved: Step 1, preparing a test device: the test device includes a drone, a Bluetooth accelerometer, a high-energy laser emission component, a large-range thermal imager, and a high-speed camera; the Bluetooth accelerometer is bonded to the drone, a high-energy laser is emitted to the drone through the high-energy laser emission component, an infrared thermal image video of the drone is captured through the large-range thermal imager, and a test image is captured through the high-speed camera; Step 2, conducting a laser ablation countermeasure UAV test: remotely controlling the UAV to fly within the laser strike range of the high-energy laser emitting assembly, and when the high-energy laser emitting assembly emits a high-energy laser to the UAV for ablation, recording the flight speed and acceleration of the UAV, the high-speed camera captures the flight posture image of the UAV during the laser ablation, the wide-range thermal imager obtains the infrared thermal image video of the UAV during the laser ablation, and derives the temperature-time curve of the surface of the ablated part of the UAV from the infrared thermal image video; Step 3, perform finite element simulation on the laser ablation counter-UAV test: import the two-dimensional image of the UAV into COMSOL software, add the fluid heat transfer physical field and the turbulence physical field, set the simulation parameters in the fluid heat transfer physical field and the turbulence physical field according to the test parameters in step 2, set the mesh size of the finite element simulation and the COMSOL software parameters, simulate the process of laser ablation counter-UAV, and derive the temperature-time simulation curve of the surface of the ablated part; Step 4, adjust the mesh size of the finite element simulation and the parameters of the COMSOL software so that the experimental temperature-time curve and the simulated temperature-time curve are consistent, export the simulated thermal flow field change image inside the fuselage of the drone, select the key points inside the fuselage, and export the temperature-time simulation curve of the key points inside the fuselage; Step 5, combining the laser ablation counter-UAV test and finite element simulation, based on the relationship between the UAV flight attitude parameters and the temperature-time simulation curve of the key points inside the fuselage, and the UAV internal thermal flow field formula, analyze the relationship between the UAV fuselage internal thermal flow field and the flight attitude.

2. According to claim 1, a laser ablation countermeasure UAV internal temperature field analysis test method is characterized in that: In step 1, the high-energy laser emitting assembly includes a high-energy laser, a freely rotating gimbal, a sight, and a radiator. The high-energy laser is used to emit a high-energy laser, the freely rotating gimbal is used to drive the high-energy laser to rotate to adjust the emission direction, the sight is used to emit an aiming laser, and the radiator is used to dissipate heat for the high-energy laser.

3. The laser ablation countermeasure UAV internal temperature field analysis test method according to claim 1 is characterized in that: In step 3, a two-dimensional space dimension is selected in the model wizard in COMSOL, the material of the domain is set to air, and a transient study is selected; in the fluid heat transfer physics field and the turbulence physics field, the ablated part of the drone is set as the air inlet and outlet.

4. The laser ablation countermeasure UAV internal temperature field analysis test method according to claim 3 is characterized in that: In step 3, According to the flight speed of the drone recorded in step 2 , set the wind speed at the air inlet in the turbulence physics field to ; In the fluid heat transfer physical field, the air temperature at the air inlet is set to the temperature obtained in step 2, and the initial temperature of the air is set to the initial real temperature of the test area; Record the total time range of laser ablation of the drone in step 2, determine the time unit in transient research based on the total time range in step 2, and set the total calculation time and time step.

5. The laser ablation countermeasure UAV internal temperature field analysis test method according to claim 1 is characterized in that: In step 5, the UAV flight attitude parameters include pitch angle, yaw angle, roll angle, and acceleration.

6. The laser ablation countermeasure UAV internal temperature field analysis test method according to claim 1 is characterized in that: In step 5, the thermal flow field formula inside the UAV fuselage specifically includes: The thermal flow field inside the UAV fuselage satisfies the law of conservation of fluid momentum. equation: ； In the formula, For time; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; The flow field center Coordinate components in direction; The flow field center The average relative velocity component in the direction; is the fluid density; is the fluid pressure; for Increment; is the dynamic viscosity; is the acceleration due to gravity; There is an axial balance between the incoming and outgoing mass flows: ； The fluid properties are related to temperature, and the coupling formula with the energy conservation equation is as follows: ； In the formula, is the specific heat capacity; is temperature; is the thermal conductivity; is the Stanton number.

7. A laser ablation countermeasure UAV internal temperature field analysis test device, characterized in that: It includes a drone, a Bluetooth accelerometer, a high-energy laser emitting component, a large-range thermal imager, and a high-speed camera; the Bluetooth accelerometer is bonded to the drone, the high-energy laser emitting component is arranged in a test area for emitting high-energy laser to the drone, the large-range thermal imager is arranged in the test area for shooting infrared thermal imaging video of the drone, and the high-speed camera is arranged in the test area for shooting test images.

8. The laser ablation countermeasure UAV internal temperature field analysis test device according to claim 7 is characterized in that: The high-energy laser emitting assembly includes a high-energy laser, a freely rotating gimbal, a sight, and a radiator. The high-energy laser and the sight are arranged on the freely rotating gimbal. The high-energy laser is used to emit a high-energy laser. The freely rotating gimbal is used to drive the high-energy laser to rotate to adjust the emitting direction. The sight is used to emit an aiming laser. The radiator is arranged on the high-energy laser to dissipate heat from the high-energy laser.

9. The laser ablation countermeasure UAV internal temperature field analysis test device according to claim 7, characterized in that: The invention also comprises a plurality of light sources, which are arranged in the test area and used for illuminating the test area.

Images