An aircraft motion simulation platform and a target motion and scene simulation platform thereof

Abstract

This invention relates to the field of measurement technology, and more particularly to an aircraft motion simulation platform and its target motion and scene simulation platform, comprising three aircraft; two fixed guide rails; three movable guide rails, on which a first movable component is mounted; a second movable component, on which a telescopic rod is mounted; and a two-dimensional turntable. This invention consists of control guide rails and high-precision control motors, possessing five degrees of freedom in five directions: three degrees of translation and two degrees of rotation. It can simulate the spatial trajectory of a non-rotating aircraft and its spatial attitude at any given time. Simultaneously, the simulation platform incorporates an equal number of aircraft as the two-dimensional turntable, working in conjunction with the target motion and scene simulation platform to simulate the imaging characteristics of a target under visible light and infrared imaging conditions. This enables the verification of coordinated flight and detection by multiple aircraft, as well as the five-degree-of-freedom motion of aircraft in space.

Description

Technical Field

[0001] This invention relates to the field of measurement technology, and in particular to an aircraft motion simulation platform and its target motion and scene simulation platform. Background Technology

[0002] The statements herein provide only background information in relation to this invention and do not necessarily constitute prior art.

[0003] Aircraft simulation testing technology is a crucial part of the aircraft development process. It enables the simulation of an aircraft's spatial motion in a ground-based laboratory environment, thereby verifying and evaluating its guidance, navigation, and control systems. In existing technologies, typical aircraft motion simulation platforms usually employ a three-axis flight turntable to simulate the aircraft's attitude changes, i.e., three rotational degrees of freedom (pitch, yaw, and roll). This "one aircraft simulating three degrees of freedom" architecture is a common configuration in the current hardware-in-the-loop simulation field.

[0004] Existing three-degree-of-freedom turntables can only simulate the attitude angle changes of an aircraft, but cannot simultaneously simulate the three translational degrees of freedom (forward, backward, left, right, and up / down) of its center of mass in space. This results in simulation experiments failing to accurately reproduce the six-degree-of-freedom motion trajectory of the aircraft in space, as well as its complete spatial attitude at any point on the trajectory. For the verification of guidance and control systems that require precise simulation of the coupling effect between flight trajectory and attitude, this missing dimension will directly affect the confidence level of simulation experiments and the accuracy of evaluation results. Summary of the Invention

[0005] The purpose of this invention is to address the aforementioned shortcomings by providing an aircraft motion simulation platform and a target motion and scene simulation platform thereof.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: an aircraft motion simulation platform, used to cooperate with and simulate the changes in the motion state of an aircraft in space, comprising three aircraft; Two fixed guide rails are arranged in parallel and spaced relative to each other to drive the aircraft to translate in space along the Y-axis. Three movable guide rails are spaced apart and intersect perpendicularly on two of the fixed guide rails. Each movable guide rail is connected to a movable component at the end of the fixed guide rail for linear movement along the length of the fixed guide rail, which drives the aircraft to translate in space along the X-axis. The second moving component has the same number as the movable guide rail and moves linearly along the length of the movable guide rail. The second moving component is provided with a telescopic rod for driving the aircraft to translate in space along the Z-axis. Two-dimensional turntables, in equal numbers to and corresponding to the aircraft, are fixed at the top of the telescopic rod and are used to simulate and drive the aircraft to perform pitch and yaw movements.

[0007] Furthermore, the moving component includes a first slide table located at the end of the movable guide rail and adapted to move on the fixed guide rail, and a Y-axis motion motor disposed on one side of the first slide table. The output side of the Y-axis motion motor is provided with two meshing first gears a and b, and a first rack fixed on the end face of the fixed guide rail is fitted on the first gear b.

[0008] Furthermore, the second movable component includes a second slide adapted to move on the movable guide rail, an X-axis motion motor located on the second slide, and two meshing second gears a and b provided on the output side of the X-axis motion motor. A second rack that cooperates with the second gear b is provided on the movable guide rail at the same length.

[0009] Furthermore, a Z-axis motion motor is also provided on the second slide. A worm gear is provided at the output end of the Z-axis motion motor. A worm wheel is provided on one side of the worm gear. A winding shaft is passed through the end face of the worm wheel. A pull wire for driving the telescopic rod to move up and down is provided on the winding shaft. One end of the pull wire is fixed on the winding shaft and the other end is fixed on one side of the movable end of the telescopic rod. The worm gear and the worm wheel cooperate with each other to maintain the original height and position of the telescopic rod in the event of a power failure of the Z-axis motion motor.

[0010] Furthermore, the two-dimensional turntable includes a bracket one located at the top of the telescopic rod, left and right angle motors located on the end face of the bracket one and connected to the top of the telescopic rod, a pitch angle motor horizontally arranged on one side inside the bracket one, a bracket two arranged on the output side of the pitch angle motor, and the two legs of the bracket two rotatably connected to the two legs of the bracket one through pins.

[0011] Furthermore, the second support is provided with a mounting bracket for fixing the aircraft, and the second support is also provided with a detection unit for detecting the target.

[0012] An aircraft target motion and scene simulation platform, comprising: A realistic sand table, constructed with a frame, is used to simulate the target area environment of the aircraft. The target model is moved and set on the real-world sand table. The target model is divided into static targets and dynamic targets, and is used to simulate the target state on the real-world sand table. An ambient light control module, located on the real-world sand table, is used to simulate the lighting environment under different orientations and illuminances in the visible light band.

[0013] Furthermore, the real-life sand table is divided into three areas: Area 1, Area 2, and Area 3. Area 1 is set as a room temperature area, while Area 2 and Area 3 are both heated areas. The temperature of Area 1 is set to be greater than or equal to 50°C, and the temperature of Area 3 is set to be greater than or equal to 80°C. The heated area adopts a 5-layer structure, which consists of a stainless steel base plate, a mineral wool insulation layer, a heating layer, an aluminum heat-conducting layer, and a surface model layer, arranged sequentially from bottom to top.

[0014] Furthermore, the static target adopts the same geometric appearance as the real target, and its external dimensions are simulated according to the ratio of the static target to the three-dimensional space; The dynamic target is made of metal and has a low-pressure heating film and a platinum resistance temperature sensor inside. The low-pressure heating film and the platinum resistance temperature sensor are connected to a back-end computer via wires, and the back-end computer controls and displays the temperature of the dynamic target to simulate the infrared characteristics of the dynamic target. The motion simulation of the dynamic target adopts a slide rail slider connection mechanism. The slide rail is equipped with a synchronous belt for driving the slider to move and a motor for cooperating with the synchronous belt. The synchronous belt is equipped with a tensioning wheel for adjusting the tension of the synchronous belt. The slider is equipped with a trolley support for fixing the dynamic target. The motor is started, and the dynamic target is moved on the real-world sand table by the motor and the synchronous belt. When the dynamic target is tracked and locked by the aircraft, it stops moving to simulate the state of the dynamic target being hit.

[0015] Furthermore, the ambient light control module includes a main control soft control light source switch and a main light that works in conjunction with the main control soft control light source switch and is located on the real-scene sand table. The main control soft control light source switch is used to adjust the brightness and color temperature of the light source. The main light is a 50W white ceiling light and adjustable focus track lights located on the four sides of the ceiling light to simulate midday and dusk ambient light conditions.

[0016] The beneficial effects of this invention are reflected in: This invention consists of a control guide rail and a high-precision control motor, possessing five degrees of freedom in five directions: three degrees of translation and two degrees of rotation. It can simulate the spatial trajectory of a non-rotating aircraft and its spatial attitude at any given time. Simultaneously, an equal number of aircraft designed on the simulation platform, along with a target motion and scene simulation platform, can simulate the imaging characteristics of the target under visible light and infrared imaging conditions. This enables the verification of coordinated flight and detection by multiple aircraft, as well as the five-degree-of-freedom motion of the aircraft in space. Attached Figure Description

[0017] Figure 1 This is a perspective view of the overall structure of an embodiment of the present invention. Figure 2 This is a diagram of the temperature zone structure in the sand table.

[0018] In the picture: 1. Fixed guide rail; 2. Movable guide rail; 3. Movable component one; 4. Movable component two; 5. Telescopic rod; 6. Two-dimensional turntable. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Please see Figure 1-2 This invention discloses an aircraft motion simulation platform for coordinating and simulating changes in the motion state of an aircraft in space, comprising three aircraft. Two fixed guide rails 1 are arranged in parallel and at intervals relative to each other to drive the aircraft to translate in space along the Y-axis direction; Three movable guide rails 2 are spaced apart and intersect perpendicularly on two fixed guide rails 1. The movable guide rails 2 are respectively connected to the ends of the fixed guide rails 1 and are provided with movable components 3 for linear movement along the length direction of the fixed guide rails 1, which are used to drive the aircraft to translate in space along the X-axis direction. The second movable component 4 is the same number as the movable guide rail 2 and moves linearly along the length direction of the movable guide rail 2. The second movable component 4 is provided with a telescopic rod 5 for driving the aircraft to translate in space along the Z-axis direction. Two-dimensional turntables 6, in equal numbers to and corresponding to the aircraft, are fixed to the top of the telescopic rod 5 and are used to simulate and drive the aircraft to perform pitch and yaw movements.

[0021] In specific implementation, by using two fixed guide rails 1 that are parallel and relatively arranged in space, and three movable guide rails 2 that are vertically arranged and spaced apart on the two fixed guide rails 1, and telescopic rods 5 that move accordingly on the movable guide rails 2, the aircraft fixed at the top of the corresponding telescopic rods 5 can be driven to simulate the flatness of three degrees of freedom in space through the movable component 1 3 and the movable component 2 4. Furthermore, by installing a two-dimensional turntable 6 at the top of the telescopic rod 5, it is possible to simulate the rotation of the corresponding aircraft in space with two degrees of freedom. This allows the platform to simultaneously simulate the five-degree-of-freedom motion of three aircraft in space, presenting the spatial trajectory of a non-rotating aircraft and its spatial attitude at any given moment.

[0022] In one embodiment, the moving component 3 includes a first slide located at the end of the movable guide rail 2 and adapted to move on the fixed guide rail 1, and a Y-axis motion motor disposed on one side of the first slide. The output side of the Y-axis motion motor is provided with two meshing first gears a and b. A first rack fixed to the end face of the fixed guide rail 1 is fitted onto the first gear b. With this design, by welding the first slide to the end of the movable guide rail 2 and moving the first slide relative to the fixed guide rail 1, the Y-axis motion motor is activated. The reducer formed by the first gears a and b drives the first gear b to rotate. The first gear b meshes with the first rack welded to or fixed to the end face of the fixed guide rail 1, thereby causing the first slide and the movable guide rail 2 to move linearly along the Y-axis.

[0023] It should be noted that the reducer consisting of the first gear a and the first gear b can multiply the two single-stage transmission ratios through two-stage transmission. For example, if the first-stage transmission ratio is 1:5 and the second-stage transmission ratio is 1:4, the total transmission ratio can reach 1:20, which can easily realize the "reduction and torque increase" of the Y-axis motion motor, using a high-speed, low-torque Y-axis motion motor to output low-speed, high-torque power.

[0024] In one embodiment, the second movable component 4 includes a second slide adapted to move on the movable guide rail 2, and an X-axis motion motor located on the second slide. The output side of the X-axis motion motor is provided with two meshing second gears a and b. A second rack of equal length is provided on the movable guide rail 2 to mesh with the second gear b. With this design, the movement on the movable guide rail 2 is achieved by the X-axis motion motor driving the second gear b to rotate via a reducer composed of the second gears a and b. The meshing of the second gear b with the second rack causes the second slide to move linearly along the X-axis.

[0025] It should be noted that the reducer consisting of the second gear a and the second gear b can multiply the two single-stage transmission ratios through two-stage transmission. For example, if the first-stage transmission ratio is 1:5 and the second-stage transmission ratio is 1:4, the total transmission ratio can reach 1:20, which can easily realize the "reduction and torque increase" of the X-axis motion motor, using a high-speed, low-torque X-axis motion motor to output low-speed, high-torque power.

[0026] In one embodiment, a Z-axis motion motor is also provided on the second slide. A worm gear is provided at the output end of the Z-axis motion motor. A worm wheel is provided on one side of the worm gear. A winding shaft is passed through the end face of the worm wheel. A pull wire for driving the telescopic rod 5 to move up and down is provided on the winding shaft. One end of the pull wire is fixed on the winding shaft and the other end is fixed on one side of the movable end of the telescopic rod 5. The worm and worm wheel cooperate to maintain the telescopic rod 5 at its original height and position in the event of a power failure of the Z-axis motor. This design, via the Z-axis motor mounted on the second slide and a worm gear reducer driven by the Z-axis motor and composed of the worm and worm wheel, rotates the winding shaft. The winding of the wire on the shaft then drives the telescopic rod 5 up and down. Because the Z-axis is vertically mounted and bears a certain weight, the worm gear reducer provides a degree of self-locking, ensuring the telescopic rod 5 remains in its original position even when the Z-axis motor loses power.

[0027] It should be noted that, in order to prevent movement beyond the range or collisions between axes, there are three layers of protection measures: software limit, limit switch limit, and mechanical hard limit.

[0028] In one embodiment, the two-dimensional turntable 6 includes a first bracket located at the top of the telescopic rod 5, and left and right angle motors disposed on the end face of the first bracket and connected to the top of the telescopic rod 5. A pitch motor is horizontally disposed on one side inside the first bracket, and a second bracket is disposed on the output side of the pitch motor. The two legs of the second bracket are rotatably connected to the two legs of the first bracket via pins. With this design, by using the first bracket installed at the top of the telescopic rod 5, and the left and right angle motors coaxially installed inside the first bracket with the telescopic rod 5, the left and right angle motors can be activated to drive the first bracket installed on the telescopic rod 5 to rotate relative to the telescopic rod 5 and control the azimuth angle of the aircraft, with a range of ±70°. A pitch motor is also installed horizontally inside the first support. When the pitch motor is started, it drives the second support, which is installed on its output side and rotates with the first support, to perform pitch angle movement, so as to control the pitch angle of the aircraft. The range can reach ±70°, thereby simulating the pitch and yaw motion of the aircraft.

[0029] In one embodiment, the second support is equipped with a mounting bracket for fixing the aircraft, and a detection unit for detecting targets is also provided on the second support. This design, with the mounting bracket welded to the top surface of the second support to fix the aircraft one by one according to the number of supports, and the detection units installed on the second support, such as visible light, infrared, and low-light detectors, simulate the aircraft's detection and attack on targets, realizing semi-physical simulation verification of algorithms such as target detection, formation coordination, and guidance control. To simulate the "human-in-the-loop" guidance method, the ground control station and the onboard camera can perform bidirectional real-time transmission of image information and control commands.

[0030] It should be noted that the detection unit includes, but is not limited to, visible light, infrared, low light, and cameras that transmit image information and control commands in real time.

[0031] An aircraft target motion and scene simulation platform, comprising: A realistic sand table, constructed with a frame, is used to simulate the target area environment of the aircraft. The target model is moved and set on the real-world sand table. The target model is divided into static targets and dynamic targets, and is used to simulate the target state on the real-world sand table. An ambient light control module, located on the real-world sand table, is used to simulate the lighting environment under different orientations and illuminances in the visible light band.

[0032] In practice, the aircraft target motion and scene simulation platform, which consists of a simulated target, a real-scene sand table, and an ambient light control module, is used to simulate the imaging characteristics of the target under visible light imaging, infrared imaging, and other conditions. The real-scene sand table is mainly used to simulate the environment of the target area, providing terrain conditions, background temperature, and scene for the moving target. The target can emit sound and light alarms after being tracked, locked, and hit by the aircraft. If it is in motion, it will stop moving to simulate the effect of being hit.

[0033] It should be noted that audible and visual alarms are compatible with the installation of dynamic targets.

[0034] In one embodiment, the realistic sand table is divided into three areas: Area 1, Area 2, and Area 3. Area 1 is a room temperature zone, while Areas 2 and 3 are both heated zones. The temperature of Area 1 is set to be greater than or equal to 50°C, and the temperature of Area 3 is set to be greater than or equal to 80°C. The heated zones have a five-layer structure, consisting of a stainless steel base plate, a mineral wool insulation layer, a heating layer, an aluminum heat-conducting layer, and a surface model layer, arranged sequentially from bottom to top. This design divides the realistic sand table into three different temperature zones: Area 1 is a room temperature zone, Area 2 is a zone with a temperature not lower than 50°C, and Area 3 is a zone with a temperature not lower than 80°C. Areas 2 and 3 are both heated zones, and the heated zones have a total of five layers. Figure 2 As shown, the temperatures of the two heating zones are controllable, using polyimide heating belts, with PT100 as the temperature sensing element, and a PLC as the main control device, which can be adjusted as needed.

[0035] It should be noted that the five-layer structure of "stainless steel base plate - mineral wool insulation layer - heating layer - aluminum plate heat conduction layer - surface model layer" is adopted. Among them, the mineral wool insulation layer, heating layer and aluminum plate heat conduction layer enable the real scene sand table to be heated to the set temperature quickly and evenly and maintain a stable temperature field, avoiding local overheating or overcooling, and achieving efficient and uniform heating and temperature control. The stainless steel base plate is used as a rigid foundation, providing a sturdy support platform to prevent the entire structure from bending and ensure the flatness and long-term stability of the real scene sand table surface. The mineral wool insulation layer is used for heat preservation and plays a certain buffering role, reducing the stress transmission from the bottom layer to the heating layer and heat conduction layer. The surface model layer can simulate temperature-related physical phenomena, which can more realistically simulate the scene of the target area.

[0036] In one embodiment, the static target adopts the same geometric appearance as the real target, and its external dimensions are simulated according to the ratio of the static target to three-dimensional space; The dynamic target is made of metal and has a low-pressure heating film and a platinum resistance temperature sensor inside. The low-pressure heating film and the platinum resistance temperature sensor are connected to a back-end computer via wires, and the back-end computer controls and displays the temperature of the dynamic target to simulate the infrared characteristics of the dynamic target. The motion simulation of the dynamic target adopts a slide rail slider connection mechanism. The slide rail is equipped with a synchronous belt for driving the slider to move and a motor for cooperating with the synchronous belt. The synchronous belt is equipped with a tensioning wheel for adjusting the tension of the synchronous belt. The slider is equipped with a trolley support for fixing the dynamic target. The motor is started, and the motor and the synchronous belt drive the dynamic target to move on the realistic sand table. When the dynamic target is tracked, locked, and hit by the aircraft, it stops moving to simulate the state of the dynamic target being hit. In this design, by using static and dynamic targets, the shape and size of the static target are simulated according to the ratio of the target to three-dimensional space, while the dynamic target is realized by simulating the target's movement speed and infrared characteristics. To simulate the infrared characteristics of the target, the dynamic target is made of metal and internally equipped with a low-pressure heating film and a platinum resistance temperature sensor. The target's temperature is controlled and displayed by a wired computer. The motion simulation of the dynamic target uses a sliding rail and slider mechanism, with a motor and synchronous belt driving the trolley. The synchronous belt's tension can be adjusted via a tensioning pulley to facilitate adjustment of the trolley's stability, and the speed is controlled within a range of 0–1.0 m / s. The dynamic target emits audible and visual alarms upon being tracked, locked, and hit by the aircraft; if it is in motion, it stops moving to simulate the effect of being hit.

[0037] In one embodiment, the ambient light control module includes a main control soft-control light source switch and a main light located on the realistic sand table, which works in conjunction with the main control soft-control light source switch. The main control soft-control light source switch is used to adjust the brightness and color temperature of the light source. The main light is a 50W white ceiling light and adjustable focus track lights located on all four sides of the ceiling light, used to simulate midday and dusk ambient lighting conditions. This design, using the 50W white ceiling light and adjustable focus track lights on all four sides of the ceiling light on the realistic sand table, along with the installed main control soft-control light source switch, allows for the adjustment of the brightness and color temperature of the light source, simulating midday and dusk ambient lighting conditions. This achieves the simulation of lighting environments under different orientations and illuminances in the visible light band, suitable for aircraft target detection and guidance control.

[0038] The electrical components described in this article are controlled automatically by a controller. The controller circuit can be implemented by a person skilled in the art through simple programming. The power supply is also common knowledge in the field. Furthermore, since this application is mainly used to protect mechanical devices, the control method and circuit connection will not be explained in detail here.

[0039] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0040] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0041] Additionally, "multiple" refers to two or more.

[0042] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An aircraft motion simulation platform, used to coordinate and simulate changes in the motion state of an aircraft in space, characterized in that: Includes three aircraft; Two fixed guide rails (1) are arranged in parallel and at intervals to drive the aircraft to translate in space along the Y-axis. Three movable guide rails (2) are spaced apart and intersect perpendicularly on two fixed guide rails (1). The movable guide rails (2) are respectively connected to the ends of the fixed guide rails (1) and are provided with a movable component (3) for linear movement along the length direction of the fixed guide rails (1) to drive the aircraft to translate in space along the X-axis direction. The second moving component (4) is equal in number to the movable guide rail (2) and moves linearly along the length direction of the movable guide rail (2). The second moving component (4) is provided with a telescopic rod (5) for driving the aircraft to translate in space along the Z-axis direction. Two-dimensional turntables (6) are equal in number to the number of aircraft and are fixed to the aircraft. They are set at the top of the telescopic rod (5) to simulate and drive the aircraft to pitch and yaw.

2. The aircraft motion simulation platform according to claim 1, characterized in that: The moving component (3) includes a first slide located at the end of the movable guide rail (2) and adapted to move on the fixed guide rail (1), and a Y-axis motion motor located on one side of the first slide. The output side of the Y-axis motion motor is provided with two meshing first gears a and b. A first rack fixed on the end face of the fixed guide rail (1) is provided on the first gear b.

3. The aircraft motion simulation platform according to claim 1, characterized in that: The second movable component (4) includes a second slide adapted to move on the movable guide rail (2) and an X-axis motion motor located on the second slide. The output side of the X-axis motion motor is provided with two meshing second gears a and b. The movable guide rail (2) is provided with a second rack of equal length that cooperates with the second gear b.

4. The aircraft motion simulation platform according to claim 3, characterized in that: The second slide is also equipped with a Z-axis motion motor. The output end of the Z-axis motion motor is equipped with a worm gear. A worm wheel is provided on one side of the worm gear. A winding shaft is passed through the end face of the worm wheel. A pull wire for driving the telescopic rod (5) to move up and down is provided on the winding shaft. One end of the pull wire is fixed on the winding shaft and the other end is fixed on one side of the movable end of the telescopic rod (5). The worm gear and the worm wheel cooperate with each other to maintain the original height and position of the telescopic rod (5) in the event of a power failure of the Z-axis motion motor.

5. The aircraft motion simulation platform according to claim 1, characterized in that: The two-dimensional turntable (6) includes a bracket one located at the top of the telescopic rod (5), left and right angle motors located on the end face of the bracket one and connected to the top of the telescopic rod (5), a pitch angle motor horizontally arranged on one side inside the bracket one, a bracket two arranged on the output side of the pitch angle motor, and the two legs of the bracket two are rotatably connected to the two legs of the bracket one through pins.

6. The aircraft motion simulation platform according to claim 5, characterized in that: The second support is equipped with a mounting bracket for fixing the aircraft, and the second support is also equipped with a detection unit for detecting the target.

7. An aircraft target motion and scene simulation platform, used in conjunction with an aircraft motion simulation platform as described in any one of claims 1-6, characterized in that, include: A realistic sand table, constructed with a frame, is used to simulate the target area environment of the aircraft. The target model is moved and set on the real-world sand table. The target model is divided into static targets and dynamic targets, and is used to simulate the target state on the real-world sand table. An ambient light control module, located on the real-world sand table, is used to simulate the lighting environment under different orientations and illuminances in the visible light band.

8. The aircraft target motion and scene simulation platform according to claim 7, characterized in that: The real-life sand table is divided into three areas: Area 1, Area 2, and Area 3. Area 1 is set as a room temperature area, while Area 2 and Area 3 are both heated areas. The temperature of Area 1 is set to be greater than or equal to 50°C, and the temperature of Area 3 is set to be greater than or equal to 80°C. The heated area adopts a 5-layer structure, which consists of a stainless steel base plate, a mineral wool insulation layer, a heating layer, an aluminum heat-conducting layer, and a surface model layer, arranged from bottom to top.

9. The aircraft target motion and scene simulation platform according to claim 7, characterized in that: The static target adopts the same geometric appearance as the real target, and its external dimensions are simulated according to the ratio of the static target to the three-dimensional space; The dynamic target is made of metal and has a low-pressure heating film and a platinum resistance temperature sensor inside. The low-pressure heating film and the platinum resistance temperature sensor are connected to a back-end computer via wires, and the back-end computer controls and displays the temperature of the dynamic target to simulate the infrared characteristics of the dynamic target. The motion simulation of the dynamic target adopts a slide rail slider connection mechanism. The slide rail is equipped with a synchronous belt for driving the slider to move and a motor for cooperating with the synchronous belt. The synchronous belt is equipped with a tensioning wheel for adjusting the tension of the synchronous belt. The slider is equipped with a trolley support for fixing the dynamic target. The motor is started, and the dynamic target is moved on the real-world sand table by the motor and the synchronous belt. When the dynamic target is tracked and locked by the aircraft, it stops moving to simulate the state of the dynamic target being hit.

10. The aircraft target motion and scene simulation platform according to claim 7, characterized in that: The ambient light control module includes a main control soft control light source switch and a main light that works in conjunction with the main control soft control light source switch and is located on the real-scene sand table. The main control soft control light source switch is used to adjust the brightness and color temperature of the light source. The main light is a 50W white ceiling light and adjustable focus track lights located on the four sides of the ceiling light to simulate midday and dusk ambient light conditions.

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