Aircraft braking process simulation demonstration device

Abstract

The invention discloses an aircraft braking process simulation demonstration device, which comprises an aircraft model, a transmission runway unit and a wind field simulation unit, and is characterized in that the aircraft model is provided with a tension sensor, one end of the transmission runway unit is a fixed end, and a pull rope is connected between the fixed end and the tension sensor; the transmission runway unit is used for driving the aircraft model to move in the direction away from the fixed end, the wind field simulation unit is arranged at the fixed end, and the wind field simulation unit is used for blowing air to the aircraft model, and the device has the advantages that various flight conditions can be effectively simulated, and accurate aircraft braking process experimental data can be provided.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft brake system demonstration, and particularly relates to an aircraft brake process simulation demonstration device. BACKGROUND

[0002] In the field of aviation, the brake system of an aircraft (such as an airplane) is crucial to ensuring flight safety, especially during landing. An effective brake system can prevent the aircraft from running off the runway and reduce the risk of accidents. With the continuous advancement of aviation technology, the performance requirements for aircraft brake systems are becoming increasingly high.

[0003] However, existing aircraft brake system testing methods typically include ground testing and flight testing. Ground testing mainly relies on a tow truck or other equipment to simulate the movement and braking process of an aircraft, but these methods often fail to effectively simulate various complex conditions encountered by an aircraft during actual flight, such as wind, friction, and the dynamic response of the aircraft. While flight testing can provide a more realistic testing environment, it is costly, risky, and not conducive to detailed analysis and evaluation of the brake system. SUMMARY

[0004] The main purpose of the present application is to provide an aircraft brake process simulation demonstration device, aiming to solve the technical problem that existing aircraft brake system testing methods are difficult to effectively simulate various flight conditions.

[0005] To achieve the above-mentioned purpose, the present application provides an aircraft brake process simulation demonstration device, which includes an aircraft model, a conveyor runway unit, and a wind field simulation unit. The aircraft model is provided with a tension sensor. One end of the conveyor runway unit is a fixed end, and a pull rope is connected between the fixed end and the tension sensor. The conveyor runway unit is used to drive the aircraft model to move away from the fixed end. The wind field simulation unit is arranged at the fixed end and is used to blow wind on the aircraft model.

[0006] Optionally, the aircraft model is further provided with a turbulence simulation unit, which includes a swing assembly and two turbulence plates. The swing assembly is arranged on the aircraft model, and the two turbulence plates are connected to the swing assembly and alternately swing under the action of the swing assembly to simulate airflow disturbance conditions.

[0007] Optionally, the swing assembly comprises a vertical plate, two moving blocks, two first telescopic members, two sliding blocks and two arc-shaped frames, the vertical plate is vertically arranged on the aircraft model, the two moving blocks are vertically and slidably arranged on two sides of the vertical plate, the sliding directions of the two moving blocks are opposite, the two first telescopic members are respectively connected to one side of the corresponding moving block, the two sliding blocks are respectively hingedly connected to the other end of the first telescopic member, the two spoilers are respectively connected to the side of the corresponding sliding block away from the first telescopic member, and the two arc-shaped frames are vertically arranged and the upper and lower ends of the arc-shaped frame are suspendedly connected to one side of the vertical plate through an extension rod, and the two sliding blocks are respectively slidably sleeved on the arc-shaped frame.

[0008] Optionally, the vertical plate is further provided with a driving assembly, and the driving assembly is used to drive the two moving blocks to slide simultaneously and in opposite directions.

[0009] Optionally, the driving assembly comprises a driving motor, a crank shaft, a swing rod and two limiting shafts, the driving motor is arranged on the vertical plate, the crank shaft is connected with the driving motor and movably penetrates through the vertical plate, the swing rod is movably connected to one side of the vertical plate through a movable shaft, a first guide sliding groove is formed in the eccentric position of the swing rod and slidably matched with the crank shaft, a second guide sliding groove is further formed on the swing rod and located on the two sides of the first guide sliding groove, the two limiting shafts are respectively connected to the side of the corresponding moving block away from the first telescopic member, and a section of the two limiting shafts is respectively slidably arranged in the second guide sliding groove.

[0010] Optionally, a fixed frame is further arranged on one side of the vertical plate, and the swing rod is located between the gap between the fixed frame and the vertical plate.

[0011] Optionally, the end of the aircraft model away from the wind field simulation unit is connected with a propeller, and the aircraft model is further provided with a horizontal sensor and a wind force sensor.

[0012] Optionally, the aircraft model is further provided with a controller and a mounting member for mounting the tension sensor, the tension sensor, the horizontal sensor and the wind force sensor are electrically connected with the controller, and the controller is further electrically connected with a display screen.

[0013] Optionally, the conveying runway unit comprises a support, a plurality of transmission rollers, a motor transmission assembly and a conveying belt, the plurality of transmission rollers are movably connected to the support, the transmission roller farthest from the fixed end is a driving roller, the motor transmission assembly is arranged on the support and used to drive the driving roller to rotate, and the conveying belt is wound on the plurality of transmission rollers and used to drive the aircraft model to move.

[0014] Optionally, the wind field simulation unit comprises a fixed support and a fan, the fixed support is arranged on the fixed end, and the fan is arranged on the top of the fixed support.

[0015] Optionally, the side of the fixed support close to the aircraft model is provided with a second telescopic member, the telescopic end of the second telescopic member is connected with a pulling ring, and the pulling ring is used to connect a pulling rope.

[0016] The beneficial effects that can be achieved by the present application are as follows: The present application comprises an aircraft model, a conveying runway unit and a wind field simulation unit, the aircraft model is provided with a tension sensor, one end of the conveying runway unit is a fixed end, a pull rope is connected between the fixed end and the tension sensor, the conveying runway unit is used to drive the aircraft model to move away from the fixed end, the wind field simulation unit is arranged at the fixed end, and the wind field simulation unit is used to blow wind on the aircraft model. Based on the structure of the present application, the aircraft model can be automatically driven to move by the conveying runway unit, so as to simulate the state of the aircraft moving on the ground, and the brake performance of the aircraft under different moving speeds can be tested, and the aircraft model can be blown by the wind field simulation unit to form an interference condition, so that different wind speed and wind force conditions can be simulated, and the stability and brake effect of the aircraft under the above interference conditions can be tested. The above simulation conditions can be performed individually or simultaneously, so that various simulation environments under different conditions can be formed, and the tension data can be collected in real time by the tension sensor during the simulation process, so that the brake performance data of the aircraft under different simulation conditions can be accurately evaluated. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the specific embodiments or the prior art will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual scale.

[0018] Figure 1 FIG. 1 is a structural schematic view of an aircraft brake process simulation demonstration device in an embodiment of the present application; Figure 2 FIG. 2 is a structural schematic view of an aircraft model and its connected accessories in an embodiment of the present application; Figure 3 FIG. 3 is a structural schematic view of a conveying runway unit in an embodiment of the present application; Figure 2 FIG. 4 is a partial enlarged structural schematic view of A in FIG. 3; Figure 4 FIG. 5 is a structural schematic view of a wind field simulation unit in an embodiment of the present application; Figure 2 FIG. 6 is another perspective view of the corresponding structure of FIG. 5; Figure 5 FIG. 7 is a structural schematic view of a tension sensor in an embodiment of the present application; Figure 2 FIG. 8 is another perspective view of the corresponding structure of FIG. 7.

[0019] Reference signs: 100 - aircraft model, 110 - propeller, 120 - mounting, 200 - transfer runway unit, 210 - support, 220 - transmission roller, 230 - motor transmission assembly, 240 - transfer belt, 300 - wind field simulation unit, 310 - fixed support, 320 - fan, 400 - turbulence simulation unit, 410 - turbulence plate, 420 - swing assembly, 421 - vertical plate, 4211 - vertical sliding groove, 422 - moving block, 423 - first telescopic piece, 424 - sliding block, 425 - arc-shaped frame, 426 - driving motor, 427 - crank shaft, 428 - swing rod, 4281 - first guide sliding groove, 4282 - second guide sliding groove, 429 - limiting shaft, 430 - fixed frame, 500 - display screen, 600 - second telescopic piece, 700 - pulling ring.

[0020] The implementation, functional features and advantages of the present application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present application will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0022] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture, and if the certain posture changes, the directional indications also change accordingly.

[0023] In the present application, unless otherwise explicitly specified and limited, the terms "connection", "fixation" and the like should be understood in a broad sense, for example, "connection" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection; can be direct connection, or indirect connection through an intermediate medium; can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0024] In addition, if the description of "first", "second", etc. is involved in the embodiments of the present application, the description of "first", "second", etc. is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can be explicitly or implicitly included at least one of the features. In addition, the meaning of "and / or" appearing throughout the text includes three parallel schemes. For example, "A and / or B" includes A scheme, or B scheme, or A and B scheme. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of ordinary skilled in the art. When the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope required by the present application.

[0025] Embodiments Referring to Figures 1-5 The embodiment provides a kind of aircraft brake process simulation demonstration device, including aircraft model 100, conveying runway unit 200 and wind field simulation unit 300, aircraft model 100 is provided with tension sensor (not shown in drawing), one end of conveying runway unit 200 is fixed end, and fixed end is connected with tension sensor between pull rope (not shown in drawing), conveying runway unit 200 is used to drive aircraft model 100 move towards the direction away from fixed end, wind field simulation unit 300 is set to fixed end, and wind field simulation unit 300 is used to blow wind to aircraft model 100.

[0026] In the embodiment, aircraft model 100 can be automatically driven to move by conveying runway unit 200, to simulate the state that aircraft moves on ground, and the brake performance of aircraft under different moving speeds can be tested, and aircraft model 100 can be blown by wind field simulation unit 300 to form interference condition, so that different wind speed and wind power conditions can be simulated, and the stability and brake effect of aircraft under the above interference condition can be tested, the above simulation condition can be carried out alone, or simultaneously, so that various simulation environments of different conditions can be formed, and the tension data can be collected in real time by tension sensor in simulation process, so that the brake performance data of aircraft under different simulation conditions can be accurately evaluated.

[0027] It should be noted that the aircraft model 100 can be an airplane model having at least three wheels, when the pulling rope pulls the pulling force sensor on the aircraft model 100, the aircraft model 100 drives the wheels to rotate under the action of the conveying runway unit 200, thereby forming relative movement to simulate the ground moving state of the aircraft, at this time, the aircraft model 100 is in an unbraked state, the pulling force sensor monitors the pulling force in real time, and then the aircraft model 100 performs a braking operation, at this time, the wheels of the aircraft model 100 are stopped, and a large sliding friction force is formed between the aircraft model 100 and the conveying runway unit 200, thereby testing the braking performance of the aircraft model 100 based on different sliding friction forces formed by different moving speeds.

[0028] As an optional implementation, the aircraft model 100 is further provided with a spoiler simulation unit 400, the spoiler simulation unit 400 includes a swing assembly 420 and two spoilers 410, the swing assembly 420 is arranged on the aircraft model 100, the two spoilers 410 are connected with the swing assembly 420, and the two spoilers 410 swing alternately under the action of the swing assembly 420 to simulate air flow disturbance conditions.

[0029] In the embodiment, the aircraft model 100 is further provided with the spoiler simulation unit 400, and the swing assembly 420 can drive the two spoilers 410 to swing alternately, thereby realizing spoiler effect, simulating air flow disturbance encountered by the aircraft model 100 in flight, and testing the stability thereof, here, the spoiler simulation unit 400 and the wind field simulation unit 300 can be performed separately or simultaneously, thereby simulating a complex interference environment, so that different interference conditions can be flexibly selected according to test requirements, and the simulation precision of the braking system of the aircraft model 100 under various complex conditions is improved.

[0030] As an optional implementation, the swing assembly 420 includes a vertical plate 421, two moving blocks 422, two first telescopic members 423, two sliding blocks 424 and two arc-shaped frames 425, the vertical plate 421 is vertically arranged on the aircraft model 100, the two moving blocks 422 are vertically and slidably arranged on both sides of the vertical plate 421, the sliding directions of the two moving blocks 422 are opposite, the two first telescopic members 423 are respectively connected to one side of the corresponding moving block 422, the two sliding blocks 424 are respectively hinged to the other end of the first telescopic member 423, the two spoilers 410 are respectively connected to the side of the corresponding sliding block 424 away from the first telescopic member 423, the two arc-shaped frames 425 are vertically arranged, and the upper and lower ends of the arc-shaped frame 425 are suspended and connected to one side of the vertical plate 421 through an extension rod, and the two sliding blocks 424 are respectively and slidably sleeved on the arc-shaped frame 425.

[0031] In the embodiment, the two moving blocks 422 are simultaneously vertically moved along the vertical plate 421 in opposite directions, when one of the moving blocks 422 moves to the highest position, the other moving block 422 moves to the lowest position, thereby driving the two first telescopic members 423 to move synchronously, at this time, the first telescopic members 423 can drive the sliding blocks 424 to slide along the arc-shaped frames 425 in an arc-shaped track, meanwhile, under the action of the arc-shaped track, the first telescopic members 423 are adaptively telescopic to cooperate with the change of the distance between the sliding blocks 424 and the vertical plate 421 when the sliding blocks 424 move to different positions of the arc-shaped frames 425, when the sliding blocks 424 move to different positions of the arc-shaped frames 425, the inclination angles of the sliding blocks 424 also correspondingly change, thereby driving the spoiler plates 410 to swing with the change of the inclination angles of the sliding blocks 424, cooperating with the up-and-down alternating movement of the two moving blocks 422, thereby realizing the alternating swinging of the two spoiler plates 410, the structure is compact, the design is ingenious, and the use requirement is met.

[0032] It should be noted that vertical sliding grooves 4211 corresponding to the sliding cooperation of the moving blocks 422 can be respectively formed on the two sides of the vertical plate 421, the structure is compact and reliable; the vertical plate 421 can adopt a “day” shaped structure, and the material is saved; the first telescopic member 423 adopts a combined structure of a sleeve and a sliding rod, the sleeve is fixedly connected to one side of the moving block 422, and the sliding rod can telescopically slide in the sleeve, and the other end of the sliding rod is hingedly connected with the sliding block 424.

[0033] As an optional embodiment, the vertical plate 421 is further provided with a driving assembly, the driving assembly is used for driving the two moving blocks 422 to simultaneously slide in opposite directions, thereby realizing the automatic swinging of the two spoiler plates 410.

[0034] As an optional embodiment, the driving assembly comprises a driving motor 426, a crank shaft 427, a swinging rod 428 and two limiting shafts 429, the driving motor 426 is arranged on the vertical plate 421, the crank shaft 427 is connected with the driving motor 426 and movably penetrates through the vertical plate 421, the swinging rod 428 is movably connected to one side of the vertical plate 421 through a movable shaft, a first guide sliding groove 4281 is formed in the eccentric position of the swinging rod 428 and slidably cooperates with the crank shaft 427, second guide sliding grooves 4282 are further formed on the swinging rod 428 and located on the two sides of the first guide sliding groove 4281, the two limiting shafts 429 are respectively connected to the sides of the corresponding moving blocks 422 away from the first telescopic members 423, and a section of the two limiting shafts 429 is respectively slidably arranged in the second guide sliding grooves 4282.

[0035] In the embodiment, when the spoiler 410 needs to be driven to swing, the driving motor 426 is started to drive the crank shaft 427 to rotate, the crank shaft 427 rotates and slides in the first guide sliding groove 4281, and the swing rod 428 swings around the movable shaft, that is, the swing rod 428 swings up and down alternately at two ends, so as to drive the limiting shaft 429 on the two sides of the swing rod 428 to move up and down alternately under the action of the second guide sliding groove 4282, thereby driving the corresponding moving block 422 to move synchronously. The structure is compact, the space occupation is small, and the design requirements are met.

[0036] As an optional embodiment, the stand plate 421 is further provided with a fixing frame 430 on one side, and the swing rod 428 is located between the gap between the fixing frame 430 and the stand plate 421. The fixing frame 430 can protect the swing rod 428 from winding with other pipelines when the swing rod 428 moves.

[0037] As an optional embodiment, the aircraft model 100 is connected with a propeller 110 away from the wind field simulation unit 300, and the propeller 110 is used for simulating the propulsion of the aircraft model 100. Here, the propeller 110 can be simulated by a fan. The aircraft model 100 is further provided with a horizontal sensor and a wind force sensor. The horizontal sensor is used for monitoring whether the chassis of the aircraft model 100 remains horizontal, and the wind force sensor is used for detecting wind force, so that monitoring data of the aircraft model 100 under various complex conditions can be collected in all aspects.

[0038] As an optional embodiment, the aircraft model 100 is further provided with a controller and a mounting piece 120 for mounting a tension sensor. The tension sensor, the horizontal sensor and the wind force sensor are electrically connected with the controller. The controller is further electrically connected with a display screen 500.

[0039] In the embodiment, different models of tension sensors can be detachably mounted through the mounting piece 120 to meet different test requirements. The data collected by the tension sensor, the horizontal sensor and the wind force sensor can be displayed on the display screen 500 after being processed by the controller, so that staff can intuitively view.

[0040] As an optional embodiment, the conveying runway unit 200 comprises a support 210, a plurality of transmission rollers 220, a motor transmission assembly 230 and a conveying belt 240. The plurality of transmission rollers 220 are movably connected to the support 210. The transmission roller 220 farthest from the fixed end is a driving roller. The motor transmission assembly 230 is arranged on the support 210 and is used for driving the driving roller to rotate. The conveying belt 240 is wound on the plurality of transmission rollers 220 and is used for driving the aircraft model 100 to move.

[0041] In the embodiment, the motor driving assembly 230 can drive the main roller to rotate, thereby driving the conveyor belt 240 and the plurality of transmission rollers 220 to rotate synchronously. The motor driving assembly 230 can provide different rotating speeds, thereby making the conveyor belt 240 form different moving speeds to simulate the braking performance of the aircraft model 100 at different moving speeds.

[0042] It should be noted that the motor driving assembly 230 includes a motor arranged at one side of the support 210. The motor is connected with a driving wheel. The driving wheel is connected with a driven wheel through a belt transmission. The driven wheel is connected with one end of the main roller. Different rotating speeds of the motor are arranged to realize different moving speeds of the conveyor belt 240.

[0043] As an optional embodiment, the wind field simulation unit 300 includes a fixed support 310 and a fan 320. The fixed support 310 is arranged at a fixed end. The conveyor belt 240 is located below the fixed support 310. The fan 320 is arranged on the top of the fixed support 310. The fan 320 can be arranged with different wind forces or gusts to simulate different wind speed conditions.

[0044] It should be noted that the fan 320 is installed on the fixed support 310 with an adjustable angle (the fan 320 can be rotatably connected on the top of the fixed support 310. After being adjusted to a corresponding angle, the fan 320 can be fixed by manual operation or using a fixing member). Different wind directions can be simulated to provide more simulation test data.

[0045] As an optional embodiment, the fixed support 310 is arranged with a second telescopic member 600 near one side of the aircraft model 100. A pulling ring 700 is connected with a telescopic end of the second telescopic member 600. The pulling ring 700 is used to connect a pulling rope.

[0046] In the embodiment, the pulling ring 700 is convenient to be detachably connected with the pulling rope. The second telescopic member 600 can be a telescopic cylinder. The distance between the aircraft model 100 and the wind field simulation unit 300 can be adjusted according to test requirements. The operation is flexible.

[0047] In summary, the application can simulate a plurality of condition combinations according to test requirements, including: (1) simultaneously starting the propeller 110, the wind field simulation unit 300 and the turbulence simulation unit 400 to realize simultaneous test of three interference modes; (2) only starting the propeller 110 and the wind field simulation unit 300 to realize simultaneous test of the two interference modes; (3) only starting the propeller 110 and the turbulence simulation unit 400 to realize simultaneous test of the two interference modes; (4) only start the wind field simulation unit 300 and the turbulence simulation unit 400 to realize the simultaneous test of the two interference modes; (5) start the propeller 110, the wind field simulation unit 300 or the turbulence simulation unit 400 alone to realize the test of a single interference mode.

[0048] Therefore, the present application can start various interference simulation conditions alone or in combination, so that the braking performance of the aircraft can be comprehensively evaluated.

[0049] The above is only the preferred embodiment of the present application, and does not limit the patent scope of the present application, and any equivalent structure or equivalent process transformation using the content of the specification and drawings of the present application, or direct or indirect application in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A device for simulating and demonstrating the braking process of an aircraft, characterized in that, include: An aircraft model, on which a tension sensor is installed; A transfer runway unit, one end of which is a fixed end, and a pull rope is connected between the fixed end and the tension sensor. The transfer runway unit is used to move the aircraft model away from the fixed end. A wind field simulation unit is disposed at the fixed end and is used to blow air onto the aircraft model.

2. The aircraft braking process simulation demonstration device as described in claim 1, characterized in that, The aircraft model is also equipped with a turbulence simulation unit, which includes: A swing assembly, wherein the swing assembly is disposed on the aircraft model; Two spoilers are connected to the swing assembly, and the two spoilers swing alternately under the action of the swing assembly to simulate airflow disturbance conditions.

3. The aircraft braking process simulation demonstration device as described in claim 2, characterized in that, The swing component includes: A vertical support plate is provided on the aircraft model. Two movable blocks are vertically slidably disposed on both sides of the upright plate, and the two movable blocks slide in opposite directions; Two first telescopic components are respectively connected to one side of the corresponding movable block; Two sliders are respectively hinged to the other end of the first telescopic member, and two spoilers are respectively connected to the side of the corresponding slider away from the first telescopic member; Two arc-shaped frames are arranged vertically, with their upper and lower ends suspended and connected to one side of the upright plate via extension rods. Two sliders are slidably fitted onto the arc-shaped frames.

4. The aircraft braking process simulation demonstration device as described in claim 3, characterized in that, The upright plate is also provided with a driving component, which is used to drive the two moving blocks to slide simultaneously in opposite directions.

5. The aircraft braking process simulation demonstration device as described in claim 4, characterized in that, The driving component includes: A drive motor is mounted on the upright plate; A crankshaft, which is connected to the drive motor and movably passes through the vertical plate; A swing rod, the middle part of which is movably connected to one side of the vertical plate via a movable shaft, a first guide groove is provided at the eccentric position of the swing rod to slide with the crank shaft, and a second guide groove is also provided on both sides of the first guide groove on the swing rod; Two limiting shafts are respectively connected to the side of the corresponding moving block away from the first telescopic member, and a section of each of the two limiting shafts is slidably disposed in the second guide groove.

6. The aircraft braking process simulation demonstration device as described in claim 5, characterized in that, A fixing frame is also provided on one side of the upright plate, and the swing rod is located between the fixing frame and the upright plate.

7. A simulation demonstration device for aircraft braking process as described in any one of claims 1-6, characterized in that, The aircraft model is connected to a thruster at the end furthest from the wind field simulation unit, and a level sensor and a wind force sensor are also installed on the aircraft model.

8. The aircraft braking process simulation demonstration device as described in claim 7, characterized in that, The aircraft model is also equipped with a controller and a mounting device for mounting the tension sensor. The tension sensor, the level sensor, and the wind sensor are all electrically connected to the controller, which is also electrically connected to a display screen.

9. The aircraft braking process simulation demonstration device as described in claim 1, characterized in that, The transfer runway unit includes: support; Multiple drive rollers are movably connected to the bracket, with the drive roller furthest from the fixed end being the driving roller. A motor drive assembly is mounted on the bracket and is used to drive the drive roller to rotate. A conveyor belt, which is wound around a plurality of the drive rollers, is used to move the aircraft model.

10. The aircraft braking process simulation demonstration device as described in claim 1, characterized in that, The wind field simulation unit includes: A fixed support is disposed at the fixed end; A fan is mounted on top of the fixed support.

11. The aircraft braking process simulation demonstration device as described in claim 10, characterized in that, A second telescopic component is provided on the side of the fixed support near the aircraft model. The telescopic end of the second telescopic component is connected to a pull ring, which is used to connect the pull rope.

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