An aircraft brake process simulation demonstration device

Abstract

The application discloses a kind of aircraft brake process simulation demonstration device, including aircraft model, conveying runway unit and wind field simulation unit, aircraft model is provided with tension sensor, one end of conveying runway unit is fixed end, and fixed end is connected with pull rope between tension sensor, conveying runway unit is used to drive aircraft model to move in the direction away from fixed end, wind field simulation unit is set to fixed end, and wind field simulation unit is used to blow wind to aircraft model, the application has the advantages that various flight conditions can be effectively simulated, and accurate aircraft brake process experimental data can be provided.

Description

Technical Field

[0001] This application relates to the field of aircraft braking system demonstration technology, and in particular to an aircraft braking process simulation demonstration device. Background Technology

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

[0003] Existing testing methods for aircraft braking systems typically include ground testing and flight testing. Ground testing mainly relies on towing vehicles or other equipment to simulate the movement and braking process of the aircraft. However, these methods often fail to effectively simulate the various complex conditions encountered by the aircraft in actual flight, such as wind force, friction, and the dynamic response of the aircraft. Although flight testing can provide a more realistic testing environment, it is costly, risky, and not conducive to detailed analysis and evaluation of the braking system. Summary of the Invention

[0004] The main purpose of this application is to provide a simulation demonstration device for the braking process of an aircraft, which aims to solve the technical problem that existing aircraft braking system testing methods are difficult to effectively simulate various flight conditions.

[0005] To achieve the above objectives, this application provides a simulation demonstration device for the braking process of an aircraft, including an aircraft model, a transfer runway unit, and a wind field simulation unit. A tension sensor is installed on the aircraft model. One end of the transfer runway unit 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. The wind field simulation unit is located at the fixed end and is used to blow air onto the aircraft model.

[0006] Optionally, the aircraft model is also equipped with a turbulence simulation unit, which includes a swing component and two spoilers. The swing component is set on the aircraft model, and the two spoilers are connected to the swing component. The two spoilers swing alternately under the action of the swing component to simulate airflow disturbance conditions.

[0007] Optionally, the swing assembly includes a vertical plate, two movable blocks, two first telescopic members, two sliders, and two arc-shaped frames. The vertical plate is vertically mounted on the aircraft model. The two movable blocks are vertically slidably mounted on both sides of the vertical plate, and the two movable blocks slide in opposite directions. The two first telescopic members are respectively connected to one side of the corresponding movable block. The two sliders are respectively hinged to the other end of the first telescopic members. The two spoilers are respectively connected to the side of the corresponding slider away from the first telescopic members. The two arc-shaped frames are vertically arranged, and the upper and lower ends of the arc-shaped frames are suspended and connected to one side of the vertical plate through extension rods. The two sliders are respectively slidably mounted on the arc-shaped frames.

[0008] Optionally, a drive component is also provided on the upright plate, which is used to drive the two moving blocks to slide simultaneously in opposite directions.

[0009] Optionally, the drive assembly includes a drive motor, a crankshaft, a swing arm, and two limiting shafts. The drive motor is mounted on the upright plate, the crankshaft is connected to the drive motor and movably passes through the upright plate, the middle part of the swing arm is movably connected to one side of the upright plate via a movable shaft, a first guide groove is provided at the eccentric position of the swing arm to slide with the crankshaft, and a second guide groove is also provided on both sides of the first guide groove on the swing arm. 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 each of the two limiting shafts is slidably disposed in the second guide groove.

[0010] Optionally, 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.

[0011] Optionally, a thruster is connected to the end of the aircraft model away from the wind field simulation unit, and a horizontal sensor and a wind force sensor are also installed on the aircraft model.

[0012] Optionally, the aircraft model is also equipped with a controller and a mounting device for installing a tension sensor. The tension sensor, level sensor, and wind sensor are all electrically connected to the controller, which is also electrically connected to a display screen.

[0013] Optionally, the transfer runway unit includes a support frame, multiple drive rollers, a motor drive assembly, and a conveyor belt. The multiple drive rollers are movably connected to the support frame, and the drive roller furthest from the fixed end is the drive roller. The motor drive assembly is mounted on the support frame and is used to drive the drive roller to rotate. The conveyor belt is wound around the multiple drive rollers and is used to move the aircraft model.

[0014] Optionally, the wind farm simulation unit includes a fixed support and a fan, with the fixed support located at a fixed end and the fan located on top of the fixed support.

[0015] Optionally, a second telescopic component is provided on the side of the fixed support near the aircraft model, and the telescopic end of the second telescopic component is connected to a pull ring, which is used to connect a pull rope.

[0016] The beneficial effects that this application can achieve are as follows: This application includes an aircraft model, a transfer runway unit, and a wind field simulation unit. A tension sensor is installed on the aircraft model. One end of the transfer runway unit is fixed, and a tension rope connects the fixed end to the tension sensor. The transfer runway unit is used to move the aircraft model away from the fixed end. The wind field simulation unit is located at the fixed end and is used to blow air onto the aircraft model. Based on the structure of this application, the transfer runway unit can automatically move the aircraft model, simulating the aircraft's movement on the ground. This allows for testing the aircraft's braking performance at different speeds. The wind field simulation unit creates disturbance conditions by blowing air onto the aircraft model, simulating different wind speeds and forces. This allows for testing the aircraft's stability and braking effect under these disturbance conditions. These simulation conditions can be performed individually or simultaneously, creating various simulation environments. Furthermore, the tension sensor can collect tension data in real time during the simulation, allowing for accurate evaluation of the aircraft's braking performance under different simulation conditions. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings 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, the elements or parts are not necessarily drawn to scale.

[0018] Figure 1 This is a schematic diagram of the structure of an aircraft braking process simulation demonstration device according to an embodiment of this application; Figure 2 This is a schematic diagram of the structure of the aircraft model and its connecting accessories in the embodiments of this application; Figure 3 for Figure 2 A magnified schematic diagram of the partial structure at point A in the middle; Figure 4 for Figure 2 A schematic diagram of the corresponding structure from another perspective; Figure 5 for Figure 2 A schematic diagram of the corresponding structure from another perspective.

[0019] Figure label: 100-Aircraft model, 110-Thruster, 120-Mounting component, 200-Transfer runway unit, 210-Support, 220-Transmission roller, 230-Motor transmission assembly, 240-Conveyor belt, 300-Wind field simulation unit, 310-Fixed support, 320-Wind fan, 400-Disturbance simulation unit, 410-Disturbance plate, 420-Swing assembly, 421-Upright plate, 4211-Vertical slide, 422-Moving block, 423-First telescopic component, 424-Slider, 425-Arc frame, 426-Drive motor, 427-Crankshaft, 428-Swing rod, 4281-First guide slide, 4282-Second guide slide, 429-Limiting shaft, 430-Fixed frame, 500-Display screen, 600-Second telescopic component, 700-Pull ring.

[0020] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0021] The technical solutions of the embodiments of this application 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 this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0022] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0023] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral part; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0024] Furthermore, if the embodiments of this application 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 meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, 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. When 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 in this application.

[0025] Example Reference Figures 1-5 This embodiment provides a simulation demonstration device for the braking process of an aircraft, including an aircraft model 100, a transfer runway unit 200, and a wind field simulation unit 300. A tension sensor (not shown in the figure) is installed on the aircraft model 100. One end of the transfer runway unit 200 is a fixed end, and a pull rope (not shown in the figure) is connected between the fixed end and the tension sensor. The transfer runway unit 200 is used to move the aircraft model 100 away from the fixed end. The wind field simulation unit 300 is installed at the fixed end and is used to blow air onto the aircraft model 100.

[0026] In this embodiment, the transport runway unit 200 can automatically move the aircraft model 100, thereby simulating the state of the aircraft moving on the ground. This allows for testing the braking performance of the aircraft at different moving speeds. The wind field simulation unit 300 can create interference conditions by blowing wind onto the aircraft model 100, thereby simulating different wind speeds and wind force conditions. This allows for testing the stability and braking effect of the aircraft under the aforementioned interference conditions. The above simulation conditions can be performed individually or simultaneously, thereby creating various simulation environments with different conditions. Furthermore, during the simulation process, tension data can be collected in real time by a tension sensor, thereby accurately evaluating the braking performance data of the aircraft under different simulation conditions.

[0027] It should be noted that the aircraft model 100 here can be an airplane model with at least three wheels. When the tension sensor on the aircraft model 100 is pulled by the rope, the aircraft model 100 drives its wheels to rotate under the action of the transfer runway unit 200, thereby forming relative movement to simulate the ground movement state of the aircraft. At this time, the aircraft model 100 is in an unbraked state, and the tension sensor monitors the tension in real time. Then the aircraft model 100 performs a braking operation. At this time, the wheels of the aircraft model 100 are braked, and a large sliding friction force is formed between the aircraft model 100 and the transfer runway unit 200. The braking performance of the aircraft model 100 is tested based on the different sliding friction forces formed at different movement speeds.

[0028] As an optional implementation, the aircraft model 100 is also provided with a turbulence simulation unit 400. The turbulence simulation unit 400 includes a swing component 420 and two spoilers 410. The swing component 420 is disposed on the aircraft model 100, and the two spoilers 410 are connected to the swing component 420. The two spoilers 410 swing alternately under the action of the swing component 420 to simulate airflow disturbance conditions.

[0029] In this embodiment, a turbulence simulation unit 400 is also provided on the aircraft model 100. The two spoilers 410 can be driven to swing alternately by the swing component 420, thereby achieving a turbulence effect and simulating the airflow disturbance encountered by the aircraft model 100 in flight to test its stability. Here, the turbulence simulation unit 400 and the wind field simulation unit 300 can be performed separately or simultaneously, thereby simulating complex interference environments. Different interference conditions can be flexibly selected according to test requirements, which improves the simulation accuracy of the braking system of the aircraft model 100 under various complex conditions.

[0030] As an optional implementation, the swing assembly 420 includes a vertical plate 421, two movable blocks 422, two first telescopic members 423, two sliders 424, and two arc-shaped frames 425. The vertical plate 421 is vertically mounted on the aircraft model 100. The two movable blocks 422 are vertically slidably mounted on both sides of the vertical plate 421, and the two movable blocks 422 slide in opposite directions. The two first telescopic members 423 are respectively connected to one side of the corresponding movable block 422. The two sliders 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 slider 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 frames 425 are suspended and connected to one side of the vertical plate 421 through extension rods. The two sliders 424 are respectively slidably mounted on the arc-shaped frames 425.

[0031] In this embodiment, the two moving blocks 422 are made to move vertically simultaneously along the vertical plate 421 in opposite moving directions. When one moving block 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 further drive the sliding blocks 424 to slide along the arc-shaped frames 425 along an arc-shaped track. Meanwhile, under the action of the arc-shaped track, the first telescopic members 423 telescopically adapt to match 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 change correspondingly, so that the spoilers 410 swing along with the change of the inclination angles of the sliding blocks 424. In cooperation with the alternate up-and-down movement of the two moving blocks 422, the alternate swinging of the two spoilers 410 is realized. The structure is compact, the design is ingenious, and the use requirements are satisfied.

[0032] It should be noted that vertical sliding grooves 4211 in sliding fit with the corresponding moving blocks 422 can be respectively provided on both sides of the vertical plate 421, which has a compact and reliable structure; the vertical plate 421 can adopt a "日"-shaped structure to save materials; 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, the sliding rod can telescopically slide in the sleeve, and the other end of the sliding rod is hinged to the sliding block 424.

[0033] As an alternative embodiment, a driving assembly is further provided on the vertical plate 421, and the driving assembly is configured to drive the two moving blocks 422 to slide simultaneously in opposite sliding directions, so as to realize the automatic swinging of the two spoilers 410.

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

[0035] In this embodiment, when it is necessary to drive the spoiler 410 to swing, the drive motor 426 is started to drive the crankshaft 427 to rotate. While the crankshaft 427 rotates, it slides along the first guide groove 4281, which can drive the swing rod 428 to swing around the movable shaft. That is, the two ends of the swing rod 428 swing up and down alternately, so as to drive the limiting shafts 429 on both sides of the swing rod 428 to move up and down alternately under the action of the second guide groove 4282, thereby driving the corresponding moving block 422 to move synchronously. The structure is compact, occupies little space, and meets the design requirements.

[0036] As an optional implementation, a fixing frame 430 is also provided on one side of the upright plate 421, and the swing rod 428 is located between the fixing frame 430 and the upright plate 421. The fixing frame 430 can protect the swing rod 428 and prevent the swing rod 428 from getting tangled with other pipelines when it moves.

[0037] As an optional implementation, the end of the aircraft model 100 furthest from the wind field simulation unit 300 is connected to a thruster 110. The thruster 110 is used to simulate the propulsion of the aircraft model 100. Here, the thruster 110 can be simulated by a wind turbine. The aircraft model 100 is also equipped with a level sensor and a wind force sensor. The level sensor is used to monitor whether the chassis of the aircraft model 100 remains level, and the wind force sensor is used to detect wind force, so that the monitoring data of the aircraft model 100 under various complex conditions can be collected in a comprehensive manner.

[0038] As an optional implementation, the aircraft model 100 is also provided with a controller and a mounting bracket 120 for mounting a tension sensor. The tension sensor, level sensor and wind sensor are all electrically connected to the controller, which is also electrically connected to a display screen 500.

[0039] In this embodiment, different types of tensile sensors can be detachably installed via mounting component 120 to meet different testing requirements. The data collected by the tensile sensor, level sensor, and wind sensor can be processed by the controller and displayed on the display screen 500 for intuitive viewing by the staff.

[0040] As an optional implementation, the transfer runway unit 200 includes a support 210, multiple drive rollers 220, a motor drive assembly 230, and a conveyor belt 240. The multiple drive rollers 220 are movably connected to the support 210, and the drive roller 220 furthest from the fixed end is the drive roller. The motor drive assembly 230 is disposed on the support 210 and is used to drive the drive roller to rotate. The conveyor belt 240 is wound around the multiple drive rollers 220 and is used to move the aircraft model 100.

[0041] In this embodiment, the motor drive assembly 230 can drive the active roller to rotate, thereby driving the conveyor belt 240 and multiple drive rollers 220 to rotate synchronously. Here, the motor drive assembly 230 can provide different speeds, so that the conveyor belt 240 can 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 transmission assembly 230 here includes a motor disposed on one side of the bracket 210. The motor is connected to a drive wheel, and the drive wheel is connected to a driven wheel via a belt drive. The driven wheel is connected to one end of the drive roller. By setting different speeds of the motor, different moving speeds of the conveyor belt 240 can be achieved.

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

[0044] It should be noted that the fan 320 is installed at an adjustable angle on the fixed support 310 (the fan 320 can be rotated and connected to the top of the fixed support 310, and after being adjusted to the corresponding angle, the fan 320 can be fixed manually or by using fasteners), thus simulating different wind directions and providing more simulation test data.

[0045] As an optional implementation, a second telescopic member 600 is provided on the side of the fixed support 310 near the aircraft model 100. The telescopic end of the second telescopic member 600 is connected to a pull ring 700, which is used to connect a pull rope.

[0046] In this embodiment, the pull ring 700 is easy to detachably connect with the pull rope, and the second telescopic component 600 can be a telescopic cylinder, so that the distance between the aircraft model 100 and the wind field simulation unit 300 can be adjusted according to the test requirements, and the operation is flexible.

[0047] In summary, this application can simulate various combinations of conditions according to testing requirements, including: (1) Simultaneously turn on the thruster 110, the wind field simulation unit 300 and the turbulence simulation unit 400 to achieve simultaneous testing of the three interference modes; (2) Only the thruster 110 and the wind field simulation unit 300 are turned on to achieve simultaneous testing of these two interference methods; (3) Only the thruster 110 and the turbulence simulation unit 400 are turned on to achieve simultaneous testing of these two interference methods; (4) Only turn on the wind field simulation unit 300 and the turbulence simulation unit 400 to achieve simultaneous testing of these two interference methods; (5) The thruster 110, wind field simulation unit 300 or turbulence simulation unit 400 are turned on separately to test a single interference mode.

[0048] Therefore, this application can activate various interference simulation conditions individually or in combination, thereby enabling a comprehensive evaluation of the aircraft's braking performance.

[0049] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this 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. 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. 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 respectively slidably fitted onto the arc-shaped frames.

2. The aircraft braking process simulation demonstration device as described in claim 1, 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.

3. The aircraft braking process simulation demonstration device as described in claim 2, 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.

4. The aircraft braking process simulation demonstration device as described in claim 3, 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.

5. A simulation demonstration device for aircraft braking process as described in any one of claims 1-4, 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.

6. The aircraft braking process simulation demonstration device as described in claim 5, 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.

7. 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.

8. 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.

9. The aircraft braking process simulation demonstration device as described in claim 8, 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.

Images