Method for testing wear resistance of airport machine-made sand road panel

Abstract

The invention discloses a method for testing the wear resistance of an airport machine-made sand road panel, and relates to the technical field of airport machine-made sand road panel wear resistance testing. A support frame; an aircraft take-off and landing simulation mechanism; an aircraft simulation device; a test piece; the method comprises a first test mode, a second test mode and a third test mode. According to the invention, the performance of the wear-resistant layer on the surface of the test piece can be tested in multiple modes, including the influence of an aircraft take-off state on wear resistance, the influence of an aircraft landing state on wear resistance and the influence of an aircraft accident state on wear resistance, and the wear resistance of the wear-resistant layer can be fully verified through the tests; and a data reference is provided for the improvement of the pavement slab and the flight safety of an airplane.

Description

Technical Field

[0001] The present invention relates to the technical field of wear resistance testing of machine-made sandway panels at airports, and in particular to a method for testing the wear resistance of machine-made sandway panels at airports. Background Art

[0002] Airport road panels have very high requirements for wear resistance. The reason is that, unlike conventional roads that are only for vehicle traffic, airport road panels not only need to carry a large number of people or goods through vehicles, but also need to withstand the huge impact and pressure caused by aircraft takeoff and landing. Only wear-resistant road panels can ensure that they remain flat and durable under frequent use, reducing wear and deformation.

[0003] The wear resistance test of the airport machine-made sand road panel mainly adopts the existing building materials industry and highway industry standards, both of which use the method of steel wheel abrasion machine-made sand concrete specimens. This method has the following disadvantages:

[0004] 1) Testing on concrete specimens formed in the laboratory differs from the actual pavement forming process used on-site: On-site pavements undergo a roughening process, which is not performed in the laboratory; and a slurry extraction process is performed on-site, which is not performed in the laboratory. This test method involves a 30-turn pre-grinding process, which removes the laitance and some mortar from the specimen surface. This subsequent grinding often involves the removal of coarse aggregate, which has better wear resistance than the mortar layer, resulting in distorted data. The actual wear-resistant layer is only the mortar layer, not the coarse aggregate. Coarse aggregate is the main component of the concrete structure and is responsible for structural performance, not wear resistance. Therefore, the test results of the specimens are not necessarily related to the wear resistance of the actual pavement delivered for use.

[0005] 2) Existing indoor testing methods differ from the actual wear conditions experienced during pavement operation: They employ steel wheels to grind concrete, whereas in reality, tires (including aircraft and vehicle tires) grind concrete. Due to the sheer size of aircraft, their impact on the manufactured sand wear layer is particularly significant. This means that the existing steel wheel grinding method can only qualitatively characterize the wear resistance differences between different concrete compositions, and the data obtained is irrelevant to actual wear.

[0006] In addition, some existing methods for testing the wear resistance of airport pavement are carried out by using a friction tester, which has the following defects:

[0007] 1. Unable to simulate the impact of aircraft landing on the pavement's wear resistance: Since the aircraft has a great impact on the pavement during landing, this impact has a great impact on the pavement's friction performance, but existing methods lack simulation of the aircraft landing process.

[0008] 2. In extreme cases, the aircraft loses control and falls directly from the air and impacts the pavement. The existing methods lack the simulation of such extreme situations and cannot detect the impact of extreme situations on the wear resistance of airport pavements.

[0009] 3. During takeoff, as the lift of the aircraft increases, the friction between the aircraft tires and the road surface gradually decreases. Existing detection methods cannot simulate this process and therefore cannot provide data that is of reference significance.

[0010] In summary, the real wear-resistant layer is only the mortar layer and does not include coarse aggregate. How to test the wear resistance of the wear-resistant layer is an important issue that needs to be solved urgently. Summary of the Invention

[0011] The present invention provides a method for testing the wear resistance of airport machine-made sand pavement panels, aiming to solve the problems 1-3 described in the prior art. The wear resistance of the mortar layer (i.e., the wear-resistant layer) of the machine-made sand is tested to provide data reference for the actual construction and safe use of the airport pavement.

[0012] In order to solve the above problems, the technical solution of the present invention is:

[0013] A method for testing the wear resistance of airport machine-made sandway panels includes a testing device, which includes:

[0014] A base, wherein the upper end of the base is provided with a specimen fixing groove;

[0015] A support frame, the support frame comprising a first support plate and a second support plate provided at left and right ends of an upper surface of the base;

[0016] An aircraft take-off and landing simulation mechanism, wherein the aircraft take-off and landing simulation mechanism is provided between the first support plate and the second support plate;

[0017] An aircraft simulator, the aircraft simulator being connected to an aircraft take-off and landing simulation mechanism, and having a rubber wheel at the bottom thereof for contacting the surface of the test piece;

[0018] The test piece is an airport road panel test piece, and a wear-resistant layer is provided on the surface of the test piece;

[0019] The wear resistance test method adopts the above-mentioned test device to test the wear resistance of the road panel through different test modes.

[0020] Preferably, the base is a rectangular plate structure, and the specimen fixing groove includes a first fixing block provided on the left side, a second fixing block provided on the right side, a third fixing block provided on the front side, and a fourth fixing block provided on the rear side;

[0021] The second fixing block and the third fixing block are both provided with penetrating positioning bolts, and the positioning bolts are respectively screwed to the second fixing block and the third fixing block, and the inner ends of the positioning bolts are provided with pressing plates for pressing the test piece.

[0022] Preferably, the aircraft take-off and landing simulation mechanism includes an aircraft take-off and landing trajectory simulation guide rail, a driving unit for driving the aircraft simulation device to move left and right along the simulation guide rail, and a lifting unit for vertically adjusting the height of the aircraft simulation device.

[0023] Preferably, the simulated guide rail comprises an integrally formed guide rail body, wherein the left side of the guide rail body is provided with an inclined section and the right side is provided with a horizontal section, the upper end of the inclined section is fixedly connected to the first support plate, the lower end is connected to one end of the horizontal section, and the other end of the horizontal section is fixedly connected to the second support plate;

[0024] There are two guide rail bodies, which are symmetrically arranged about the central vertical plane of the first support plate and the second support plate. The connection position of the inclined section and the horizontal section is an arc-shaped transition, and the inclined section and the horizontal section are provided with an integrally connected guide rail groove.

[0025] Preferably, the aircraft simulator comprises a box for loading a counterweight, the front and rear sides of the bottom of the box are respectively provided with rubber wheels, and the front and rear walls of the box are penetrated by a fixed shaft;

[0026] The two ends of the fixed shaft are equipped with guide wheels, which are embedded in the corresponding guide rail grooves and slide in cooperation with the guide rail grooves;

[0027] The portion where the fixed shaft contacts the front and rear walls of the box is provided with a guide groove, a guide slider is vertically slidably connected in the guide groove, the fixed shaft passes through the guide slider and is fixedly connected to the guide slider, and a damping device is further connected between the fixed shaft and the front or rear wall of the box;

[0028] The damping device comprises a viscoelastic damper, the fixed end of the viscoelastic damper is fixedly connected to the outer wall of the box body, and the telescopic end is connected to the fixed shaft through a spring.

[0029] Preferably, the driving unit comprises two linear guide rails provided between the front and rear sides of the inner surfaces of the first support plate and the second support plate, and a movable seat is slidably connected between the two linear guide rails;

[0030] The front and rear ends of the movable seat are respectively slidably connected to the corresponding linear guide rails, and a first lead screw and a second lead screw are respectively provided on the front and rear sides of the opposite surfaces of the first support plate and the second support plate. The first lead screw and the second lead screw are arranged in parallel, and one end of the first lead screw passes through the outer surface of the second support plate and is fixedly connected to the output shaft of the servo motor preset on the outer surface of the second support plate;

[0031] The other end of the first lead screw and the same side end of the second lead screw respectively pass through the first support plate and are respectively provided with a driving sprocket and a driven sprocket at the end, the driving sprocket and the driven sprocket are connected by a chain transmission, the first lead screw and the second lead screw respectively pass through the movable base and are screwed to the movable base, and the movable base moves left and right along the linear guide rail under the drive of the servo motor;

[0032] The front and rear sides of the top of the box are respectively provided with connecting plates, and the left and right sides of the top of the connecting plate are respectively provided with guide rods in the vertical direction. The movable seat is provided with 4 guide holes arranged in a rectangular shape, and the guide rods pass through the corresponding guide holes and are slidably connected to the guide holes. The top ends of the 4 guide rods are commonly fixedly connected to a fixed plate.

[0033] Preferably, the lifting unit includes an electric cylinder vertically arranged in the middle of the top of the movable seat, the fixed end of the electric cylinder is fixedly connected to the movable seat, and the telescopic end is in contact with the center of the bottom end of the fixed plate through a pressure sensor.

[0034] Preferably, two sleeves with internal threads are arranged side by side in the front-to-back direction in the movable seat, and the first screw and the second screw are respectively threadedly connected to the corresponding sleeves;

[0035] The outer sliding sleeve of the sleeve is connected to a guide sleeve, and the guide sleeve is fixedly connected to a through hole preset on the movable seat and passing through the left and right ends of the movable seat. The upper and lower ends of the movable seat are respectively provided with electric push rods in the vertical direction. The fixed end of the electric push rod is fixedly connected to the movable seat, and the telescopic end extends into the movable seat and is fixedly connected to the positioning rod.

[0036] The positioning rod passes through a preset sliding hole on the outer wall of the guide sleeve and is plugged into the positioning hole on the outer wall of the sleeve. The locking and unlocking of the sleeve and the guide sleeve are achieved by the extension and retraction of the electric push rod. The cross-sections of the outer wall of the sleeve and the inner hole of the guide sleeve are both rectangular.

[0037] Preferably, it further includes a control system, which is electrically connected to the power supply and the pressure sensor and is configured to control the actions of the servo motor, the electric cylinder, and the electric push rod.

[0038] Preferably, the different test modes in the wear resistance test method include the following:

[0039] Test mode 1: Add a counterweight to the box, and adjust the height and position of the box by extending and retracting the electric cylinder and rotating the servo motor, so that the box hovers at the starting position at the high end of the tilt section;

[0040] The servo motor drives the moving seat to move the box to the right. At the same time, under the control of the control system, the electric cylinder gradually shortens and the box enters the horizontal section. When the rubber wheel contacts the surface of the test piece, the pressure sensor is separated from the fixed plate.

[0041] Then, the electric cylinder stops moving, and the servo motor drives the box to move to the right a set distance and stops at the end position, simulating the landing of an airplane through this process.

[0042] Then, the box is extended and lifted by the electric cylinder. When the rubber wheel does not contact the surface of the specimen, the box is moved back to the starting position by the rotation of the servo motor. The process of simulating the landing of an airplane is repeated until the wear-resistant layer is worn through. The number of simulations is recorded. The wear resistance of the wear-resistant layer on the surface of different specimens is evaluated based on the number of simulations. The wear resistance represents the effect of a simple airplane landing on the wear resistance of the wear-resistant layer.

[0043] Simulation mode 2: The box is at the end position, the rubber wheel is in contact with the specimen surface, and driven by the servo motor, the box gradually moves toward the starting position. During this process, the pressure sensor contacts the fixed plate. The control system gradually increases the thrust of the electric cylinder based on the pressure sensor data to simulate the process of the rubber wheel reducing the pressure on the ground during aircraft takeoff. When the box moves to the inclined section, the rubber wheel separates from the specimen surface, simulating an aircraft takeoff, until the box returns to the starting position.

[0044] Then, while keeping the rubber wheel separated from the specimen surface, the servo motor drives the box to the end position again. By adjusting the electric cylinder to retract, the pressure sensor data is set to zero. At this time, due to the gravity of the aircraft simulator, the rubber wheel contacts the wear-resistant layer, and the aircraft take-off process is simulated again; until the wear-resistant layer on the specimen surface is worn through, the number of simulated aircraft take-offs is recorded. The wear resistance performance of the wear-resistant layer on the specimen surface is evaluated based on the number of simulated times. The wear resistance performance represents the impact of a simple aircraft take-off on the wear resistance of the wear-resistant layer.

[0045] Test mode three: When the box is moved to the starting position, the control system controls the servo motor to move the box to the right at a certain acceleration. When the box reaches the bottom of the inclined section, the electric push rod retracts, releasing the lock of the sleeve and the guide sleeve. Under the action of inertia, the sleeve and the guide sleeve are separated, and the box moves to the horizontal section, and the rubber wheel impacts the wear-resistant layer on the surface of the test piece. During this process, the electric cylinder gradually shortens as in test mode one, and ensures that the rubber wheel contacts the wear-resistant layer when the box enters the horizontal section and the pressure sensor is separated from the fixed plate.

[0046] Repeat the above test method until the wear-resistant layer is worn through, record the simulation number three, and evaluate the wear resistance performance three of the wear-resistant layer based on the simulation number three. The wear resistance performance three represents the impact of the wear-resistant layer on the wear resistance performance of the wear-resistant layer when an aircraft crashes under extreme circumstances.

[0047] The present invention has the following beneficial effects:

[0048] The present invention can realize multiple mode tests on the performance of the wear-resistant layer (machine-made sand mortar layer) on the surface of the test piece, including the influence of the aircraft take-off state on the wear resistance, the influence of the aircraft landing state on the wear resistance, and the influence of the aircraft crash state on the wear resistance. Through the above tests, the wear resistance of the wear-resistant layer can be fully verified, providing data reference for the improvement of the pavement panel and the flight safety of the aircraft; the detection method of the present invention is closer to reality and has high practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] Figure 1 , a front view structural diagram of the present invention;

[0050] Figure 2 , a schematic diagram of the top view of the structure of the present invention in the direction AA;

[0051] Figure 3 , a schematic diagram of the top view of the structure of the present invention in the direction BB;

[0052] Figure 4 , a schematic diagram of the top view of the test piece fixing groove of the present invention;

[0053] Figure 5 , a schematic front view of the structure of the aircraft simulator of the present invention;

[0054] Figure 6 , a side structural schematic diagram of the aircraft simulator of the present invention (without the damping device);

[0055] Figure 7 , a schematic cross-sectional structural diagram of the movable seat of the present invention.

[0056] 1. Base; 2. First support plate; 3. Second support plate; 4. Linear guide; 5. Box; 6. Guide rod; 7. Fixed plate; 8. Electric cylinder; 9. Specimen fixing groove; 91. First fixed block; 92. Second fixed block; 93. Third fixed block; 10. Positioning bolt; 11. Press plate; 12. Simulated guide rail; 13. Guide rail body; 131. Inclined section; 132. Horizontal section; 14. Fixed shaft; 15. Guide wheel; 16. Rubber wheel; 17. Servo motor; 18. Viscoelastic damper; 19. First lead screw; 20. Second lead screw; 21. Driving sprocket; 22. Moving seat; 23. Guide sleeve; 24. Sleeve; 25. Electric push rod; 26. Connecting plate; 27. Specimen; 28. Spring; 29. Guide groove; 30. Guide slider; 31. Positioning rod. DETAILED DESCRIPTION

[0057] The following describes in detail the implementation methods of the present invention in a step-by-step manner. This description is only a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0058] In the description of the present invention, it should be noted that the terms "up", "down", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings. They are only for describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, and a specific orientation structure and operation. Therefore, they cannot be understood as limiting the present invention.

[0059] Example 1

[0060] The present invention provides a method for testing the wear resistance of an airport machine-made sandway panel, comprising a testing device, which is a testing device for testing the wear resistance of an airport machine-made sandway panel, such as Figure 1-7 As shown, including:

[0061] A base 1, wherein a specimen fixing groove 9 is provided at the upper end of the base 1;

[0062] A support frame, the support frame includes a first support plate 2 and a second support plate 3 provided on the left and right ends of the upper surface of the base 1;

[0063] An aircraft take-off and landing simulation mechanism, which is provided between the first support plate 2 and the second support plate 3;

[0064] An aircraft simulator, the aircraft simulator being connected to an aircraft take-off and landing simulation mechanism, and having a rubber wheel 16 at the bottom thereof for contacting the surface of a test piece 27;

[0065] Specimen 27 is an airport road panel specimen, and the specimen surface is provided with a wear-resistant layer (such as Figure 1 shown, not marked in the figure).

[0066] The wear resistance test method adopts the above-mentioned test device to test the wear resistance of the road panel through different test modes.

[0067] Example 2

[0068] like Figure 2-4As shown, in the test device, the base 1 is a rectangular plate structure, and the specimen fixing groove 9 includes a first fixing block 91 provided on the left, a second fixing block 92 provided on the right, a third fixing block 93 provided on the front side, and a fourth fixing block (not marked in the figure) provided on the rear side. The second fixing block 92 and the third fixing block 93 are both provided with a penetrating positioning bolt 10, and the positioning bolt 10 is screwed to the second fixing block 92 and the third fixing block 93 respectively. The inner end of the positioning bolt 10 is provided with a pressure plate 11 for pressing the specimen 27.

[0069] In this embodiment, the specimen is placed in the specimen fixing groove, and then the positioning bolts are tightened to compress and secure the specimen in the groove. This arrangement is intended to reduce the difficulty of specimen installation. The specimen can be made of prefabricated airport runway panel material, cut into cubical specimens of predetermined dimensions.

[0070] Example 3

[0071] like Figure 1-4 As shown, the aircraft takeoff and landing simulation mechanism in the test device includes a guide rail 12 for simulating the aircraft's takeoff and landing trajectory, a drive unit for driving the aircraft simulator to move left and right along the simulation rail 12, and a lifting unit for vertically adjusting the height of the aircraft simulator. The drive unit is used to drive the aircraft simulator to simulate the deceleration state during landing, the acceleration state during takeoff, and the gradual deceleration state during taxiing. The lifting unit ensures that the rubber wheel contacts the wear-resistant layer on the test piece's surface at the set position and assists in switching the aircraft simulator between different states (takeoff, landing, aircraft crash, taxiing).

[0072] Example 4

[0073] like Figure 1-4 As shown, the simulated guide rail 12 in the test device includes an integrally formed guide rail body 13, wherein the left side of the guide rail body 13 is provided with an inclined section 131 and the right side is provided with a horizontal section 132, the high end of the inclined section 131 is fixedly connected to the first support plate 2, and the low end is connected to one end of the horizontal section 132, and the other end of the horizontal section 132 is fixedly connected to the second support plate 3, and there are two guide rail bodies 13, which are symmetrically arranged with respect to the middle vertical plane of the first support plate 2 and the second support plate 3 (i.e., arranged front to back), the connection position of the inclined section 131 and the horizontal section 132 is arc-shaped, and the inclined section 131 and the horizontal section 132 are provided with an integrally connected guide rail groove (such as Figure 1 shown).

[0074] Example 5

[0075] like Figure 1-7As shown, the aircraft simulation device includes a box body 5 for loading a counterweight, and rubber wheels 16 are respectively provided on the front and rear sides of the bottom of the box body 5. A fixed shaft 14 passes through the front and rear walls of the box body 5, and guide wheels 15 are installed at the two ends of the fixed shaft 14. The guide wheels 15 are embedded in the corresponding guide rail grooves and slide in cooperation with the guide rail grooves; the parts where the fixed shaft 14 contacts the front and rear walls of the box body 5 are provided with guide grooves 29.

[0076] A guide slider 30 is vertically slidably connected in the guide groove 29, and the fixed shaft 14 passes through the guide slider 30 and is fixedly connected to the guide slider 30. A damping device is also connected between the fixed shaft 14 and the front or rear wall of the box body 5. The damping device includes a viscoelastic damper 18. The fixed end of the viscoelastic damper 18 is fixedly connected to the outer wall of the box body 5, and the telescopic end is connected to the fixed shaft 14 through a spring 28.

[0077] In this embodiment, when the box moves to the horizontal section, the wear-resistant layer on the specimen's surface supports the weight of the box (and its internal counterweight) via rubber wheels, simulating the pressure exerted by an aircraft on the wear-resistant layer. During this process, the guide slider slides up and down in the guide groove, and the damping device reduces vibration, simulating the vibration reduction measures during an aircraft landing.

[0078] It should be noted that a partition plate may be provided inside the box above the guide groove to support and accommodate the counterweight.

[0079] Example 6

[0080] like Figure 1-4 As shown, the driving unit includes two linear guides 4 arranged between the front and rear sides of the inner surfaces of the first support plate 2 and the second support plate 3, and a moving seat 22 is slidably connected between the two linear guides 4. The front and rear ends of the moving seat 22 are slidably connected to the corresponding linear guides 4 respectively. A first lead screw 19 and a second lead screw 20 are also provided on the front and rear sides of the opposite surfaces of the first support plate 2 and the second support plate 3 respectively. The first lead screw 19 and the second lead screw 20 are arranged in parallel. One end of the first lead screw 19 passes through the outer surface of the second support plate 3 and is fixedly connected to the output shaft of the servo motor 17 preset on the outer surface of the second support plate 3; the other end of the first lead screw 19 and the same side end of the second lead screw 20 respectively pass through the first support plate 2 and are respectively provided with a driving sprocket 21 and a driven sprocket (not marked in the figure) at the end.

[0081] The driving sprocket 21 and the driven sprocket are connected by a chain (not marked in the figure). The first lead screw 19 and the second lead screw 20 respectively pass through the movable seat 22 and are screwed to the movable seat 22. Driven by the servo motor 17, the movable seat 22 moves left and right along the linear guide rail 4. The front and rear sides of the top of the box body 5 are respectively provided with connecting plates 26. The left and right sides of the top of the connecting plate 26 are respectively provided with guide rods 6 in the vertical direction. There are 4 guide holes (not marked in the figure) arranged in a rectangular shape on the movable seat 22. The guide rods 6 pass through the corresponding guide holes and are slidably connected to the guide holes. The top ends of the 4 guide rods 6 are commonly fixedly connected to a fixed plate 7.

[0082] Example 7

[0083] like Figure 1 、 2 As shown, the lifting unit includes an electric cylinder 8 vertically arranged in the middle of the top of the moving seat 22. The fixed end of the electric cylinder 8 is fixedly connected to the moving seat 22, and the telescopic end is in contact with the center of the bottom end of the fixed plate through a pressure sensor (not shown in the figure).

[0084] In this embodiment, when the electric cylinder is extended, it can contact the bottom end of the fixed plate through the pressure sensor, thereby lifting the fixed plate and driving the box body to rise, thereby adjusting the height of the rubber wheel. When it reaches a certain level, the rubber wheel can be separated from the wear-resistant layer. Before separating from the wear-resistant layer, the pressure applied by the rubber wheel to the wear-resistant layer is adjusted; when the box body enters the horizontal section, the electric cylinder is shortened to the point where the pressure sensor is separated from the fixed plate. At this time, the weight of the aircraft simulation device can be transferred to the wear-resistant layer through the rubber wheel.

[0085] Example 8

[0086] like Figure 2 、 7 As shown, two sleeves 24 with internal threads are arranged side by side in the front-to-back direction inside the movable seat 22, and the first screw 19 and the second screw 20 are respectively screwed with the corresponding sleeves 24; the sleeve 24 is slidably sleeved with a guide sleeve 23, and the guide sleeve 23 is fixedly connected to a through hole (not shown in the figure) preset on the movable seat 22 and passing through the left and right ends of the movable seat, and the upper and lower ends of the movable seat 22 are respectively provided with an electric push rod 25 in the vertical direction.

[0087] The fixed end of the electric push rod 25 is fixedly connected to the moving seat 22, and the telescopic end extends into the moving seat 22 and is fixedly connected to the positioning rod 31. The positioning rod 32 passes through a preset sliding hole (not marked in the figure) on the outer wall of the guide sleeve 23 and is plugged into a positioning hole (not marked in the figure) on the outer wall of the sleeve 24. The locking and unlocking of the sleeve 24 and the guide sleeve 23 are achieved by the telescopic movement of the electric push rod 25. The cross-sections of the outer wall of the sleeve 24 and the inner hole of the guide sleeve 23 are both rectangular.

[0088] This design facilitates the relative positioning of the sliding hole and the positioning hole. After the sleeve is released from the guide sleeve, reinserting it into the guide sleeve requires only the sleeve to be straightened (i.e., secured so that it does not rotate with the lead screw). With the first or second lead screw rotating, the sleeve is inserted into the guide sleeve. The electric push rod then drives the positioning rod to lock the sleeve and guide sleeve. In this embodiment, unlocking the guide sleeve and sleeve can simulate an aircraft crash.

[0089] Example 9

[0090] Based on the above embodiments, this embodiment discloses: further comprising a control system, wherein the control system is electrically connected to the power supply and the pressure sensor and is configured to control the actions of the servo motor, the electric cylinder, and the electric push rod.

[0091] Example 10

[0092] Based on the above embodiments, this embodiment discloses a wear resistance test method using the above test device to test the wear resistance of the road panel through three test modes, such as Figure 1-7 shown.

[0093] Test mode 1:

[0094] Add counterweights inside the box, and adjust the height and position of the box by extending and retracting the electric cylinder in coordination with the rotation of the servo motor (that is, when the electric cylinder extends, the box can be lifted up by the pressure sensor, and vice versa), so that the box hovers at the starting position at the high end of the tilting section (this can be set to stop as needed).

[0095] The servo motor drives the moving seat to move the box to the right. At the same time, under the control of the control system, the electric cylinder gradually shortens and makes the rubber wheel contact the surface of the specimen when the box enters the horizontal section, and the pressure sensor is separated from the fixed plate. Then, the electric cylinder stops and the servo motor drives the box to move to the right (because the moving seat pushes the guide rod to drive the box to move) and stops at the end position after the set distance. This process simulates the landing of an aircraft.

[0096] Then, the box is extended and lifted by the electric cylinder, and the box is moved back to the starting position by the rotation of the servo motor when the rubber wheel is not in contact with the surface of the specimen. The process of aircraft landing is repeatedly simulated until the wear-resistant layer is worn through. The number of simulations is recorded. The wear resistance performance of the wear-resistant layer on the surface of different specimens is evaluated based on the number of simulations. The wear resistance performance represents the impact of a simple aircraft landing on the wear resistance of the wear-resistant layer.

[0097] Simulation mode 2:

[0098] The box is at the end position, and the rubber wheel is in contact with the surface of the specimen. Driven by the servo motor, the box gradually moves toward the starting position. During this process, the pressure sensor is in contact with the fixed plate. The control system gradually increases the thrust of the electric cylinder based on the data from the pressure sensor to simulate the process of reducing the pressure of the rubber wheel on the ground during aircraft takeoff.

[0099] When the box moves to the inclined section, the rubber wheel detaches from the surface of the specimen to simulate the aircraft taking off until the box returns to the starting position; then, while keeping the rubber wheel detached from the surface of the specimen, the servo motor drives the box to the end position again, and by adjusting the electric cylinder to contract, the data of the pressure sensor is made zero. At this time, due to the gravity of the aircraft simulation device, the rubber wheel contacts the wear-resistant layer, and the aircraft take-off process is simulated again; until the wear-resistant layer on the surface of the specimen is worn through, the number of simulations of the simulated aircraft take-off is recorded. The wear resistance performance of the wear-resistant layer on the surface of the specimen is evaluated based on the number of simulations. The wear resistance performance represents the influence of a simple aircraft take-off on the wear resistance of the wear-resistant layer.

[0100] Test mode three:

[0101] When the box is moved to the starting position, the control system controls the servo motor to move the box to the right with a certain acceleration. When the box reaches the bottom of the inclined section, the electric push rod contracts, releasing the lock of the sleeve and the guide sleeve. Under the action of inertia, the sleeve and the guide sleeve are disengaged (at this time, due to the limited sliding fit between the moving seat and the linear guide rails on both sides, the first lead screw or the second lead screw will not contact the inner wall of the guide sleeve), the box moves to the horizontal section, and the rubber wheel impacts the wear-resistant layer on the surface of the specimen.

[0102] During this process, the electric cylinder is gradually shortened as in test mode 1, and it is ensured that the rubber wheel contacts the wear-resistant layer and the pressure sensor is separated from the fixed plate when the box enters the horizontal section; the above test method is repeated until the wear-resistant layer is worn through, and the simulation number three is recorded. The wear resistance performance three of the wear-resistant layer is evaluated based on the number of simulation times three. The wear resistance performance three represents the impact of the wear-resistant layer on the wear resistance performance of the wear-resistant layer in extreme cases when an aircraft crashes.

[0103] In the above methods, the wear-resistant layer is worn through when the machine-made sand mortar layer is worn through and the coarse aggregate is exposed. Of course, if the airport pavement is formed with a wear-resistant layer using other processes, the equipment and method of the present invention are also applicable.

Claims

1. A method for testing the wear resistance of airport machine-made sandway panels, characterized in that: Including test equipment, the test equipment includes: A base, wherein the upper end of the base is provided with a specimen fixing groove; A support frame, the support frame comprising a first support plate and a second support plate provided at left and right ends of an upper surface of the base; An aircraft take-off and landing simulation mechanism, wherein the aircraft take-off and landing simulation mechanism is provided between the first support plate and the second support plate; An aircraft simulator, the aircraft simulator being connected to an aircraft take-off and landing simulation mechanism, and having a rubber wheel at the bottom thereof for contacting the surface of the test piece; The test piece is an airport road panel test piece, and a wear-resistant layer is provided on the surface of the test piece; The wear resistance test method adopts the above-mentioned test device to test the wear resistance of the road panel through different test modes.

2. The method for testing the wear resistance of airport machine-made sandway panels according to claim 1, wherein: The base is a rectangular plate structure, and the specimen fixing groove includes a first fixing block provided on the left side, a second fixing block provided on the right side, a third fixing block provided on the front side, and a fourth fixing block provided on the rear side; The second fixing block and the third fixing block are both provided with penetrating positioning bolts, and the positioning bolts are respectively screwed to the second fixing block and the third fixing block, and the inner ends of the positioning bolts are provided with pressing plates for pressing the test piece.

3. A method for testing the wear resistance of airport machine-made sandway panels according to claim 2, characterized in that: The aircraft take-off and landing simulation mechanism includes an aircraft take-off and landing trajectory simulation guide rail, a driving unit for driving the aircraft simulation device to move left and right along the simulation guide rail, and a lifting unit for vertically adjusting the height of the aircraft simulation device.

4. A method for testing the wear resistance of airport machine-made sandway panels according to claim 3, characterized in that: The simulated guide rail includes an integrally formed guide rail body, wherein the left side of the guide rail body is provided with an inclined section and the right side is provided with a horizontal section, the upper end of the inclined section is fixedly connected to the first support plate, the lower end is connected to one end of the horizontal section, and the other end of the horizontal section is fixedly connected to the second support plate; There are two guide rail bodies, which are symmetrically arranged about the central vertical plane of the first support plate and the second support plate. The connection position of the inclined section and the horizontal section is an arc-shaped transition, and the inclined section and the horizontal section are provided with an integrally connected guide rail groove.

5. The method for testing the wear resistance of airport machine-made sandway panels according to claim 4, wherein: The aircraft simulator comprises a box for loading a counterweight, with rubber wheels provided on the front and rear sides of the bottom of the box, and a fixed shaft passing through the front and rear walls of the box; The two ends of the fixed shaft are equipped with guide wheels, which are embedded in the corresponding guide rail grooves and slide in cooperation with the guide rail grooves; The portion where the fixed shaft contacts the front and rear walls of the box is provided with a guide groove, a guide slider is vertically slidably connected in the guide groove, the fixed shaft passes through the guide slider and is fixedly connected to the guide slider, and a damping device is further connected between the fixed shaft and the front or rear wall of the box; The damping device comprises a viscoelastic damper, the fixed end of the viscoelastic damper is fixedly connected to the outer wall of the box body, and the telescopic end is connected to the fixed shaft through a spring.

6. A method for testing the wear resistance of airport machine-made sandway panels according to claim 5, characterized in that: The driving unit includes two linear guide rails provided between the front and rear sides of the inner surfaces of the first support plate and the second support plate, and a moving seat is slidably connected between the two linear guide rails; The front and rear ends of the movable seat are respectively slidably connected to the corresponding linear guide rails, and a first lead screw and a second lead screw are respectively provided on the front and rear sides of the opposite surfaces of the first support plate and the second support plate. The first lead screw and the second lead screw are arranged in parallel, and one end of the first lead screw passes through the outer surface of the second support plate and is fixedly connected to the output shaft of the servo motor preset on the outer surface of the second support plate; The other end of the first lead screw and the same side end of the second lead screw respectively pass through the first support plate and are respectively provided with a driving sprocket and a driven sprocket at the end, the driving sprocket and the driven sprocket are connected by a chain transmission, the first lead screw and the second lead screw respectively pass through the movable base and are screwed to the movable base, and the movable base moves left and right along the linear guide rail under the drive of the servo motor; The front and rear sides of the top of the box are respectively provided with connecting plates, and the left and right sides of the top of the connecting plate are respectively provided with guide rods in the vertical direction. The movable seat is provided with 4 guide holes arranged in a rectangular shape, and the guide rods pass through the corresponding guide holes and are slidably connected to the guide holes. The top ends of the 4 guide rods are commonly fixedly connected to a fixed plate.

7. A method for testing the wear resistance of airport machine-made sandway panels according to claim 6, characterized in that: The lifting unit includes an electric cylinder vertically arranged in the middle of the top of the moving seat. The fixed end of the electric cylinder is fixedly connected to the moving seat, and the telescopic end is in contact with the center of the bottom end of the fixed plate through a pressure sensor.

8. A method for testing the wear resistance of airport machine-made sandway panels according to claim 7, characterized in that: Two sleeves with internal threads are arranged side by side in the front-to-back direction in the movable seat, and the first screw and the second screw are respectively threadedly connected to the corresponding sleeves; The outer sliding sleeve of the sleeve is connected to a guide sleeve, and the guide sleeve is fixedly connected to a through hole preset on the movable seat and passing through the left and right ends of the movable seat. The upper and lower ends of the movable seat are respectively provided with electric push rods in the vertical direction. The fixed end of the electric push rod is fixedly connected to the movable seat, and the telescopic end extends into the movable seat and is fixedly connected to the positioning rod. The positioning rod passes through a preset sliding hole on the outer wall of the guide sleeve and is plugged into the positioning hole on the outer wall of the sleeve. The locking and unlocking of the sleeve and the guide sleeve are achieved by the extension and retraction of the electric push rod. The cross-sections of the outer wall of the sleeve and the inner hole of the guide sleeve are both rectangular.

9. A method for testing the wear resistance of airport machine-made sandway panels according to claim 8, characterized in that: It also includes a control system, which is electrically connected to the power supply and the pressure sensor and is configured to control the actions of the servo motor, the electric cylinder, and the electric push rod.

10. The method for testing the wear resistance of airport machine-made sandway panels according to claim 9, wherein: The different test modes in the wear resistance test method include the following: Test mode 1: Add a counterweight to the box, and adjust the height and position of the box by extending and retracting the electric cylinder and rotating the servo motor, so that the box hovers at the starting position at the high end of the tilt section; The servo motor drives the moving seat to move the box to the right. At the same time, under the control of the control system, the electric cylinder gradually shortens and the box enters the horizontal section. When the rubber wheel contacts the surface of the test piece, the pressure sensor is separated from the fixed plate. Then, the electric cylinder stops moving, and the servo motor drives the box to move to the right a set distance and stops at the end position, simulating the landing of an airplane through this process. Then, the box is extended and lifted by the electric cylinder. When the rubber wheel does not contact the surface of the specimen, the box is moved back to the starting position by the rotation of the servo motor. The process of simulating the landing of an airplane is repeated until the wear-resistant layer is worn through. The number of simulations is recorded. The wear resistance of the wear-resistant layer on the surface of different specimens is evaluated based on the number of simulations. The wear resistance represents the effect of a simple airplane landing on the wear resistance of the wear-resistant layer. Simulation mode 2: The box is at the end position, the rubber wheel is in contact with the specimen surface, and driven by the servo motor, the box gradually moves toward the starting position. During this process, the pressure sensor contacts the fixed plate. The control system gradually increases the thrust of the electric cylinder based on the pressure sensor data to simulate the process of the rubber wheel reducing the pressure on the ground during aircraft takeoff. When the box moves to the inclined section, the rubber wheel separates from the specimen surface, simulating an aircraft takeoff, until the box returns to the starting position. Then, while keeping the rubber wheel separated from the specimen surface, the servo motor drives the box to the end position again. By adjusting the electric cylinder to retract, the pressure sensor data is set to zero. At this time, due to the gravity of the aircraft simulator, the rubber wheel contacts the wear-resistant layer, and the aircraft take-off process is simulated again; until the wear-resistant layer on the specimen surface is worn through, the number of simulated aircraft take-offs is recorded. The wear resistance performance of the wear-resistant layer on the specimen surface is evaluated based on the number of simulated times. The wear resistance performance represents the impact of a simple aircraft take-off on the wear resistance of the wear-resistant layer. Test mode three: When the box is moved to the starting position, the control system controls the servo motor to move the box to the right at a certain acceleration. When the box reaches the bottom of the inclined section, the electric push rod retracts, releasing the lock of the sleeve and the guide sleeve. Under the action of inertia, the sleeve and the guide sleeve are separated, and the box moves to the horizontal section, and the rubber wheel impacts the wear-resistant layer on the surface of the test piece. During this process, the electric cylinder gradually shortens as in test mode one, and ensures that the rubber wheel contacts the wear-resistant layer when the box enters the horizontal section and the pressure sensor is separated from the fixed plate. Repeat the above test method until the wear-resistant layer is worn through, record the simulation number three, and evaluate the wear resistance performance three of the wear-resistant layer based on the simulation number three. The wear resistance performance three represents the impact of the wear-resistant layer on the wear resistance performance of the wear-resistant layer when an aircraft crashes under extreme circumstances.

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