An apparatus and method for testing the damping coefficient of aircraft tires

Abstract

This invention discloses a testing device and method for testing the damping coefficient of aircraft tires, belonging to the field of aircraft tire testing technology. It simulates the actual load and vibration conditions of aircraft tires to obtain the true damping coefficient. The device includes a test bench, a test piece, a force measuring platform, a flange, a load-bearing frame, a load-bearing wall, a vertical force loading mechanism, and a damping coefficient testing system. The load-bearing wall is fixedly installed on the test bench, and a flange for fixing the test piece is also fixedly installed on the load-bearing wall. The force measuring platform is horizontally placed beside the load-bearing wall and below the test piece. Vertical force and triaxial excitation are applied to the force measuring platform through the vertical force loading mechanism and the damping coefficient testing system, respectively. This invention concentrates the measurement of the damping coefficient of aircraft tires in different directions on the same testing equipment, realizing the completion of aircraft tire damping coefficient testing in the laboratory.

Description

Technical Field

[0001] This invention relates to a device and method for testing the damping coefficient of aircraft tires, belonging to the field of aircraft tire testing technology. Background Technology

[0002] As one of the main components of an aircraft, aircraft tires need to withstand high speeds, high loads, and high internal pressures, playing a crucial role in the safe takeoff, landing, and taxiing of the aircraft, and operating under extremely demanding conditions. During landing, the tires bear the entire load of the aircraft and high-speed impact loads. An aircraft tire is a highly elastic body composed of materials such as rubber and nylon cords, requiring good deformation capacity to effectively absorb these impact kinetic energies.

[0003] The damping characteristics of aircraft tires can effectively absorb and disperse mechanical vibration and impact energy, reducing vibration transmission and providing excellent vibration reduction and isolation effects. This reduces vibrations generated by mechanical parts during flight and during landing. Currently, research on the damping coefficient of aircraft tires is limited. Most studies on aircraft tire damping employ analytical methods, typically using rigid ring models. However, these calculations cannot be directly correlated with the actual tire structure, and experimental comparative analysis of the aircraft tire damping coefficient is lacking. Therefore, research on the damping coefficient of aircraft tires is crucial. Summary of the Invention

[0004] To address the above problems, this invention proposes an aircraft tire damping coefficient testing device and method to simulate the actual load and vibration conditions of aircraft tires and obtain the true damping coefficient of aircraft tires.

[0005] The technical solution of the present invention includes a test bench 3, a test piece, a force measuring platform 8, a flange 15, a load-bearing frame 2, a load-bearing wall 10, a vertical force loading mechanism, and a damping coefficient testing system.

[0006] The load-bearing wall 10 is fixedly installed on the test bench 3, and the load-bearing wall 10 is also fixedly installed with a flange 15 for fixing the test piece;

[0007] The force measuring platform 8 is horizontally positioned next to the load-bearing wall 10 and below the test specimen. Vertical force and triaxial excitation are applied to the force measuring platform 8 by the vertical force loading mechanism and the damping coefficient testing system, respectively.

[0008] Specifically:

[0009] It also includes a load-bearing frame 2, which is fixedly installed on the test bench 3;

[0010] The vertical force loading mechanism is installed between the top of the load-bearing frame 2 and the force measuring platform 8, and includes a vertical power source that drives the force measuring platform 8 to rise and fall linearly.

[0011] The damping coefficient testing system includes three exciters mounted on the test bench 3 and a triaxial acceleration sensor placed on the force measuring platform 8 via a magnetic base. The three exciters are respectively arranged in the longitudinal direction perpendicular to the axis of the test piece and in the lateral direction parallel to the axis of the test piece. The three exciters are a torsional exciter 12, a lateral exciter 13, and a longitudinal exciter 14. The torsional exciter 12 acts at the longitudinal edge of the force measuring platform 8, the lateral exciter 13 acts at the lateral center of the force measuring platform 8, and the longitudinal exciter 14 acts at the longitudinal center of the force measuring platform 8.

[0012] Regarding the vertical power source:

[0013] The vertical force loading mechanism includes several uniformly arranged vertical power sources, each of which includes a servo actuator 1, a boom 7, a vertical force sensor 6, and a lifting ring 9.

[0014] The housing of the servo actuator 1 is fixedly installed on the top of the load-bearing frame 2. The output rod of the servo actuator 1 is connected to the vertical force sensor 6 via a Y-type connector 5. The top of the boom 7 is fixedly connected to the vertical force sensor 6, and the bottom of the boom 7 is fixedly connected to the force measuring platform 8 via another Y-type connector 5.

[0015] Furthermore, the output rod of the vertical power source located on one side of the test piece maintains synchronous movement through the connecting lug 4, which is fixedly connected to the output rod of the vertical power source.

[0016] Regarding the damping coefficient testing system:

[0017] The housings of the torsional vibrator 12, the lateral vibrator 13, and the longitudinal vibrator 14 are all hinged to the test bench 3 via a bracket, and the output ends of the torsional vibrator 12, the lateral vibrator 13, and the longitudinal vibrator 14 are all connected to the force measuring platform 8.

[0018] The experimental method in this case includes the following steps:

[0019] Step 1: Measure the tire pressure of the aircraft tires to ensure that the tire pressure meets the test requirements;

[0020] Step 2: Install the test device according to the test requirements, fix the aircraft tire, ensure that the force measuring platform is horizontal and corresponds to the center of the aircraft tire, and keep the vertical force applied by different servo actuators the same.

[0021] Step 3: Activate the servo actuator to raise the force measuring platform and bring it into contact with the aircraft tire;

[0022] Step 4: Place the accelerometers at the measurement points as required by the test, ensuring that the accelerometers are oriented in the same direction;

[0023] Step 5: Start the data acquisition and analysis system, clear the cache, and start data acquisition;

[0024] Step Six: Continue to raise the force measuring platform until the vertical force on the aircraft tire reaches the test load.

[0025] Step 7: Keeping the vertical force constant, connect the vibrator to the force measuring platform, ensuring the vibrator is horizontal, and apply lateral excitation, longitudinal excitation, and torsional excitation to the force measuring platform respectively;

[0026] Step 8: During the application of lateral, longitudinal, and torsional excitation, a sinusoidal frequency sweep is used to cause the force measuring platform and the aircraft tire to vibrate.

[0027] Step 9: Observe the data from the data acquisition system. When the aircraft tire resonates with the force measurement platform, the frequency sweep ends and the data acquisition system is stopped.

[0028] Step 10: Turn off the vibrator and disconnect the vibrator from the force measuring platform;

[0029] Step 11: Lower the force measuring platform to release the vertical load until the force measuring platform is no longer in contact with the aircraft tire;

[0030] Step 12: After the experiment is completed, the data is processed and analyzed through the data acquisition system to obtain the natural frequency and damping ratio of the aircraft tire;

[0031] Step 13: Substitute the natural frequency and damping ratio obtained from the experiment into formula (1) to calculate the damping coefficient of the aircraft tire.

[0032]

[0033] Where: f is the natural frequency; ξ is the damping ratio; m is the mass of the force measuring platform; and c is the tire damping coefficient.

[0034] This invention integrates the measurement of damping coefficients of aircraft tires in different directions into a single testing device, enabling the testing of aircraft tire damping coefficients in a laboratory. The arrangement and installation of the testing device can accurately simulate the load and vibration of aircraft tires, yielding the damping ratio and natural frequency of the aircraft tires, and calculating the damping coefficient using formulas. The servo actuator is used for loading, resulting in stable load and good continuity. The testing device has a simple structure, is easy to construct, reduces the scale of the test, and saves on testing costs. Attached Figure Description

[0035] Figure 1 A schematic diagram of the overall structure of the aircraft tire damping test device;

[0036] Figure 2 This is a schematic diagram of the vertical loading mechanism;

[0037] Figure 3 This is a structural diagram illustrating the connection method of the vertical loading mechanism;

[0038] Figure 4 This is a schematic diagram of the connection between the lead screw and the force measuring platform.

[0039] Figure 5 A structural diagram illustrating the mounting method of aircraft tires and vibrators;

[0040] Figure 6 A schematic diagram showing the installation location of the vibrator;

[0041] Figure 7 A schematic diagram of the structure for measuring the longitudinal damping of aircraft tires;

[0042] Figure 8 A schematic diagram of the structure for measuring the lateral damping of aircraft tires;

[0043] Figure 9 A schematic diagram of the structure for measuring the torsional damping of aircraft tires.

[0044] In the figure, 1-servo actuator, 2-load-bearing frame, 3-test bench, 4-connecting lug, 5-Y-type connector, 6-force sensor, 7-lead screw, 8-force measuring platform, 9-lifting ring, 10-load-bearing wall, 11-aircraft tire, 12-torsional vibrator, 13-lateral vibrator, 14-longitudinal vibrator, 15-flange. Detailed Implementation

[0045] To clearly illustrate the technical features of this patent, the following detailed description is provided through specific embodiments and in conjunction with the accompanying drawings.

[0046] The present invention provides an aircraft tire damping coefficient testing device comprising a test bench 3, a test piece, a force measuring platform 8, a flange 15, a load-bearing frame 2, a load-bearing wall 10, a vertical force loading mechanism, a damping coefficient testing system, and a data acquisition and analysis system.

[0047] The test specimens were different models of aircraft tires 11;

[0048] The test bench 3 is fixed on the ground, the load-bearing wall 10 is fixedly installed on the test bench 3, and the load-bearing wall 10 is also fixedly installed with a flange 15 for fixing the test piece; the aircraft tire 11 is installed on the load-bearing wall 10 through the flange 15 to ensure that the aircraft tire 11 is fixed.

[0049] The force measuring platform 8 is horizontally positioned next to the load-bearing wall 10 and below the test specimen. Vertical force and triaxial excitation are applied to the force measuring platform 8 by the vertical force loading mechanism and the damping coefficient testing system, respectively.

[0050] Specifically:

[0051] It also includes a load-bearing frame 2, which is fixedly installed on the test bench 3;

[0052] The vertical force loading mechanism is installed between the top of the load-bearing frame 2 and the force measuring platform 8, and includes a vertical power source that drives the force measuring platform 8 to rise and fall linearly.

[0053] The damping coefficient testing system includes three exciters mounted on the test bench 3 and a triaxial acceleration sensor placed on the force measuring platform 8 by a magnetic base. The three exciters are respectively arranged in the longitudinal direction perpendicular to the axis of the test piece and in the lateral direction parallel to the axis of the test piece. The three exciters are a torsional exciter 12, a lateral exciter 13 and a longitudinal exciter 14. The torsional exciter 12 acts at the longitudinal edge of the force measuring platform 8, the lateral exciter 13 acts at the lateral center of the force measuring platform 8, and the longitudinal exciter 14 acts at the longitudinal center of the force measuring platform 8.

[0054] Regarding the vertical power source:

[0055] The vertical force loading mechanism includes several uniformly arranged vertical power sources, each of which includes a servo actuator 1, a boom 7, a vertical force sensor 6, and a lifting ring 9.

[0056] The housing of the servo actuator 1 is fixedly installed on the top of the load-bearing frame 2. The output rod of the servo actuator 1 is connected to the vertical force sensor 6 via a Y-type connector 5. The top of the boom 7 is fixedly connected to the vertical force sensor 6, and the bottom of the boom 7 is fixedly connected to the force measuring platform 8 via another Y-type connector 5.

[0057] The output rod of the vertical power source located on one side of the test piece is kept in synchronous motion through the connecting lug 4, which is fixedly connected to the output rod of the vertical power source.

[0058] Regarding the damping coefficient testing system:

[0059] The housings of the torsional vibrator 12, the lateral vibrator 13, and the longitudinal vibrator 14 are all hinged to the test bench 3 via a bracket, and the output ends of the torsional vibrator 12, the lateral vibrator 13, and the longitudinal vibrator 14 are all connected to the force measuring platform 8.

[0060] A longitudinal vibrator 14 is positioned in the middle of the force measuring platform 8 to achieve longitudinal vibration of the aircraft tire 11. A lateral vibrator 13 is installed on the side of the aircraft tire 11, positioned in the middle of the force measuring platform 8 to achieve lateral vibration of the aircraft tire 11. A torsional vibrator 12 is installed longitudinally on the aircraft tire 11, positioned at the edge of the force measuring platform 8 to achieve torsional vibration of the aircraft tire 11.

[0061] About the data acquisition system:

[0062] The vertical force sensors 6 and the triaxial acceleration sensors mentioned above constitute the data output of the data acquisition system. The frequency and amplitude of the exciter are controlled by the frequency sweep signal generator, and the exciter is started to vibrate after passing through the power amplifier.

[0063] The test method of the aircraft tire damping coefficient testing device of the present invention includes the following steps:

[0064] Step 1: Measure the tire pressure of the aircraft tires to ensure that the tire pressure meets the test requirements;

[0065] Step 2: Install the test device according to the test requirements, fix the aircraft tire, ensure that the force measuring platform is horizontal and corresponds to the center of the aircraft tire, and keep the vertical force applied by different servo actuators the same.

[0066] Step 3: Activate the servo actuator to raise the force measuring platform and bring it into contact with the aircraft tire;

[0067] Step 4: Place the accelerometers at the measurement points as required by the test, ensuring that the accelerometers are oriented in the same direction;

[0068] Step 5: Start the data acquisition and analysis system, clear the cache, and start data acquisition;

[0069] Step Six: Continue to raise the force measuring platform until the vertical force on the aircraft tire reaches the test load.

[0070] Step 7: Keeping the vertical force constant, connect the vibrator to the force measuring platform, ensuring the vibrator is horizontal, and apply lateral excitation, longitudinal excitation, and torsional excitation to the force measuring platform respectively;

[0071] Step 8: During the application of lateral, longitudinal, and torsional excitation, a sinusoidal frequency sweep is used to cause the force measuring platform and the aircraft tire to vibrate.

[0072] Step 9: Observe the data from the data acquisition system. When the aircraft tire resonates with the force measurement platform, the frequency sweep ends and the data acquisition system is stopped.

[0073] Step 10: Turn off the vibrator and disconnect the vibrator from the force measuring platform;

[0074] Step 11: Lower the force measuring platform to release the vertical load until the force measuring platform is no longer in contact with the aircraft tire;

[0075] Step 12: After the experiment is completed, the data is processed and analyzed through the data acquisition system to obtain the natural frequency and damping ratio of the aircraft tire;

[0076] Step 13: Substitute the natural frequency and damping ratio obtained from the experiment into formula (1) to calculate the damping coefficient of the aircraft tire.

[0077]

[0078] Where: f is the natural frequency; ξ is the damping ratio; m is the mass of the force measuring platform; and c is the tire damping coefficient.

[0079] There are many specific ways to implement this invention. The above description is only a preferred embodiment of this invention. It should be noted that for those skilled in the art, several improvements can be made without departing from the principle of this invention, and these improvements should also be considered within the scope of protection of this invention.

Claims

1. A test method based on an aircraft tire damping coefficient testing device, characterized in that, The aircraft tire damping coefficient testing device includes a test bench (3), test piece, force measuring platform (8), flange (15), load-bearing frame (2), load-bearing wall (10), vertical force loading mechanism and damping coefficient testing system; The load-bearing wall (10) is fixedly installed on the test bench (3), and the load-bearing wall (10) is also fixedly installed with a flange (15) for fixing the test piece; The force measuring platform (8) is horizontally set on one side of the load-bearing wall (10) and below the test specimen. Vertical force and triaxial excitation are applied to the force measuring platform (8) by the vertical force loading mechanism and the damping coefficient testing system, respectively. Includes the following steps: Step 1: Measure the tire pressure of the aircraft tires to ensure that the tire pressure meets the test requirements; Step 2: Install the test device according to the test requirements, fix the aircraft tire, ensure that the force measuring platform is horizontal and corresponds to the center of the aircraft tire, and keep the vertical force applied by different servo actuators the same. Step 3: Activate the servo actuator to raise the force measuring platform and bring it into contact with the aircraft tire; Step 4: Place the accelerometers at the measurement points as required by the test, ensuring that the accelerometers are oriented in the same direction; Step 5: Start the data acquisition and analysis system, clear the cache, and start data acquisition; Step Six: Continue to raise the force measuring platform until the vertical force on the aircraft tire reaches the test load. Step 7: Keeping the vertical force constant, connect the vibrator to the force measuring platform, ensuring the vibrator is horizontal, and apply lateral excitation, longitudinal excitation, and torsional excitation to the force measuring platform respectively; Step 8: During the application of lateral, longitudinal, and torsional excitation, a sinusoidal frequency sweep is used to cause the force measuring platform and the aircraft tire to vibrate. Step 9: Observe the data from the data acquisition system. When the aircraft tire resonates with the force measurement platform, the frequency sweep ends and the data acquisition system is stopped. Step 10: Turn off the vibrator and disconnect the vibrator from the force measuring platform; Step 11: Lower the force measuring platform to release the vertical load until the force measuring platform is no longer in contact with the aircraft tire; Step 12: After the experiment is completed, the data is processed and analyzed through the data acquisition system to obtain the natural frequency and damping ratio of the aircraft tire; Step 13: Substitute the natural frequency and damping ratio obtained from the experiment into formula (1) to calculate the damping coefficient of the aircraft tire; Where: f is the natural frequency; ξ is the damping ratio; m is the mass of the force measuring platform; and c is the tire damping coefficient.

2. The test method based on the aircraft tire damping coefficient test device according to claim 1, characterized in that, It also includes a load-bearing frame (2), which is fixedly installed on the test bench (3); The vertical force loading mechanism is installed between the top of the load-bearing frame (2) and the force measuring platform (8), and includes a vertical power source that drives the force measuring platform (8) to rise and fall linearly; The damping coefficient testing system includes three exciters mounted on the test bench (3) and a triaxial acceleration sensor placed on the force measuring platform (8) via a magnetic base. The three exciters are respectively arranged in the longitudinal direction perpendicular to the axis of the test piece and in the lateral direction parallel to the axis of the test piece. The three exciters are divided into a torsional exciter (12), a lateral exciter (13), and a longitudinal exciter (14). The torsional exciter (12) acts at the longitudinal edge of the force measuring platform (8), the lateral exciter (13) acts at the lateral center of the force measuring platform (8), and the longitudinal exciter (14) acts at the longitudinal center of the force measuring platform (8).

3. The test method based on the aircraft tire damping coefficient test device according to claim 2, characterized in that, The vertical force loading mechanism includes several uniformly arranged vertical power sources, which include a servo actuator (1), a boom (7), a vertical force sensor (6), and a lifting ring (9). The housing of the servo actuator (1) is fixedly installed on the top of the load-bearing frame (2). The output rod of the servo actuator (1) is connected to the vertical force sensor (6) via a Y-type connector (5). The top of the boom (7) is fixedly connected to the vertical force sensor (6), and the bottom of the boom (7) is fixedly connected to the force measuring platform (8) via another Y-type connector (5).

4. The test method based on the aircraft tire damping coefficient test device according to claim 3, characterized in that, The output rod of the vertical power source located on one side of the test piece is kept in synchronous motion through the connecting lug (4), which is fixedly connected to the output rod of the vertical power source.

5. The test method based on the aircraft tire damping coefficient test device according to claim 2, characterized in that, The housings of the torsional vibrator (12), the lateral vibrator (13), and the longitudinal vibrator (14) are all hinged to the test bench (3) via a bracket, and the output ends of the torsional vibrator (12), the lateral vibrator (13), and the longitudinal vibrator (14) are all connected to the force measuring platform (8).

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