Aviation tire damping coefficient testing device and testing method thereof

Abstract

The invention discloses an aircraft tire damping coefficient testing device and a testing method thereof, and belongs to the technical field of aircraft tire testing. The real loading condition and the vibration condition of the aircraft tire are simulated, and the real damping coefficient of the aircraft tire is obtained. Comprising a test bed, a test piece, a force measuring platform, a flange, a force bearing frame, a force bearing wall, a vertical force loading mechanism and a damping coefficient testing system, the bearing wall is fixedly mounted on the test bed, and a flange for fixing a test piece is also fixedly mounted on the bearing wall; the force measuring platform is horizontally arranged beside the force bearing wall and is positioned below the test piece, and vertical force and three-way excitation are respectively applied to the force measuring platform through the vertical force loading mechanism and the damping coefficient testing system. Measurement of the damping coefficients of the aircraft tire in different directions is concentrated on the same test equipment, and the damping coefficient test of the aircraft tire is completed in a laboratory.

Description

Technical Field

[0001] The invention relates to an aircraft tire damping coefficient test device and a test method thereof, belonging to the technical field of aircraft tire testing. Background Art

[0002] As one of the main parts of an aircraft, aircraft tires need to withstand high speed, high load, and high internal pressure. They are extremely important for the safe take-off, landing, and taxiing of aircraft, and their use conditions are relatively harsh. When the aircraft lands, the tires bear the entire load of the aircraft and the high-speed impact load. Aircraft tires are a strong elastic body composed of materials such as rubber and nylon cords. They need to have good deformation ability and be able to absorb these impact kinetic energy well.

[0003] The damping characteristics of aircraft tires can effectively absorb and disperse mechanical vibration and impact energy, reduce the transmission of vibration, have good vibration reduction and isolation effects, and can reduce the vibration of mechanical parts during aircraft flight and landing. At present, there are few studies on the damping coefficient of aircraft tires. The research on aircraft tire damping mostly uses analytical methods, which usually use rigid ring models, but their calculation results cannot be directly related to the actual structure of the tire, and there is a lack of experimental comparative analysis of the damping coefficient of aircraft tires. Therefore, it is crucial to study the damping coefficient of aircraft tires. Summary of the invention

[0004] In view of the above problems, the present invention proposes an aircraft tire damping coefficient test device and a test method thereof, which simulate the actual loading and vibration conditions of the aircraft tire and obtain the actual damping coefficient of the aircraft tire.

[0005] The technical solution of the present invention is as follows: it comprises 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 mounted on the test bench 3, and the load-bearing wall 10 is also fixedly mounted with a flange 15 for fixing the test piece;

[0007] The force measuring platform 8 is horizontally arranged beside the load-bearing wall 10 and under the test piece. The vertical force and three-dimensional excitation are applied to the force measuring platform 8 respectively through the vertical force loading mechanism and the damping coefficient testing system.

[0008] Specifically:

[0009] It also includes a load-bearing frame 2, which is fixedly mounted on a 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 test system includes three exciters installed on the test bench 3 and a three-axis acceleration sensor placed on the force measuring platform 8 through 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 on the longitudinal edge of the force measuring platform 8, the lateral exciter 13 acts on the lateral center of the force measuring platform 8, and the longitudinal exciter 14 acts on the longitudinal center of the force measuring platform 8.

[0012] About vertical power source:

[0013] The vertical force loading mechanism includes a plurality of evenly arranged vertical power sources, and the vertical power sources include a servo actuator 1, a suspension rod 7, a vertical force sensor 6 and a suspension ring 9;

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

[0015] Furthermore, the output rod of the vertical power source located at one side of the test piece keeps synchronous movement through the connecting ear piece 4, and the connecting ear piece 4 is fixedly connected to the output rod of the vertical power source.

[0016] About the damping coefficient test system:

[0017] The shells of the torsional vibration exciter 12 , the lateral vibration exciter 13 and the longitudinal vibration exciter 14 are hinged to the test bench 3 through brackets, and the output ends of the torsional vibration exciter 12 , the lateral vibration exciter 13 and the longitudinal vibration exciter 14 are connected to the force measuring platform 8 .

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

[0019] Step 1: Measure the aircraft tire pressure to ensure that the aircraft 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 the vertical force applied by different servo actuators remains the same;

[0021] Step 3: Start the servo actuator to lift the force measuring platform so that the force measuring platform contacts the aircraft tire;

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

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

[0024] Step 6: Continue to lift the force measuring platform until the vertical force on the aircraft tire reaches the specified load of the test;

[0025] Step 7: Keep the vertical force unchanged, connect the exciter to the force measuring platform, ensure that the exciter is horizontal, and apply lateral vibration, longitudinal vibration and torsional vibration to the force measuring platform respectively;

[0026] Step 8: During the process of applying lateral vibration, longitudinal vibration and torsional vibration, a sine frequency sweep is used to make the force measuring platform and the aircraft tire vibrate;

[0027] Step 9: Observe the data of 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 vibration exciter and disconnect it from the force measuring platform;

[0029] Step 11: The force measuring platform descends and the vertical load is released until the force measuring platform is no longer in contact with the aircraft tire;

[0030] Step 12: After the test is completed, the data is sorted 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 test 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; c is the tire damping coefficient.

[0034] The present invention concentrates the measurement of damping coefficients of aircraft tires in different directions on the same test equipment, thereby completing the damping coefficient test of aircraft tires in a laboratory; the arrangement and installation of the test device can accurately simulate the loading and vibration of the aircraft tire, obtain the damping ratio and natural frequency of the aircraft tire, and calculate the damping coefficient through a formula; a servo actuator is used for loading, so the load is stable and the continuity is good; the test device has a simple structure and is convenient to construct, which reduces the test scale and saves the test cost. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0037] Figure 3 It is a structural schematic diagram of the vertical loading mechanism connection mode;

[0038] Figure 4 It is a structural schematic diagram of the connection between the lead screw and the force measuring platform;

[0039] Figure 5 This is a structural diagram of the installation method of the aircraft tire and the vibrator;

[0040] Figure 6 It is a structural diagram of the installation position of the vibration exciter;

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

[0042] Figure 8 This is a schematic diagram of the structure for measuring the lateral damping of an aircraft tire;

[0043] Fig. 9 Schematic diagram of the structure for measuring torsional damping of aircraft tires.

[0044] In the figure, 1-servo actuator, 2-load-bearing frame, 3-test bench, 4-connecting ear piece, 5-Y-type joint, 6-force sensor, 7-screw, 8-force measuring platform, 9-lifting ring, 10-load-bearing wall, 11-aircraft tire, 12-torsion exciter, 13-lateral exciter, 14-longitudinal exciter, 15-flange. DETAILED DESCRIPTION

[0045] In order to clearly illustrate the technical features of this patent, this patent is elaborated in detail below through a specific implementation method and in combination with its accompanying drawings.

[0046] An aviation tire damping coefficient test device of the present invention comprises 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 test system and a data acquisition and analysis system.

[0047] The test pieces are aircraft tires 11 of different models;

[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 arranged beside the load-bearing wall 10 and under the test piece. The vertical force and three-dimensional excitation are applied to the force measuring platform 8 respectively through the vertical force loading mechanism and the damping coefficient testing system.

[0050] Specifically:

[0051] It also includes a load-bearing frame 2, which is fixedly mounted on a 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 test system includes three exciters installed on the test bench 3 and a three-axis 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 divided into a torsional exciter 12, a lateral exciter 13 and a longitudinal exciter 14. The torsional exciter 12 acts on the longitudinal edge of the force measuring platform 8, the lateral exciter 13 acts on the lateral center of the force measuring platform 8, and the longitudinal exciter 14 acts on the longitudinal center of the force measuring platform 8.

[0054] About vertical power source:

[0055] The vertical force loading mechanism includes a plurality of evenly arranged vertical power sources, and the vertical power sources include a servo actuator 1, a suspension rod 7, a vertical force sensor 6 and a suspension ring 9;

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

[0057] The output rod of the vertical power source located at one side of the test piece keeps synchronous movement through the connecting ear piece 4, and the connecting ear piece 4 is fixedly connected to the output rod of the vertical power source.

[0058] About the damping coefficient test system:

[0059] The shells of the torsional vibration exciter 12 , the lateral vibration exciter 13 and the longitudinal vibration exciter 14 are hinged to the test bench 3 through brackets, and the output ends of the torsional vibration exciter 12 , the lateral vibration exciter 13 and the longitudinal vibration exciter 14 are connected to the force measuring platform 8 .

[0060] The longitudinal exciter 14 is located in the middle of the force measuring platform 8 to realize longitudinal excitation of the aircraft tire 11. The lateral exciter 13 is installed laterally on the aircraft tire 11, and the lateral exciter 13 is located in the middle of the force measuring platform 8 to realize lateral excitation of the aircraft tire 11. The torsional exciter 12 is installed longitudinally on the aircraft tire 11, and the torsional exciter 12 is located at the edge of the force measuring platform 8 to realize torsional excitation of the aircraft tire 11.

[0061] About the data acquisition system:

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

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

[0064] Step 1: Measure the aircraft tire pressure to ensure that the aircraft 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 the vertical force applied by different servo actuators remains the same;

[0066] Step 3: Start the servo actuator to lift the force measuring platform so that the force measuring platform contacts the aircraft tire;

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

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

[0069] Step 6: Continue to lift the force measuring platform until the vertical force on the aircraft tire reaches the specified load of the test;

[0070] Step 7: Keep the vertical force unchanged, connect the exciter to the force measuring platform, ensure that the exciter is horizontal, and apply lateral vibration, longitudinal vibration and torsional vibration to the force measuring platform respectively;

[0071] Step 8: During the process of applying lateral vibration, longitudinal vibration and torsional vibration, a sine frequency sweep is used to make the force measuring platform and the aircraft tire vibrate;

[0072] Step 9: Observe the data of 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 vibration exciter and disconnect it from the force measuring platform;

[0074] Step 11: The force measuring platform descends and the vertical load is released until the force measuring platform is no longer in contact with the aircraft tire;

[0075] Step 12: After the test is completed, the data is sorted 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 test 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; c is the tire damping coefficient.

[0079] There are many specific implementation ways of the present invention. The above is only the preferred implementation mode of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principle of the present invention. These improvements should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft tire damping coefficient test device, characterized in that: It comprises 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; The load-bearing wall (10) is fixedly mounted on the test bench (3), and a flange (15) for fixing the test piece is also fixedly mounted on the load-bearing wall (10); The force measuring platform (8) is horizontally arranged beside the load-bearing wall (10) and under the test piece, and vertical force and three-dimensional excitation are applied to the force measuring platform (8) respectively through a vertical force loading mechanism and a damping coefficient testing system.

2. The aircraft tire damping coefficient test device according to claim 1, characterized in that: It also includes a load-bearing frame (2), wherein the load-bearing frame (2) is fixedly mounted 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 for driving the force measuring platform (8) to move up and down linearly; The damping coefficient test system comprises three exciters installed on a test bench (3) and a three-axis acceleration sensor placed on a force measuring platform (8) via a magnetic base. The three exciters are respectively arranged in a longitudinal direction perpendicular to the axis of the test piece and in a 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 on the longitudinal edge of the force measuring platform (8), the lateral exciter (13) acts on the lateral center of the force measuring platform (8), and the longitudinal exciter (14) acts on the longitudinal center of the force measuring platform (8).

3. The aircraft tire damping coefficient test device according to claim 2, characterized in that: The vertical force loading mechanism comprises a plurality of evenly arranged vertical power sources, wherein the vertical power sources comprise a servo actuator (1), a suspension rod (7), a vertical force sensor (6) and a suspension ring (9); The housing of the servo actuator (1) is fixedly mounted 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-shaped joint (5), the top of the suspension rod (7) is fixedly connected to the vertical force sensor (6), and the bottom of the suspension rod (7) is fixedly connected to the force measuring platform (8) via another Y-shaped joint (5).

4. 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 via a connecting ear piece (4), and the connecting ear piece (4) is fixedly connected to the output rod of the vertical power source.

5. The aircraft tire damping coefficient test device according to claim 2, characterized in that: The shells of the torsional vibration exciter (12), the lateral vibration exciter (13) and the longitudinal vibration exciter (14) are all hinged to the test bench (3) through brackets, and the output ends of the torsional vibration exciter (12), the lateral vibration exciter (13) and the longitudinal vibration exciter (14) are all connected to the force measuring platform (8).

6. A test method for the aircraft tire damping coefficient test device according to claim 1, characterized in that: The steps include: Step 1: Measure the aircraft tire pressure to ensure that the aircraft 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 the vertical force applied by different servo actuators remains the same; Step 3: Start the servo actuator to lift the force measuring platform so that the force measuring platform contacts the aircraft tire; Step 4: Place the accelerometer at the measuring points required by the test, ensuring that the accelerometers are in the same direction; Step 5: Start the data acquisition and analysis system, clear and collect data; Step 6: Continue to lift the force measuring platform until the vertical force on the aircraft tire reaches the specified load of the test; Step 7: Keep the vertical force unchanged, connect the exciter to the force measuring platform, ensure that the exciter is horizontal, and apply lateral vibration, longitudinal vibration and torsional vibration to the force measuring platform respectively; Step 8: During the process of applying lateral vibration, longitudinal vibration and torsional vibration, a sine frequency sweep is used to make the force measuring platform and the aircraft tire vibrate; Step 9: Observe the data of 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 vibration exciter and disconnect it from the force measuring platform; Step 11: The force measuring platform descends and the vertical load is released until the force measuring platform is no longer in contact with the aircraft tire; Step 12: After the test is completed, the data is sorted 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 test 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; c is the tire damping coefficient.

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