Aircraft tire rigidity test device and test method thereof

Abstract

The invention discloses an aircraft tire rigidity testing device and a testing method thereof, and belongs to the technical field of aircraft tire testing. The rigidity change characteristic of the aircraft tire is obtained by simulating the real loading condition of the aircraft tire. Comprising a test bed, a force measuring platform, a test piece, a flange, a force bearing wall, a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism and a torsional force loading mechanism, the force bearing wall comprises a first force bearing wall and a second force bearing wall which are arranged on the test bed and are oppositely arranged, and a flange for fixing a test piece is also fixedly arranged between the first force bearing wall and the second force bearing wall; and a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism and a torsional force loading mechanism are used for respectively applying a vertical force, a lateral force, a longitudinal force and a torsional force to the force measuring platform. According to the invention, the rigidity test of the aircraft tire is completed in a laboratory.

Description

Technical Field

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

[0002] As a key component of aircraft landing gear, the mechanical properties of aircraft tires affect many aircraft performances, such as aircraft power, handling stability, braking safety, fuel economy, etc. As the only component for load transmission between the ground and the aircraft landing gear, the mechanical properties of aircraft tires are one of the key basic properties for studying aircraft ground dynamics. In the study of the mechanical properties of aircraft tires, the stiffness of aircraft tires not only directly affects the landing gear's drop shock buffering performance and the aircraft's taxiing handling performance, but also serves as one of the important mechanical property parameters in aircraft analysis and design.

[0003] Considering that the tires will also be subjected to huge impact loads when the aircraft lands, there are great requirements for the stiffness of aircraft tires. As one of the strong nonlinear factors of the front landing gear, the tire stiffness characteristics have an important influence on the front landing gear shimmy. At present, there are few experimental studies on the stiffness of aircraft tires, and there are no experiments to verify the simulation results for the simulation study of the stiffness of aircraft tires. Therefore, it is very important to study the stiffness of aircraft tires. Summary of the invention

[0004] In view of the above problems, the present invention proposes an aircraft tire stiffness test device and a test method thereof, which can obtain the stiffness variation characteristics of the aircraft tire by simulating the actual loading condition of the aircraft tire.

[0005] The technical solution of the present invention is: comprising a test bench 3, a force measuring platform 8, a test piece, a flange 10, a load-bearing wall, a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism, and a torsional force loading mechanism;

[0006] The load-bearing wall comprises a first load-bearing wall 12 and a second load-bearing wall 13 installed on the test bench and arranged relatively to each other, and a flange 10 for fixing the test piece is fixedly installed between the first load-bearing wall 12 and the second load-bearing wall 13;

[0007] The force measuring platform 8 is horizontally placed between the first load-bearing wall 12 and the second load-bearing wall 13 and under the test piece. Vertical force, lateral force, longitudinal force and torsional force are applied to the force measuring platform 8 respectively through a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism and a torsional force loading mechanism.

[0008] Specifically, it also includes a load-bearing frame 1;

[0009] The load-bearing frame 1 is fixedly mounted on the test bench 3; the vertical force loading mechanism is installed between the top of the load-bearing frame 1 and the force measuring platform 8, and includes a vertical power source that drives the force measuring platform 8 to rise and fall linearly;

[0010] Several groups of cross beams 21 and brackets 22 are fixedly installed around the load-bearing frame 1; a height-adjustable horizontal power source is installed on the bracket 22, and the horizontal power source is arranged horizontally, and its outer end is detachably installed on the bracket 22, and its inner end is installed on the force measuring platform 8. The several horizontal power sources are divided into a longitudinal power source perpendicular to the axis of the test piece and a lateral power source parallel to the axis of the test piece;

[0011] The longitudinal force loading mechanism includes a longitudinal power source, which drives the force measuring platform 8 to translate longitudinally;

[0012] The lateral force loading mechanism includes a lateral power source located on one side of the test piece, and the lateral power source drives the force measuring platform 8 to translate in a lateral direction;

[0013] The torsion force loading mechanism includes two lateral power sources located at two sides of the test piece and having different axes, and the force measuring platform 8 is driven to twist in the horizontal direction through these two lateral power sources.

[0014] About vertical power source:

[0015] The vertical force loading mechanism includes a plurality of evenly arranged vertical power sources, and the vertical power sources include a servo actuator 2, a suspension rod 7, a vertical force sensor 6 and a suspension ring 9;

[0016] The shell of the servo actuator 2 is fixedly installed on the top of the load-bearing frame 1, and the output rod of the servo actuator 2 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.

[0017] 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.

[0018] About horizontal power source:

[0019] The horizontal power source includes an electric cylinder and a horizontal force sensor 20 . The outer end of the electric cylinder is connected to a pair of detachably connected clamping blocks 23 , which clamp the bracket 22 . The inner end of the electric cylinder is connected to the force measuring platform 8 via the horizontal force sensor 20 .

[0020] Furthermore, the horizontal power source around the force measuring platform 8 is divided into a first longitudinal electric cylinder 14, a second longitudinal electric cylinder 15, a first lateral and torsional electric cylinder 16, a second lateral electric cylinder 17 and a second torsional electric cylinder 18. The first longitudinal electric cylinder 14 and the second longitudinal electric cylinder 15 are arranged in parallel in the longitudinal direction perpendicular to the axis of the test piece, the first lateral and torsional electric cylinder 16 and the second lateral electric cylinder 17 are arranged in parallel in the lateral direction parallel to the axis of the test piece, and the second torsional electric cylinder 18 is also arranged in the lateral direction parallel to the axis of the test piece. The first lateral and torsional electric cylinder 16 and the second torsional electric cylinder 18 are located on both sides of the test piece, and the axes of the two are different.

[0021] The test method in this case includes the following steps:

[0022] Step 1: Measure the air pressure of the aircraft tire 11 to ensure that the air pressure of the aircraft tire 11 meets the test requirements;

[0023] Step 2: Install the aircraft tire 11 according to the test device, ensure that the force measuring platform 8 is level, and the vertical loads applied by each servo actuator 2 remain the same;

[0024] Step 3: Start the servo actuator 2 to lift the force measuring platform 8 so that the force measuring platform 8 contacts the aircraft tire 11;

[0025] Step 4: Start the data acquisition system, clear and collect data;

[0026] Step 5: Continue to lift the force measuring platform 8 so that the vertical load on the aircraft tire 11 reaches the specified value of the test, and the vertical stiffness test is completed;

[0027] Step 6: Keep the vertical load specified in the test unchanged, adjust the height position of the electric cylinder to ensure that the electric cylinder is level;

[0028] Step 7: testing the lateral stiffness, longitudinal stiffness and torsional stiffness of the test piece respectively, that is, applying horizontal forces in different directions through the electric cylinder to displace the force measuring platform 8 until the horizontal force on the aircraft tire 11 reaches the specified value of the test;

[0029] Step 8: Turn off the data acquisition system and the test is completed;

[0030] Step 9: Start the electric cylinder and release the horizontal force until the horizontal force is zero;

[0031] Step 10: Disconnect the electric cylinder from the force measuring platform;

[0032] Step 11: The force measuring platform descends and the vertical force is released until the force measuring platform is no longer in contact with the aircraft tire;

[0033] Step 12: The overall test is completed, check and organize the data.

[0034] The present invention integrates different stiffness measurements of aircraft tires on the same test equipment, thereby completing the stiffness test of the aircraft tire in a laboratory; the arrangement and installation of the test device can accurately simulate the loading of the aircraft tire and obtain the stiffness change of the aircraft tire; the servo actuator is used for loading, and the load is stable and continuous; 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 stiffness test device;

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

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

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

[0039] Figure 5 This is a schematic diagram of the installation structure of an aircraft tire;

[0040] Figure 6 It is a schematic diagram of the connection structure between the lateral motor, longitudinal motor and torsional motor and the test bench;

[0041] Figure 7 This is a schematic diagram of the motor installation structure;

[0042] Figure 8 This is a schematic diagram of the structure of the motor and bracket installation;

[0043] Fig. 9 It is the structural schematic diagram of the longitudinal stiffness measurement;

[0044] Fig.10 It is a schematic diagram of the structure for torsional stiffness measurement;

[0045] Fig.11 Schematic diagram of the structure for lateral stiffness measurement.

[0046] In the figure, 1-load-bearing frame, 2-servo actuator, 3-test bench, 4-connecting ear piece, 5-Y-type joint, 6-vertical force sensor, platform 7-screw, 8-force measuring platform, 9-lifting ring, 10-flange, 11-aircraft tire, 12-first load-bearing wall, 13-second load-bearing wall, 14-first longitudinal electric cylinder, 15-second longitudinal electric cylinder, 16-first lateral and torsional electric cylinder, 17-second lateral electric cylinder, 18-second torsional electric cylinder, 19-rod end joint bearing, 20-horizontal force sensor, 21-crossbeam, 22-bracket, 23-clamp block. DETAILED DESCRIPTION

[0047] 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.

[0048] The present invention comprises a test bench 3, a force measuring platform 8, a test piece, a flange 10, a load-bearing frame 1, a load-bearing wall, a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism, a torsional force loading mechanism and a data acquisition system.

[0049] The test pieces are aircraft tires 11 of different models;

[0050] The test bench 3 is fixed on the ground, and the load-bearing walls include a first load-bearing wall 12 and a second load-bearing wall 13 installed on the test bench and arranged relatively to each other, and a flange 10 for fixing the test piece is also fixedly installed between the first load-bearing wall 12 and the second load-bearing wall 13; the aircraft tire 11 is installed between the first load-bearing wall 12 and the second load-bearing wall 13 through the flange 10 to ensure that the aircraft tire 11 is fixed.

[0051] The force measuring platform 8 is horizontally placed between the first load-bearing wall 12 and the second load-bearing wall 13 and under the test piece. Vertical force, lateral force, longitudinal force and torsional force are applied to the force measuring platform 8 respectively through a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism and a torsional force loading mechanism.

[0052] Specifically:

[0053] The load-bearing frame 1 is fixedly mounted on the test bench 3;

[0054] The vertical force loading mechanism is installed between the top of the load-bearing frame 1 and the force measuring platform 8, and includes a vertical power source that drives the force measuring platform 8 to rise and fall linearly;

[0055] Several groups of beams 21 and brackets 22 are fixedly installed around the load-bearing frame 1;

[0056] A height-adjustable horizontal power source is installed on the bracket 22. The horizontal power source is arranged horizontally, and its outer end is detachably installed on the bracket 22, and its inner end is installed on the force measuring platform 8. The horizontal power sources are divided into a longitudinal power source perpendicular to the axis of the test piece and a lateral power source parallel to the axis of the test piece.

[0057] The longitudinal force loading mechanism includes a longitudinal power source, which drives the force measuring platform 8 to translate longitudinally;

[0058] The lateral force loading mechanism includes a lateral power source located on one side of the test piece, and the lateral power source drives the force measuring platform 8 to translate in a lateral direction;

[0059] The torsion force loading mechanism includes two lateral power sources located at two sides of the test piece and having different axes, and the force measuring platform 8 is driven to twist in the horizontal direction through these two lateral power sources.

[0060] When in use, vertical pressure is first applied to the force measuring platform 8 through a vertical power source to test the vertical stiffness, and then the lateral force loading mechanism, longitudinal force loading mechanism, and torsional force loading mechanism are started respectively to test the lateral stiffness, longitudinal stiffness, and torsional stiffness of the test piece respectively.

[0061] About vertical power source:

[0062] The vertical force loading mechanism includes a plurality of evenly arranged vertical power sources, and the vertical power sources include a servo actuator 2, a suspension rod 7, a vertical force sensor 6 and a suspension ring 9;

[0063] The shell of the servo actuator 2 is fixedly installed on the top of the load-bearing frame 1, and the output rod of the servo actuator 2 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.

[0064] 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.

[0065] About horizontal power source:

[0066] The horizontal power source includes an electric cylinder and a horizontal force sensor 20 . The outer end of the electric cylinder is connected to a pair of detachably connected clamping blocks 23 , which clamp the bracket 22 . The inner end of the electric cylinder is connected to the force measuring platform 8 via the horizontal force sensor 20 .

[0067] The horizontal power source around the force measuring platform 8 is divided into a first longitudinal electric cylinder 14, a second longitudinal electric cylinder 15, a first lateral and torsional electric cylinder 16, a second lateral electric cylinder 17 and a second torsional electric cylinder 18. The first longitudinal electric cylinder 14 and the second longitudinal electric cylinder 15 are arranged in parallel in the longitudinal direction perpendicular to the axis of the test piece, the first lateral and torsional electric cylinder 16 and the second lateral electric cylinder 17 are arranged in parallel in the lateral direction parallel to the axis of the test piece, and the second torsional electric cylinder 18 is also arranged in the lateral direction parallel to the axis of the test piece. The first lateral and torsional electric cylinder 16 and the second torsional electric cylinder 18 are located on both sides of the test piece, and the axes of the two are different.

[0068] The vertical force sensors 6 and horizontal force sensors 20 mentioned above constitute the data input of the data acquisition system.

[0069] The test method of the aircraft tire stiffness test device of the present invention comprises the following steps:

[0070] Step 1: Measure the air pressure of the aircraft tire 11 to ensure that the air pressure of the aircraft tire 11 meets the test requirements;

[0071] Step 2: Install the aircraft tire 11 according to the test device, ensure that the force measuring platform 8 is level, and the vertical loads applied by each servo actuator 2 remain the same;

[0072] Step 3: Start the servo actuator 2 to lift the force measuring platform 8 so that the force measuring platform 8 contacts the aircraft tire 11;

[0073] Step 4: Start the data acquisition system, clear and collect data;

[0074] Step 5: Continue to lift the force measuring platform 8 so that the vertical load on the aircraft tire 11 reaches the specified value of the test, and the vertical stiffness test is completed;

[0075] Step 6: Keep the vertical load specified in the test unchanged, adjust the height position of the electric cylinder to ensure that the electric cylinder is level;

[0076] Step 7: testing the lateral stiffness, longitudinal stiffness and torsional stiffness of the test piece respectively, that is, applying horizontal forces in different directions through the electric cylinder to displace the force measuring platform 8 until the horizontal force on the aircraft tire 11 reaches the specified value of the test;

[0077] Step 8: Turn off the data acquisition system and the test is completed;

[0078] Step 9: Start the electric cylinder and release the horizontal force until the horizontal force is zero;

[0079] Step 10: Disconnect the electric cylinder from the force measuring platform;

[0080] Step 11: The force measuring platform descends and the vertical force is released until the force measuring platform is no longer in contact with the aircraft tire;

[0081] Step 12: The overall test is completed, check and organize the data.

[0082] 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 stiffness test device, characterized in that: It comprises a test bench (3), a force measuring platform (8), a test piece, a flange (10), a load-bearing wall, a vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism, and a torsional force loading mechanism; The load-bearing wall comprises a first load-bearing wall (12) and a second load-bearing wall (13) which are installed on the test bench and arranged relative to each other, and a flange (10) for fixing the test piece is fixedly installed between the first load-bearing wall (12) and the second load-bearing wall (13); The force measuring platform (8) is horizontally placed between a first load-bearing wall (12) and a second load-bearing wall (13), and is located below the test piece. A vertical force loading mechanism, a lateral force loading mechanism, a longitudinal force loading mechanism, and a torsional force loading mechanism are used to apply vertical force, lateral force, longitudinal force, and torsional force to the force measuring platform (8), respectively.

2. The aircraft tire stiffness test device according to claim 1, characterized in that: Also includes a load-bearing frame (1); The load-bearing frame (1) is fixedly mounted on the test bench (3); the vertical force loading mechanism is mounted between the top of the load-bearing frame (1) 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; A plurality of groups of cross beams (21) and brackets (22) are fixedly installed around the load-bearing frame (1); a height-adjustable horizontal power source is installed on the bracket (22); the horizontal power source is arranged horizontally, its outer end is installed on the bracket (22), and its inner end is installed on the force measuring platform (8); the plurality of horizontal power sources are divided into a longitudinal power source perpendicular to the axis of the test piece and a lateral power source parallel to the axis of the test piece; The longitudinal force loading mechanism comprises a longitudinal power source, which drives the force measuring platform (8) to translate longitudinally; The lateral force loading mechanism comprises a lateral power source located on one side of the test piece, and the lateral power source drives the force measuring platform (8) to translate in a lateral direction; The torsion force loading mechanism comprises two lateral power sources located at two sides of the test piece and having different axes, and the force measuring platform (8) is driven to twist in the horizontal direction through the two lateral power sources.

3. The aircraft tire stiffness 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 (2), a suspension rod (7), a vertical force sensor (6) and a suspension ring (9); The housing of the servo actuator (2) is fixedly mounted on the top of the load-bearing frame (1), the output rod of the servo actuator (2) 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).

4. The aircraft tire stiffness 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 stiffness test device according to claim 2, characterized in that: The horizontal power source comprises an electric cylinder and a horizontal force sensor (20); the outer end of the electric cylinder is connected to a pair of detachably connected clamping blocks (23), and the pair of clamping blocks (23) clamp the bracket (22); the inner end of the electric cylinder is connected to the force measuring platform (8) via the horizontal force sensor (20).

6. The aircraft tire stiffness test device according to claim 2, characterized in that: The horizontal power source around the force measuring platform (8) is divided into a first longitudinal electric cylinder (14), a second longitudinal electric cylinder (15), a first lateral and torsional electric cylinder (16), a second lateral electric cylinder (17) and a second torsional electric cylinder (18). The first longitudinal electric cylinder (14) and the second longitudinal electric cylinder (15) are arranged in parallel in the longitudinal direction perpendicular to the axis of the test piece. The first lateral and torsional electric cylinder (16) and the second lateral electric cylinder (17) are arranged in parallel in the lateral direction parallel to the axis of the test piece. The second torsional electric cylinder (18) is also arranged in the lateral direction parallel to the axis of the test piece. The first lateral and torsional electric cylinder (16) and the second torsional electric cylinder (18) are respectively located on both sides of the test piece, and the axes of the two are different.

7. A test method for the aircraft tire stiffness test device according to claim 1, characterized in that: The steps include: Step 1: measuring the air pressure of the aircraft tire (11) to ensure that the air pressure of the aircraft tire (11) meets the test requirements; Step 2: Install the aircraft tire (11) according to the test device, ensure that the force measuring platform (8) is level, and the vertical loads applied by each servo actuator (2) remain the same; Step 3: Start the servo actuator (2) to lift the force measuring platform (8) so that the force measuring platform (8) contacts the aircraft tire (11); Step 4: Start the data acquisition system, clear and collect data; Step 5: Continue to lift the force measuring platform (8) so that the vertical load on the aircraft tire (11) reaches the specified value of the test, and the vertical stiffness test is completed; Step 6: Keep the vertical load specified in the test unchanged, adjust the height position of the electric cylinder to ensure that the electric cylinder is level; Step 7: testing the lateral stiffness, longitudinal stiffness and torsional stiffness of the test piece respectively, i.e. applying horizontal forces in different directions respectively through the electric cylinder to displace the force measuring platform (8) until the horizontal force on the aircraft tire (11) reaches the specified value of the test; Step 8: Turn off the data acquisition system and the test is completed; Step 9: Start the electric cylinder and release the horizontal force until the horizontal force is zero; Step 10: Disconnect the electric cylinder from the force measuring platform; Step 11: The force measuring platform descends and the vertical force is released until the force measuring platform is no longer in contact with the aircraft tire; Step 12: The overall test is completed, check and organize the data.

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