Testing device and testing method of airplane main wheel turning system

Abstract

The invention discloses a testing device and a testing method for an aircraft main wheel turning system. The aircraft main wheel turning system comprises a turning system crank, a turning actuation system, a turning system connecting rod and a turning shaft and is mounted on the test device, and one end of the turning system crank is fixedly connected with a bracket connecting piece of the turning system bracket; the upper end of the turning actuation system is hinged with the other end of the turning system crank; a connecting rod connecting piece at the upper end of a turning system connecting rod is hinged to the third end of a turning system crank, loading points are additionally arranged on the two sides away from the rotation center of a turning shaft, clockwise rotation loading and anticlockwise rotation loading of a main wheel turning system are achieved by switching the loading points, and the loading mode of a conventional loading test bed is expanded. The maximum pressure and the tension locking force of the aircraft main wheel turning system and the turning rate of the aircraft main wheel turning system can be tested, the test requirements of the aircraft main wheel turning system are met, and safe, reliable and efficient work of the aircraft main wheel turning system is guaranteed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft design, in particular to a device capable of testing the locking force and loaded turning rate of an aircraft main wheel turning system and a related testing method. Background Art

[0002] The aircraft main wheel turning system can provide lateral force for the aircraft's turning to reduce the aircraft's ground turning radius and reduce the wear of the aircraft's tires. The locking function of the aircraft's main wheel turning system can ensure that the aircraft's main wheels will not turn when the main wheel turning system is not working, thereby preventing the aircraft from yaw. In addition, the turning rate of the aircraft's main wheel turning system needs to match the turning rate of the nose wheel turning system to improve the aircraft's turning efficiency. Therefore, after the aircraft's main wheel turning system is designed, it is necessary to conduct relevant tests on the locking force and load turning rate of the aircraft's main wheel turning system to ensure that the aircraft's main wheel turning system can work safely, reliably and efficiently.

[0003] After searching, it was found that a device for measuring the ground control torque of main wheel turning was proposed in the invention with the publication number of CN110470464A, which is characterized by comprising a support base, a torque sensor is vertically mounted on the support base, a ground simulation platform is horizontally mounted on the top of the support base through a slewing bearing, the torque sensor is connected to the ground simulation platform through a torque pin, and the support base is fixedly connected to the inner ring of the slewing bearing, and the ground simulation platform is fixedly connected to the outer ring of the slewing bearing, so that the ground simulation platform can rotate relative to the support base. This invention can accurately measure the torsional torque under the coupling of many influencing factors such as different load distribution, tire pressure and tire-ground relative friction, solves the limitation of torque measurement by force sensor, and reduces the influence of additional factors such as transmission and friction loss on the test results. However, this invention can only be used to measure the ground control torque of main wheel turning, and cannot measure the maximum locking torque of the aircraft main wheel turning system, nor can it accurately measure the turning speed under the set torque. Summary of the invention

[0004] In order to overcome the deficiency of the prior art that it is impossible to accurately test the main wheel turning locking force and turning rate, the present invention proposes a test device and a test method for an aircraft main wheel turning system.

[0005] The test device of the aircraft main wheel turning system proposed by the present invention comprises a test bench upper computer, a test bench fixing bracket, a turning system bracket, a hydraulic cylinder, a test bench loading platform, an oil inlet pipeline, an oil return pipeline, a hydraulic source and a control system upper computer;

[0006] The test bench host computer is connected to the hydraulic cylinder through the test bench cable; the hydraulic cylinder is mechanically connected to the test bench loading platform, and the required load is set by the test bench host computer, the displacement of the hydraulic cylinder is controlled, and the test bench loading platform is further controlled to move upward to load the test load. The maximum load that the test bench can load is F max The hydraulic cylinder stroke measured by the displacement sensor in the hydraulic cylinder is returned to the test bench host computer through the test bench cable.

[0007] The turning system bracket is installed at the lower end of the test bench fixed bracket. The turning shaft is installed on the turning system bracket through bolts at the center of rotation. The wheels are installed at both ends of the turning shaft and the two are rotated together. The turning shaft is equipped with a hinge joint, which is hinged to the hinged ear piece on the test bench loading platform and makes the turning shaft rotate clockwise / counterclockwise. The maximum angle of its one-way rotation is β max The horizontal distance between the hinge head and the turning axis rotation center is L,

[0008] The connection between the hinged ear and the hinged head forms a variable loading point of the turning shaft; the loading point is installed on one side of the rotation center of the turning shaft according to the test requirements of the turning shaft rotating clockwise or counterclockwise, forming a first loading point or a second loading point.

[0009] When the maximum load moment of the main wheel turning system to be tested is M max , then L satisfies the following formula:

[0010]

[0011] The rotation center coincides with the center of the hinge between the turning system bracket and the turning shaft.

[0012] The aircraft main wheel turning system comprises a turning system crank, a turning actuation system, a turning system connecting rod and a turning shaft. The aircraft main wheel turning system is installed on a test device, and one end of the turning system crank is fixedly connected to a bracket connecting piece of a turning system bracket; the upper end of the turning actuation system is hinged to the other end of the turning system crank; and the connecting rod connecting piece at the upper end of the turning system connecting rod is hinged to the third end of the turning system crank.

[0013] The oil outlet of the hydraulic source is mechanically connected to the oil inlet of the turning actuation system through an oil inlet pipeline, and the oil return port of the hydraulic source is mechanically connected to the oil return port of the turning actuation system through an oil return pipeline.

[0014] The control system host computer is electrically connected to the turning actuation system through a control cable. The control system host computer sets a turning instruction to control the turning actuation system to extend and retract, thereby realizing the clockwise and counterclockwise turning of the aircraft main wheel turning system. At the same time, the turning actuation system is equipped with a displacement sensor, and the measured displacement information is returned to the control system host computer through the control cable.

[0015] The test using the test device proposed in the present invention includes testing the locking force of the aircraft main wheel turning system and obtaining the load turning rate of the aircraft main wheel turning system; the specific process is:

[0016] ⅠTest the locking force of the aircraft main wheel turning system:

[0017] The locking force of the aircraft main wheel turning system includes a maximum pressure locking force F1 and a maximum tension locking force F2.

[0018] iTest of the maximum pressure locking force

[0019] Step 1: Set the test parameters

[0020] The test parameters include the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint and the rotation center of the turning axis, and the initial angle between the turning actuation system and the turning axis.

[0021] The load moment M1 that the aircraft main wheel turning system needs to bear is set, and the horizontal distance between the hinge joint and the rotation center of the turning axis is L. The initial angle between the turning actuation system and the turning axis is α.

[0022] Step 2: Install the first mount point

[0023] The first loading point formed by the hinge head and the hinge ear is located on the side close to the hydraulic source.

[0024] The center distance between the first loading point and the turning axis rotation center is L=0.5m,

[0025] Step 3: Loading test

[0026] When testing the maximum pressure locking force of the aircraft main wheel turning system, the test bench host computer sets a loading instruction with a loading force of F1, controls the hydraulic cylinder to output the loading force F1 through the test bench cable, and maintains the loading force F1 for T hours.

[0027] The displacement of the turning actuation system is obtained through a displacement sensor in the turning actuation system.

[0028] If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F1 exceeds the limit capacity of the turning actuation system 13. Reduce the load force F1 by 10% and return to step 2 to reload. Until the displacement measured by the turning actuation system is ≤ 0;

[0029] If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded. The load force applied by the current test bench is the maximum pressure locking force.

[0030] ⅱTest of maximum tensile locking force

[0031] Step 1, setting the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint and the turning axis rotation center, and the initial angle between the turning actuation system and the turning axis. When testing the maximum tension locking force, the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint and the turning axis rotation center, and the initial angle between the turning actuation system and the turning axis are the same as the parameters for testing the maximum pressure locking force.

[0032] Step 2: Install the second loading point

[0033] The hinged joint forming the first loading point is removed and installed at a symmetrical position on the other side of the rotation center of the turning shaft to form a second loading point; the second loading point is located close to the host computer side of the test bench; the center distance between the second loading point and the rotation center of the turning shaft is L = 0.5m.

[0034] Step 3: Loading test

[0035] The loading force F2 is set as a loading instruction by the host computer of the test bench, and the loading force F2 is controlled by the test bench cable to output the hydraulic cylinder, maintaining the current loading force F2 and continuously outputting it for T hours.

[0036] The displacement of the turning actuation system is obtained through a displacement sensor in the turning actuation system.

[0037] If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F2 exceeds the limit capacity of the turning actuation system. Reduce the load force F2 by 10% and return to step 2 to reload until the displacement is ≤ 0;

[0038] If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded; the load force applied by the current test bench is the maximum tensile locking force.

[0039] At this point, the test of the pressure locking force and the tension locking force of the aircraft brake system is completed, and the maximum pressure locking force and the maximum tension locking force of the aircraft brake system are obtained.

[0040] Ⅱ Obtaining the load turning rate of the aircraft main wheel turning system

[0041] The load turning rate of the aircraft main wheel turning system includes the aircraft brake system clockwise turning rate V1 and the aircraft brake system counterclockwise turning rate V2.

[0042] According to the designed test outline, the rotation direction of the aircraft main wheel turning system is selected as clockwise or counterclockwise. When the rotation direction of the aircraft main wheel turning system is clockwise, the clockwise turning rate is obtained; otherwise, the counterclockwise turning rate is obtained.

[0043] If you choose to test the clockwise turning rate of the aircraft's main wheel turning system, go to step i;

[0044] If you choose to test the counterclockwise turning rate of the aircraft's main wheel turning system, go to step ii;

[0045] i obtains the clockwise turning rate of the aircraft braking system. The specific process is:

[0046] Step 1: Set the test parameters

[0047] The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance between the hinge joint and the rotation center of the turning axis.

[0048] When obtaining the clockwise turning rate of the aircraft brake system, the load moment M2 that the aircraft main wheel turning system needs to bear is set; and the horizontal distance L between the hinge joint and the rotation center of the turning axis is set to be 0.5m.

[0049] Step 2, install the first load point:

[0050] The first loading point formed by the hinged head and the hinged ear is located close to the hydraulic source. The center distance between the first loading point and the turning center of the turning shaft is L;

[0051] Step 3, loading test:

[0052] The host computer of the test bench sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder to output the loading force F3 through the test bench cable.

[0053] The control system host computer issues a command to the turning actuation system 13 to rotate the turning shaft clockwise; the turning shaft rotation angle is β1. The rotation angle β1≤β max .

[0054] The aircraft main wheel turning system rotates clockwise; the test bench host computer records the displacement Z1 measured by the displacement sensor in the hydraulic cylinder.

[0055] Step 4, determine the aircraft braking system clockwise turning rate V1:

[0056] According to the displacement Z1 measured by the displacement sensor in the hydraulic cylinder, the formula β m1 =arcsin(Z1 / L) to get the clockwise turning angle β of the aircraft braking system m1 The curve that changes with time is used to calculate the clockwise turning rate of the aircraft. By the formula V1 = Δβ m1 / Δt1 to obtain the clockwise turning rate of the aircraft braking system; where V1 is the clockwise turning rate; Δβ m1 It is the change in the turning angle in a period of time Δt1 when turning clockwise.

[0057] ⅱGet the counterclockwise turning rate of the aircraft braking system. The specific process is:

[0058] Step 1: Set the test parameters

[0059] The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance between the hinge joint and the turning axis rotation center. The set test parameters are the same as the test parameters for obtaining the clockwise turning rate of the aircraft brake system.

[0060] Step 2, install the second loading point:

[0061] The second loading point formed by the hinged head and the hinged ear piece is located near the side of the test bench host computer 1. The center distance between the second loading point and the turning axis rotation center is L = 0.5m,

[0062] Step 3, loading test:

[0063] The host computer of the test bench sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder to output the loading force F3 through the test bench cable.

[0064] The control system host computer sends a command to the turning actuation system to rotate the turning axis counterclockwise; the turning axis rotation angle is β2. The rotation angle must satisfy β2≤β max .

[0065] The aircraft main wheel turning system rotates counterclockwise; the test bench host computer records the displacement Z2 measured by the displacement sensor in the hydraulic cylinder.

[0066] Step 4, determine the aircraft braking system counterclockwise turning rate V2:

[0067] According to the displacement Z2 measured by the displacement sensor in the hydraulic cylinder, the formula β m2 =arcsin(Z2 / L) to get the counterclockwise turning angle β of the aircraft braking system m2 The time-varying curve is used to calculate the aircraft's counterclockwise turning rate. m2 / Δt2 is the counterclockwise turning rate of the aircraft braking system; where V2 is the counterclockwise turning rate; Δβ m2 It is the change of the turning angle in a period of time Δt2 when turning counterclockwise.

[0068] At this point, the test of the clockwise turning rate and the counterclockwise turning rate of the loaded aircraft brake system is completed, and the clockwise turning rate V1 of the aircraft brake system and the counterclockwise turning rate V2 of the aircraft brake system are obtained.

[0069] Based on the test device and the test method, the present invention can accurately measure the locking force of the main wheel turning system and the turning rate of the main wheel turning system of the aircraft under different set loads.

[0070] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0071] The present invention provides a test device for an aircraft main wheel turning system, a method capable of accurately measuring the locking force of an aircraft main wheel turning system, and a method capable of testing the turning rate of an aircraft main wheel turning system under different loads.

[0072] The proposed test device for the aircraft main wheel turning system only needs to add loading points on the conventional loading test bench, and by switching the added loading points, the clockwise rotation loading and counterclockwise rotation loading of the main wheel turning system can be realized, thereby expanding the loading method of the conventional loading test bench.

[0073] The present invention adds loading points at L on both sides of the turning axis rotation center. The distance L is calculated by formula (1) according to different test requirements. The proposed aircraft main wheel turning system locking force test method can be Figure 2 The process shown in the figure tests the maximum pressure and tension locking force of the aircraft main wheel turning system. The test results of the proposed aircraft main wheel turning system turning rate test method are as follows: Figure 8 As shown, the main wheel turning system rotates 8° within 2 seconds, and the turning rate is 4° / s. It can be seen that the test device and test method of the aircraft main wheel turning system proposed in the present invention can meet the requirements of the aircraft main wheel turning system locking force and load turning rate related tests to ensure the safe, reliable and efficient operation of the aircraft main wheel turning system. BRIEF DESCRIPTION OF THE DRAWINGS

[0074] Figure 1 It is a structural schematic diagram of the present invention.

[0075] Figure 2 It is a test schematic diagram of the pressure locking force test method of the aircraft main wheel turning system.

[0076] Figure 3 It is a test schematic diagram of the tension locking force test method of the aircraft main wheel turning system.

[0077] Figure 4 It is a schematic diagram of the clockwise turning rate test of the aircraft main wheel turning system under load.

[0078] Figure 5 It is a schematic diagram of the aircraft main wheel turning system's loaded counterclockwise turning rate test.

[0079] Figure 6 It is a schematic diagram of the turning rate test effect of the aircraft main wheel turning system.

[0080] Figure 7 It is a schematic diagram of the locking force test method of the aircraft main wheel turning system.

[0081] Figure 8 It is a schematic diagram of the turning rate test method of the aircraft main wheel turning system.

[0082] In the figure: 1. Test bench host computer; 2. Test bench fixing bracket; 3. Upper fixing bolt; 4. Turning system bracket; 5. Turning shaft; 6. Wheel; 7. Articulated head; 8. Lower fixing bolt; 9. Hydraulic cylinder; 10. Test bench loading platform; 11. Test bench cable; 12. Turning system crank; 13. Turning actuation system; 14. Turning system connecting rod; 15. Oil inlet pipeline; 16. Oil return pipeline; 17. Hydraulic source; 18. Control system host computer; 19. Control cable; 20. Turning angle setting value; 21. Turning angle measurement value. DETAILED DESCRIPTION

[0083] This embodiment is a device capable of testing the locking force and load turning rate of the aircraft main wheel turning system.

[0084] The test device for the aircraft main wheel turning system proposed in the present invention includes a test bench host computer 1, a test bench fixing bracket, a turning system bracket 4, a hydraulic cylinder 9, a test bench loading platform 10, an oil inlet pipeline 15, an oil return pipeline 16, a hydraulic source 17 and a control system host computer 18.

[0085] The aircraft main wheel turning system comprises a turning system crank 12 , a turning actuation system 13 , a turning system connecting rod 14 and a turning shaft 5 .

[0086] The test bench host computer 1 is connected to the hydraulic cylinder 9 through the test bench cable 11; the hydraulic cylinder 9 is mechanically connected to the test bench loading platform 10, and the required load is set through the test bench host computer 1, the displacement of the hydraulic cylinder 9 is controlled, and the test bench loading platform 10 is further controlled to move upward to load the test load. The maximum load that the test bench can load is F max The hydraulic cylinder stroke measured by the displacement sensor in the hydraulic cylinder 9 is returned to the test bench host computer 1 through the test bench cable 11.

[0087] The turning system bracket 4 is mounted on the lower end of the test bench fixing bracket 2 by means of the upper fixing bolts 3. The turning shaft 5 is mounted on the turning system bracket 4 by means of the bolts at the center of rotation. The wheels 6 are mounted on both ends of the turning shaft 5 and are rotated in coordination with each other. The turning shaft 5 is provided with an articulated joint 7, which is articulated with the articulated lug 8 on the test bench loading platform 10 and enables the turning shaft 5 to rotate clockwise / counterclockwise, and the maximum angle of its one-way rotation is β max The horizontal distance between the hinge head 7 and the turning axis 5 is L,

[0088] The connection between the hinged ear piece 8 and the hinged head 7 forms a variable loading point of the turning shaft 5; the loading point is installed on one side of the rotation center of the turning shaft 5 according to the test requirements of the turning shaft 5 rotating clockwise or counterclockwise, forming a first loading point or a second loading point.

[0089] When the maximum load moment of the main wheel turning system to be tested is M max , then L satisfies the following formula:

[0090]

[0091] The rotation center coincides with the center of the hinge between the turning system bracket 4 and the turning shaft 5 .

[0092] The aircraft main wheel turning system is installed on the test device, and one end of the turning system crank 12 is fixedly connected to the bracket connector of the turning system bracket 4; the upper end of the turning actuation system 13 is hinged to the other end of the turning system crank; the connecting rod connector at the upper end of the turning system connecting rod 14 is hinged to the third end of the turning system crank.

[0093] The oil outlet of the hydraulic source 17 is mechanically connected to the oil inlet of the turning actuation system 13 via an oil inlet pipeline 15 , and the oil return port of the hydraulic source 17 is mechanically connected to the oil return port of the turning actuation system 13 via an oil return pipeline 16 .

[0094] The control system host computer 18 is electrically connected to the turning actuation system 13 through a control cable 19. The control system host computer 18 sets a turning instruction to control the turning actuation system 13 to extend and retract, thereby realizing the clockwise and counterclockwise turning of the aircraft main wheel turning system. At the same time, the turning actuation system 13 is equipped with a displacement sensor for measurement, and the measured displacement information is returned to the control system host computer 12 through the control cable 19.

[0095] The test using the test device proposed in the present invention includes testing the locking force of the aircraft main wheel turning system and obtaining the load turning rate of the aircraft main wheel turning system; the specific process is:

[0096] ⅠTest the locking force of the aircraft main wheel turning system:

[0097] The locking force of the aircraft main wheel turning system includes a maximum pressure locking force F1 and a maximum tension locking force F2.

[0098] iTest of the maximum pressure locking force

[0099] Step 1: Set the test parameters

[0100] The test parameters include the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the articulated joint 7 and the rotation center of the turning axis 5 , and the initial angle α between the turning actuation system 13 and the turning axis 5 .

[0101] The load moment M1 that the aircraft main wheel turning system needs to bear is set, and the horizontal distance between the hinge joint and the rotation center of the turning axis is L. The initial angle between the turning actuation system and the turning axis is α.

[0102] The load moment M1 required by the aircraft main wheel turning system is set to be 50000 N.m, and the horizontal distance between the articulated joint 7 and the rotation center of the turning shaft 5 is L. In this embodiment, L = 0.5m, and the load force F1 of the hydraulic cylinder 9 is obtained by the formula F1 = M1 / L = 100 KN. The initial angle between the turning actuation system 13 and the turning shaft 5 is α = 60°.

[0103] Step 2: Install the mount point location

[0104] The first loading point formed by the hinged head 7 and the hinged lug 8 is located close to the hydraulic source 17 .

[0105] When testing the maximum pressure locking force of the aircraft main wheel turning system, the center distance between the first loading point and the rotation center of the turning shaft 5 is L=0.5m.

[0106] Step 3: Loading test

[0107] When testing the maximum pressure locking force of the aircraft main wheel turning system, the test bench host computer sets a loading instruction with a loading force of F1, and controls the hydraulic cylinder 9 to output the loading force F1 through the test bench cable 11, and maintains the loading force F1 for T hours. In this embodiment, T = 0.5 hours.

[0108] The displacement of the turning actuation system is obtained by the displacement sensor in the turning actuation system

[0109] If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F1 exceeds the limit capacity of the turning actuation system 13. Reduce the load force F1 by 10% and return to step 2 to reload. Until the displacement measured by the turning actuation system is ≤ 0;

[0110] If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded. The load force applied by the current test bench is the maximum pressure locking force.

[0111] ⅱTest of maximum tensile locking force

[0112] Step 1, setting the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint 7 and the rotation center of the turning shaft 5, and the initial angle between the turning actuation system 13 and the turning shaft 5. When testing the maximum tension locking force, the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint 7 and the rotation center of the turning shaft 5, and the initial angle between the turning actuation system 13 and the turning shaft 5 are the same as the parameters for testing the maximum pressure locking force.

[0113] Step 2: Install the second loading point

[0114] The hinged head 7 forming the first loading point is removed and installed to a symmetrical position on the other side of the rotation center of the turning shaft 5 to form a second loading point; the second loading point is located close to the side of the test bench host computer 1; the center distance between the second loading point and the rotation center of the turning shaft 5 is L = 0.5m.

[0115] Step 3: Loading test

[0116] The test bench host computer 1 sets a loading instruction with a loading force of F2 and controls the hydraulic cylinder 9 to output the loading force F2 through the test bench cable 11, maintaining the current loading force F2 and continuously outputting it for T hours.

[0117] The displacement of the turning actuation system is obtained through a displacement sensor in the turning actuation system.

[0118] If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F2 exceeds the limit capacity of the turning actuation system 13. Reduce the load force F2 by 10% and return to step 2 to reload until the displacement is less than or equal to 0;

[0119] If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded; the load force applied by the current test bench is the maximum tensile locking force.

[0120] At this point, the test of the pressure locking force and the tension locking force of the aircraft brake system is completed, and the maximum pressure locking force and the maximum tension locking force of the aircraft brake system are obtained.

[0121] If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded and the process goes to step 4. The load force applied by the current test bench is the maximum pressure locking force.

[0122] In this embodiment, F1=100KN, and the maximum pressure locking force is F1 / sinα=115.47KN.

[0123] At this point, the test of the pressure locking force and the tension locking force of the aircraft brake system is completed, and the maximum pressure locking force and the maximum tension locking force of the aircraft brake system are obtained.

[0124] Ⅱ Obtaining the load turning rate of the aircraft main wheel turning system

[0125] The load turning rate of the aircraft main wheel turning system includes the clockwise turning rate V1 of the aircraft braking system and the counterclockwise turning rate of the aircraft braking system.

[0126] According to the designed test outline, the rotation direction of the aircraft main wheel turning system is selected as clockwise or counterclockwise. When the rotation direction of the aircraft main wheel turning system is clockwise, the clockwise turning rate is obtained; otherwise, the counterclockwise turning rate is obtained.

[0127] If you choose to test the clockwise turning rate of the aircraft's main wheel turning system, go to step i;

[0128] If you choose to test the counterclockwise turning rate of the aircraft's main wheel turning system, go to step ii;

[0129] i obtains the clockwise turning rate of the aircraft braking system. The specific process is:

[0130] Step 1: Set the test parameters

[0131] The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance L between the rotation center of the articulated joint 7 and the turning shaft 5 .

[0132] When obtaining the clockwise turning rate of the aircraft brake system, the load moment M2 that the aircraft main wheel turning system needs to bear is set to be 10000 N.m; and the horizontal distance L between the hinge joint 7 and the rotation center of the turning shaft 5 is set to be 0.5 m.

[0133] The load force of the hydraulic cylinder 9 is obtained by the formula F=M2 / L as F=20KN.

[0134] Step 2, install the first load point:

[0135] The first loading point formed by the hinged head 7 and the hinged ear piece 8 is located close to the hydraulic source 17. The center distance between the first loading point and the rotation center of the turning shaft 5 is L;

[0136] Step 3, loading test:

[0137] The test bench host computer 1 sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder 9 to output the loading force F3 through the test bench cable 11.

[0138] The control system host computer sends a command to the turning actuation system 13 to rotate the turning axis clockwise; when the aircraft brake system turns clockwise, the turning axis rotates at an angle of β1. The rotation angle β1≤β max In this embodiment, β1 = 8°.

[0139] The aircraft main wheel turning system rotates clockwise; the test bench host computer 1 records the displacement Z1 measured by the displacement sensor in the hydraulic cylinder 9.

[0140] Step 4, determine the aircraft braking system clockwise turning rate V1:

[0141] According to the displacement Z1 measured by the displacement sensor in the hydraulic cylinder 9, the formula β m1 =arcsin(Z1 / L) to get the clockwise turning angle β of the aircraft braking system m1 The curve that changes with time is used to calculate the clockwise turning rate of the aircraft. By the formula V1 = Δβ m1 / Δt1 to obtain the clockwise turning rate of the aircraft braking system; where V1 is the clockwise turning rate; Δβ m1 It is the change in the turning angle in a period of time Δt1 when turning clockwise.

[0142] In this embodiment, the clockwise turning rate V1 = Δβ m1 / Δt1=4° / s.

[0143] ⅱGet the counterclockwise turning rate of the aircraft braking system. The specific process is:

[0144] Step 1: Set the test parameters

[0145] The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance between the rotation center of the articulated joint 7 and the turning axis 5. The set test parameters are the same as the test parameters for obtaining the clockwise turning rate of the aircraft brake system.

[0146] Step 2, install the second loading point:

[0147] The second loading point formed by the hinged head 7 and the hinged ear piece 8 is located close to the test bench host computer 1. The center distance between the second loading point and the rotation center of the turning shaft 5 is L=0.5m.

[0148] Step 3, loading test:

[0149] The test bench host computer 1 sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder 9 to output the loading force F3 through the test bench cable 11.

[0150] The control system host computer 18 sends a counterclockwise rotation command to the turning actuation system 13; the turning angle of the turning axis when the aircraft brake system turns counterclockwise is β 2； The rotation angle β2≤β max In this embodiment, β2 = 8°

[0151] The aircraft main wheel turning system rotates counterclockwise; the test bench host computer 1 records the displacement Z2 measured by the displacement sensor in the hydraulic cylinder 9

[0152] Step 4, determine the aircraft braking system counterclockwise turning rate V2:

[0153] According to the displacement Z2 measured by the displacement sensor in the hydraulic cylinder 9, the formula β m2 =arcsin(Z2 / L) to get the counterclockwise turning angle β of the aircraft braking system m2 The curve that changes with time is used to calculate the aircraft's counterclockwise turning rate. The formula V2 = Δβ m2 / Δt2 is the counterclockwise turning rate of the aircraft braking system; where V2 is the counterclockwise turning rate; Δβ m2 It is the change of the turning angle in a period of time Δt2 when turning counterclockwise.

[0154] In this embodiment, the counterclockwise turning rate V2 = Δβ m2 / Δt2=4° / s.

[0155] At this point, the test of the clockwise turning rate and the counterclockwise turning rate of the loaded aircraft brake system is completed, and the clockwise turning rate V1 of the aircraft brake system and the counterclockwise turning rate V2 of the aircraft brake system are obtained.

Claims

1. A test device for an aircraft main wheel turning system, characterized in that: It comprises a test bench upper computer (1), a test bench fixing bracket, a turning system bracket (4), a hydraulic cylinder (9), a test bench loading platform (10), an oil inlet pipeline (15), an oil return pipeline (16), a hydraulic source (17) and a control system upper computer (18); The test bench host computer (1) is connected to the hydraulic cylinder via a test bench cable (11); the hydraulic cylinder is mechanically connected to the test bench loading platform (10); the required load is set via the test bench host computer (1), the displacement of the hydraulic cylinder is controlled, and the test bench loading platform is further controlled to move upward to achieve the loading of the test load; the maximum load that can be loaded on the test bench is F max The hydraulic cylinder stroke measured by the displacement sensor in the hydraulic cylinder (9) is returned to the test bench host computer (1) through the test bench cable (11); The turning system bracket (4) is installed at the lower end of the test bench fixed bracket; the turning shaft (5) is installed on the turning system bracket (4) through bolts at the rotation center; the wheels (6) are installed at both ends of the turning shaft, and the two are rotatably matched; the turning shaft is provided with a hinge joint (7), which is hinged to the hinge ear piece (8) on the test bench loading platform (10), and the turning shaft is rotated clockwise / counterclockwise, and the maximum angle of unidirectional rotation is β max ; The horizontal distance between the hinged head and the rotation center of the turning shaft is L, and the connection between the hinged ear piece (8) and the hinged head forms a variable loading point of the turning shaft; the loading point is installed on one side of the rotation center of the turning shaft (5) according to the test requirements of the turning shaft rotating clockwise or counterclockwise, forming a first loading point or a second loading point; When the maximum load moment of the main wheel turning system to be tested is M max , then L satisfies the following formula: The rotation center coincides with the center of the hinge between the turning system bracket (4) and the turning shaft (5).

2. The test device for the aircraft main wheel turning system as claimed in claim 1, characterized in that: The aircraft main wheel turning system comprises a turning system crank (12), a turning actuation system (13), a turning system connecting rod (14) and a turning shaft (5); the aircraft main wheel turning system is installed on a test device, and one end of the turning system crank (12) is fixedly connected to a bracket connecting piece of a turning system bracket (4); the upper end of the turning actuation system is hinged to the other end of the turning system crank; the connecting rod connecting piece at the upper end of the turning system connecting rod is hinged to the third end of the turning system crank; The oil outlet of the hydraulic source (17) is mechanically connected to the oil inlet of the turning actuation system (13) through an oil inlet pipeline (15), and the oil return port of the hydraulic source is mechanically connected to the oil return port of the turning actuation system through an oil return pipeline (16); the control system host computer (18) is electrically connected to the turning actuation system through a control cable (19); a turning instruction is set by the control system host computer to control the turning actuation system to extend and retract, thereby realizing clockwise and counterclockwise turning of the aircraft main wheel turning system; at the same time, the turning actuation system is equipped with a displacement sensor, and the measured displacement information is returned to the control system host computer (12) through the control cable.

3. A test method using the test device according to claim 1, characterized in that: The test includes testing the locking force of the aircraft main wheel turning system and obtaining the load turning rate of the aircraft main wheel turning system; the specific process is: ⅠTest the locking force of the aircraft main wheel turning system: The locking force of the aircraft main wheel turning system includes a maximum pressure locking force and a maximum tension locking force; iTest of maximum pressure locking force: Step 1: Set the test parameters: The test parameters include the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint (7) and the rotation center of the turning shaft (5), and the initial angle between the turning actuation system (13) and the turning shaft (5); the load moment M1 that the aircraft main wheel turning system needs to bear is set, the horizontal distance between the hinge joint and the rotation center of the turning shaft is L; the initial angle between the turning actuation system and the turning shaft is α; Step 2: Install the first load point: The first loading point formed by the hinged head (7) and the hinged ear piece (8) is located on the side close to the hydraulic source (17); Step 3: Loading test: When testing the maximum pressure locking force of the aircraft main wheel turning system, the test bench host computer sets a loading instruction with a loading force of F1, and controls the hydraulic cylinder to output the loading force F1 through the test bench cable, and maintains the loading force F1 for T hours; The displacement of the turning actuation system is obtained by using a displacement sensor in the turning actuation system; If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F1 exceeds the limit capacity of the turning actuation system (13); reduce the load force F1 by 10%, and return to step 2 to reload; until the displacement measured by the turning actuation system is less than or equal to 0; If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded; the load force applied by the current test bench is the maximum pressure locking force; ⅱTest of maximum tensile locking force: Step 1: Set the test parameters: The load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint (7) and the rotation center of the turning shaft (5), and the initial angle between the turning actuation system (13) and the turning shaft are set; when testing the maximum tension locking force, the load moment that the aircraft main wheel turning system needs to bear, the horizontal distance between the hinge joint and the rotation center of the turning shaft, and the initial angle between the turning actuation system and the turning shaft are the same as the parameters for testing the maximum pressure locking force; Step 2, install the second loading point: The hinge joint (7) forming the first loading point is removed and installed at a symmetrical position on the other side of the rotation center of the turning shaft (5) to form a second loading point; the second loading point is located close to the side of the test bench host computer (1); the center distance between the second loading point and the rotation center of the turning shaft is L=0.5m; Step 3, loading test: A loading instruction with a loading force of F2 is set through the test bench host computer (1) and the hydraulic cylinder (9) is controlled to output the loading force F2 through the test bench cable (11), and the current loading force F2 is maintained and continuously output for T hours; The displacement of the turning actuation system is obtained by using a displacement sensor in the turning actuation system; If the displacement measured by the turning actuation system is greater than 0, it is considered that the currently set load force F2 exceeds the limit capacity of the turning actuation system (13); reduce the load force F2 by 10%, and return to step 2 to reload; until the displacement obtained is less than or equal to 0; If the displacement measured by the turning actuation system is ≤0, the load force applied by the current test bench is recorded; the load force applied by the current test bench is the maximum tensile locking force; At this point, the test of the pressure locking force and the tension locking force of the aircraft brake system is completed, and the maximum pressure locking force and the maximum tension locking force of the aircraft brake system are obtained; Ⅱ Obtain the load turning rate of the aircraft main wheel turning system: The load turning rate of the aircraft main wheel turning system includes the clockwise turning rate V1 of the aircraft braking system and the counterclockwise turning rate of the aircraft braking system; According to the designed test outline, the rotation direction of the aircraft main wheel turning system is selected as clockwise or counterclockwise; when the rotation direction of the aircraft main wheel turning system is clockwise, the clockwise turning rate is obtained; otherwise, the counterclockwise turning rate is obtained; If you choose to test the clockwise turning rate of the aircraft's main wheel turning system, go to step i; If you choose to test the counterclockwise turning rate of the aircraft's main wheel turning system, go to step ii; i Get the clockwise turning rate of the aircraft braking system. The specific process is: Step 1: Set the test parameters: The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance L between the rotation center of the hinge joint (7) and the turning shaft (5); Step 2, install the first load point: The first loading point formed by the hinged head (7) and the hinged ear piece (8) is located on a side close to the hydraulic source (17); the center distance between the first loading point and the rotation center of the turning shaft (5) is L; Step 3, loading test: The test bench host computer (1) sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder (9) to output the loading force F3 through the test bench cable (11); A command for causing the turning shaft to rotate clockwise is sent to the turning actuation system (13) through the control system host computer; When the aircraft brake system turns clockwise, the turning axis's rotation angle is β1; The aircraft main wheel turning system rotates clockwise; the test bench host computer (1) records the displacement Z1 measured by the displacement sensor in the hydraulic cylinder (9); Step 4, determine the aircraft braking system clockwise turning rate V1: According to the displacement Z1 measured by the displacement sensor in the hydraulic cylinder (9), the formula β m1 =arcsin(Z1 / L) to get the clockwise turning angle β of the aircraft braking system m1 The curve that changes with time is used to calculate the clockwise turning rate of the aircraft; through the formula V1 = Δβ m1 / Δt1 to obtain the clockwise turning rate of the aircraft braking system; where V1 is the clockwise turning rate; Δβ m1 It is the change of the turning angle in a period of time Δt1 when turning clockwise; ⅱ Obtain the counterclockwise turning rate of the aircraft braking system. The specific process is: Step 1: Set the test parameters: The test parameters include the load moment M2 that the aircraft main wheel turning system needs to bear and the horizontal distance between the rotation center of the hinge joint (7) and the turning axis (5); the set test parameters are the same as the test parameters when obtaining the clockwise turning rate of the aircraft brake system; Step 2, install the second loading point: The second loading point formed by the hinged head (7) and the hinged ear piece (8) is located close to the side of the test bench host machine (1); the center distance between the second loading point and the rotation center of the turning shaft (5) is L=0.5m, Step 3, loading test: The host computer of the test bench sets a loading instruction with a loading force of F3, and controls the hydraulic cylinder (9) to output the loading force F3 through the test bench cable (11); The control system host computer (18) sends a counterclockwise rotation instruction to the turning actuation system (13); when the aircraft brake system turns counterclockwise, the rotation angle of the turning axis is β 2； The rotation angle β2≤β max ; The aircraft main wheel turning system rotates counterclockwise; The test bench host computer (1) records the displacement Z2 measured by the displacement sensor in the hydraulic cylinder (9); Step 4, determine the aircraft braking system counterclockwise turning rate V2: According to the displacement Z2 measured by the displacement sensor in the hydraulic cylinder (9), the formula β m2 =arcsin(Z2 / L) to get the counterclockwise turning angle β of the aircraft braking system m2 The curve that changes with time is used to calculate the aircraft's counterclockwise turning rate; through the formula V2 = Δβ m2 / Δt2 is the counterclockwise turning rate of the aircraft braking system; where V2 is the counterclockwise turning rate; Δβ m2 It is the change of the turning angle in a period of time Δt2 when turning counterclockwise; At this point, the test of the clockwise turning rate and the counterclockwise turning rate of the loaded aircraft brake system is completed, and the clockwise turning rate V1 of the aircraft brake system and the counterclockwise turning rate V2 of the aircraft brake system are obtained.

4. A test method using the test device according to claim 3, characterized in that: The specific process is: in step 1 of testing the locking force of the aircraft main wheel turning system, the load moment M1 that the aircraft main wheel turning system needs to bear is set to 50000 N.m, the horizontal distance between the hinge joint (7) and the rotation center of the turning shaft (5) is L; the initial angle between the turning actuation system (13) and the turning shaft is α = 60°.

5. A test method using the test device according to claim 3, characterized in that: The specific process is: in step 2, the center distance between the first loading point and the rotation center of the turning axis is L=0.5m.

6. A test method using the test device according to claim 4, characterized in that: The specific process is: when obtaining the clockwise turning rate of the aircraft brake system, the load moment M2 that the aircraft main wheel turning system needs to bear is set to be 10000N.m; and the horizontal distance L between the hinge joint (7) and the rotation center of the turning shaft (5) is set to be 0.5m.

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