Test device and test method for aircraft main wheel turning system

Abstract

A test device and test method of an aircraft main wheel turning system. The aircraft main wheel turning system comprises a turning system crank, a turning actuating system, a turning system connecting rod and a turning shaft, which are installed on the test device, and one end of the turning system crank is fixedly connected with a support connecting piece of a turning system support; the upper end of the turning actuating system is hingedly connected with the other end of the turning system crank; the connecting rod connecting piece of the upper end of the turning system connecting rod is hingedly connected with the third end of the turning system crank, loading points are added on both sides of the turning center of the turning shaft, and clockwise rotation loading and counterclockwise rotation loading of the main wheel turning system are realized by switching the loading points, so that the loading mode of the conventional loading test bed is expanded. The maximum pressure and tension locking force of the aircraft main wheel turning system and the turning rate of the aircraft main wheel turning system can be tested by the aircraft main wheel turning system, the test requirements of the aircraft main wheel turning system are met, and the safe, reliable and efficient work of the aircraft main wheel turning system is ensured.

Description

TECHNICAL FIELD

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

[0002] The main wheel turning system of an aircraft can provide lateral force for the turning of the aircraft to reduce the turning radius of the aircraft on the ground and reduce the wear of the tires of the aircraft. The locking function of the main wheel turning system of the aircraft can ensure that the main wheel of the aircraft does not turn when the main wheel turning system of the aircraft is not working, thereby preventing the aircraft from deviating. In addition, the turning rate of the main wheel turning system of the aircraft needs to match the turning rate of the nose wheel turning system to improve the turning efficiency of the aircraft. Therefore, after the design of the main wheel turning system of the aircraft is completed, the locking force and the turning rate of the main wheel turning system of the aircraft need to be tested to ensure that the main wheel turning system of the aircraft can work safely, reliably and efficiently.

[0003] After searching, the invention with the publication number CN110470464A proposes a main wheel turning ground control moment measuring device, which is characterized by including a support base, a torque sensor vertically installed on the support base, a ground simulation platform horizontally installed on the top of the support base through a rotary bearing, the torque sensor and the ground simulation platform are connected through a torque pin, and the support base and the inner ring of the rotary bearing are fixedly connected, the ground simulation platform and the outer ring of the rotary bearing are fixedly connected, so that the ground simulation platform can rotate relative to the support base. The invention can accurately measure the torsional moment under the coupling of many influencing factors such as different load distribution, tire pressure and tire-ground relative friction, solves the limitations of force sensor torque measurement, and reduces the influence of additional factors such as transmission and friction loss on the test results. However, the invention can only be used to measure the main wheel turning ground control moment, cannot measure the maximum locking moment of the main wheel turning system of the aircraft, and cannot accurately measure the turning speed under the set moment. SUMMARY

[0004] In order to overcome the deficiency that the prior art cannot accurately test the locking force and the turning rate of the main wheel turning system, the present application proposes a testing device and a testing method for the main wheel turning system of an aircraft.

[0005] The testing device for the main wheel turning system of an aircraft proposed by the present application includes a test bench host computer, a test bench fixed support, a turning system support, a hydraulic cylinder, a test bench loading platform, an oil inlet pipeline, an oil return pipeline, a hydraulic source and a control system host computer.

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

[0007] The turning system support is installed at the lower end of the test bench fixed support. The turning shaft is installed on the turning system support through a bolt at the rotation center. The wheels are installed at both ends of the turning shaft and are rotationally connected between the two. A hinged joint is sleeved on the turning shaft, the hinged joint is hinged with a hinged ear on the test bench loading platform, and the turning shaft is rotated clockwise / counterclockwise, and the maximum angle of one-way rotation is β max ; the horizontal distance between the hinged joint and the rotation center of the turning shaft is L,

[0008] The connection between the hinged ear and the hinged joint 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 clockwise or counterclockwise rotation of the turning shaft, 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 , L satisfies the following formula:

[0010]

[0011] The rotation center coincides with the center of the hinged joint between the turning system support and the turning shaft.

[0012] The aircraft main wheel turning system includes 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 the test device, and one end of the turning system crank is fixedly connected with the support connector of the turning system support; the upper end of the turning actuation system is hinged with the other end of the turning system crank; the connecting rod connector at the upper end of the turning system connecting rod is hinged with the third end of the turning system crank.

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

[0014] The control system host computer is electrically connected with the turning actuating system through a control cable.

[0015] The test using the test device provided by the application includes testing the locking force of the airplane main wheel turning system and obtaining the turning speed of the airplane main wheel turning system under load; the specific process is as follows:

[0016] I. Testing the locking force of the airplane main wheel turning system

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

[0018] I. Testing the maximum pressure locking force

[0019] Step 1: Setting test parameters

[0020] The test parameters include the load moment required to be borne by the airplane main wheel turning system, the horizontal distance between the hinge joint and the turning shaft rotation center, and the initial included angle between the turning actuating system and the turning shaft.

[0021] The load moment required to be borne by the airplane main wheel turning system is set as M1, the horizontal distance between the hinge joint and the turning shaft rotation center is L, and the initial included angle between the turning actuating system and the turning shaft is α.

[0022] Step 2: Installing the first loading point

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

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

[0025] Step 3: Loading test

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

[0027] The displacement amount of the turning actuating system is obtained through the displacement sensor in the turning actuating system.

[0028] If the displacement measured by the turning actuation system is > 0, it is considered that the current 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, record the load force applied by the current test bench. The load force applied by the current test bench is the maximum pressure locking force.

[0030] ⅱTest of the maximum tensile locking force

[0031] Step 1, set the load moment required to be borne by the aircraft main wheel turning system, the horizontal distance between the hinge joint and the turning shaft rotation center, and the initial angle between the turning actuation system and the turning shaft. The load moment required to be borne by the aircraft main wheel turning system, the horizontal distance between the hinge joint and the turning shaft rotation center, and the initial angle between the turning actuation system and the turning shaft in the test of the maximum tensile locking force are the same as those in the test of the maximum pressure locking force.

[0032] Step 2, install the second loading point

[0033] Remove the hinge joint forming the first loading point and install it at a symmetrical position on the other side of the turning shaft rotation center to form the second loading point. The second loading point is located near the upper side of the test bench. The center distance between the second loading point and the turning shaft rotation center is L = 0.5 m.

[0034] Step 3, load test

[0035] Set the loading instruction of the loading force F2 through the upper machine of the test bench and output the loading force F2 through the test bench cable control hydraulic cylinder. Maintain the current loading force F2 and continuously output for T hours.

[0036] Obtain the displacement of the turning actuation system through the displacement sensor in the turning actuation system.

[0037] If the displacement measured by the turning actuation system is > 0, it is considered that the current 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 obtained is ≤ 0;

[0038] If the displacement measured by the turning actuation system is ≤ 0, record the load force applied by the current test bench. 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 tensile locking force of the aircraft brake system is completed, and the maximum pressure locking force and the maximum tensile locking force of the aircraft brake system are obtained.

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

[0041] The airplane main wheel turning system turning rate under load includes airplane brake system clockwise turning rate V1 and airplane brake system counterclockwise turning rate V2.

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

[0043] If the clockwise turning rate of the airplane main wheel turning system is selected to be tested, go to step i;

[0044] If the counterclockwise turning rate of the airplane main wheel turning system is selected to be tested, go to step ii;

[0045] iObtain the airplane brake system clockwise turning rate, and the specific process is

[0046] Step 1: Set test parameters

[0047] The test parameters include the load moment M2 required to be borne by the airplane main wheel turning system and the horizontal distance L between the hinge joint and the turning shaft rotation center.

[0048] When the airplane brake system clockwise turning rate is obtained, the load moment M2 required to be borne by the airplane main wheel turning system is set; the horizontal distance L between the hinge joint and the turning shaft rotation center is set as 0.5 m.

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

[0050] The first loading point formed by the hinge joint and the hinge ear is located close to the hydraulic source side. The center distance between the first loading point and the turning shaft rotation center is L;

[0051] Step 3, load test:

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

[0053] The host computer of the control system sends an instruction to the turning actuation system 13 to make the turning shaft turn clockwise; the turning angle of the turning shaft is β1. The turning angle β1≤β max .

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

[0055] Step 4, determine the airplane brake system clockwise turning rate V1:

[0056] Based on the displacement Z1 measured by the displacement sensor in the hydraulic cylinder, the formula β is used. m1 =arcsin(Z1 / L) gives the clockwise turning angle β of the aircraft braking system. m1 The curve that changes over time is used to calculate the aircraft's clockwise turn rate. This is achieved using the formula V1 = Δβ. m1 / Δt1 gives 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 over a time period Δt1 when turning clockwise.

[0057] ii. Obtaining the counter-clockwise turning rate of the aircraft braking system, the specific process is as follows:

[0058] Step 1: Set the test parameters

[0059] The test parameters include the load torque M2 that the aircraft's main wheel steering system needs to withstand and the horizontal distance between the hinge joint and the center of rotation of the steering shaft. The test parameters set are the same as those used to obtain the clockwise turning rate of the aircraft's braking system.

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

[0061] The second loading point, formed by the hinge joint and the hinge lug, is located near the host computer 1 on the test bench. The center distance between this second loading point and the center of rotation of the turning shaft is L = 0.5m.

[0062] Step 3, Loading the experiment:

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

[0064] The control system's host computer sends a command to the turning axle to rotate counterclockwise; the rotation angle of the turning axle is β2. This rotation angle must satisfy β2 ≤ β max .

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

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

[0067] Based on the displacement Z2 measured by the displacement sensor in the hydraulic cylinder, the formula β is used. m2 =arcsin(Z2 / L) gives the counterclockwise turning angle β of the aircraft braking system. m2 The curve varying with time is used to calculate the aircraft's counter-clockwise turn rate. This is achieved using the formula V² = Δβ. m2 / Delta t2 gets the clockwise turning rate of the airplane brake system; in the formula, V1 is the clockwise turning rate; Delta beta m2 is the change amount of the turning angle in a period of time Delta t2 when turning counterclockwise.

[0068] At this point, the clockwise turning rate and the counterclockwise turning rate of the airplane brake system are tested, and the clockwise turning rate V1 of the airplane brake system and the counterclockwise turning rate V2 of the airplane brake system are obtained.

[0069] The test device and the test method can accurately measure the locking force of the main wheel turning system and the turning rate of the airplane main wheel turning system under different loads.

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

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

[0072] The test device for the airplane 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 the counterclockwise rotation loading of the main wheel turning system are realized, and the loading mode of the conventional loading test bench is expanded.

[0073] The present application adds loading points at a distance L from the center of rotation of the turning shaft, and the distance L is calculated according to formula (1) according to different test requirements. The proposed airplane main wheel turning system locking force test method can test the maximum pressure and tension locking force of the airplane main wheel turning system according to the flowchart shown in Figure 2 The test effect of the proposed airplane main wheel turning system turning rate test method is shown in Figure 8 The main wheel turning system rotates 8° in 2 seconds, and the turning rate is 4° / s. It can be seen that the test device and the test method for the airplane main wheel turning system proposed by the present application can meet the requirements of the related tests of the locking force and the turning rate of the airplane main wheel turning system, and can ensure the safe, reliable and efficient operation of the airplane main wheel turning system. BRIEF DESCRIPTION OF DRAWINGS

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

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

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

[0077] Figure 4 Figure 1 is a schematic diagram of a test device for testing the turning rate of an airplane main wheel turning system under clockwise load.

[0078] Figure 5 Figure 2 is a schematic diagram of a test device for testing the turning rate of an airplane main wheel turning system under counterclockwise load.

[0079] Figure 6 Figure 3 is a schematic diagram of the test effect of the airplane main wheel turning system turning rate test.

[0080] Figure 7 Figure 4 is a schematic diagram of the airplane main wheel turning system locking force test method.

[0081] Figure 8 Figure 5 is a schematic diagram of the airplane main wheel turning system turning rate test method.

[0082] In the figure: 1. Test bench host computer; 2. Test bench fixed support; 3. Upper fixed bolt; 4. Turning system support; 5. Turning shaft; 6. Wheel; 7. Hinge joint; 8. Lower fixed bolt; 9. Hydraulic cylinder; 10. Test bench loading platform; 11. Test bench cable; 12. Turning system crank; 13. Turning actuating 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 set value; 21. Turning angle measured value. DETAILED DESCRIPTION

[0083] The embodiment is a device capable of testing the locking force and the turning rate under load of an airplane main wheel turning system.

[0084] The test device for the airplane main wheel turning system includes a test bench host computer 1, a test bench fixed support, a turning system support 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 airplane main wheel turning system includes a turning system crank 12, a turning actuating system 13, a turning system connecting rod 14, and a turning shaft 5.

[0086] The test bench host computer 1 is connected with the hydraulic cylinder 9 through a test bench cable 11; the hydraulic cylinder 9 is mechanically connected with the test bench loading platform 10, the required load amount is set by 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 realize the loading of the test load. The maximum load that can be loaded by the test bench is F max ; the displacement sensor in the hydraulic cylinder measures the hydraulic cylinder stroke and returns it to the test bench host computer 1 through the test bench cable 11.

[0087] The turning system support 4 is installed on the lower end of the test bench fixed support 2 through the upper fixing bolt 3. The turning shaft 5 is installed on the turning system support 4 through the bolt at the rotation center. The machine wheel 6 is installed on the two ends of the turning shaft 5 and is rotationally connected between the two ends. The turning shaft 5 is sleeved with the hinged joint 7, the hinged joint is hinged with the hinged ear 8 on the test bench loading platform 10, and the turning shaft 5 is rotated clockwise / counterclockwise, and the maximum angle of the one-way rotation is β max ; the horizontal distance between the hinged joint 7 and the rotation center of the turning shaft 5 is L,

[0088] The connection between the hinged ear 8 and the hinged joint 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 requirement of the clockwise or counterclockwise rotation of the turning shaft 5, to form a first loading point or a second loading point.

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

[0090]

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

[0092] The airplane main wheel turning system is installed on the test device, and one end of the turning system crank 12 is fixedly connected with the support connecting piece of the turning system support 4. The upper end of the turning actuating system 13 is hinged with the other end of the turning system crank. The connecting rod connecting piece at the upper end of the turning system connecting rod 14 is hinged with the third end of the turning system crank.

[0093] The oil outlet of the hydraulic source 17 is mechanically connected with the oil inlet of the turning actuating system 13 through the oil inlet pipeline 15, and the oil return port of the hydraulic source 17 is mechanically connected with the oil return port of the turning actuating system 13 through the oil return pipeline 16.

[0094] The control system host computer 18 is electrically connected with the turning actuating system 13 through the control cable 19. The turning instruction is set through the control system host computer 18 to control the extension and contraction of the turning actuating system 13, so that the clockwise turning and counterclockwise turning of the airplane main wheel turning system are realized. Meanwhile, the turning actuating system 13 is provided 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 provided by the application includes testing the locking force of the airplane main wheel turning system and obtaining the turning speed of the airplane main wheel turning system under load. The specific process is as follows:

[0096] I. Test the locking force of the airplane 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] i. Test of the maximum pressure locking force

[0099] Step 1: Set the test parameters

[0100] The test parameters include the load moment required to be borne by the aircraft main wheel turning system, the horizontal distance between the hinge joint 7 and the turning center of the turning shaft 5, and the initial angle a between the turning actuating system 13 and the turning shaft 5.

[0101] The load moment required to be borne by the aircraft main wheel turning system is set as M1, the horizontal distance between the hinge joint and the turning center of the turning shaft is L, and the initial angle between the turning actuating system and the turning shaft is a.

[0102] In this embodiment, L = 0.5 m, and the load force F1 of the hydraulic cylinder 9 is obtained by the formula F1 = M1 / L = 100 KN. The initial angle a between the turning actuating system 13 and the turning shaft 5 is a = 60°.

[0103] Step 2: Install the loading point position

[0104] The first loading point formed by the hinge joint 7 and the hinge lug 8 is located near the hydraulic source 17.

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

[0106] Step 3: Load the test

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

[0108] Obtain the displacement of the turning actuating system through the displacement sensor in the turning actuating system

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

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

[0111] ⅱTest of the maximum tension locking force

[0112] Step 1, set the load moment required to be borne by the aircraft main wheel turning system, the horizontal distance between the hinge joint 7 and the turning shaft 5 rotation center, and the initial angle between the turning actuation system 13 and the turning shaft 5. The load moment required to be borne by the aircraft main wheel turning system, the horizontal distance between the hinge joint 7 and the turning shaft 5 rotation center, and the initial angle between the turning actuation system 13 and the turning shaft 5 in the test of the maximum tension locking force are the same as those in the test of the maximum pressure locking force.

[0113] Step 2, install the second loading point

[0114] Remove the hinge joint 7 forming the first loading point and install it to the symmetrical position on the other side of the turning shaft 5 rotation center to form the second loading point; the second loading point is located close to the host computer 1 side on the test bed; the center distance between the second loading point and the turning shaft 5 rotation center is L = 0.5 m.

[0115] Step 3, load test

[0116] Set the loading instruction of the loading force F2 through the host computer 1 on the test bed and control the hydraulic cylinder 9 to output the loading force F2 through the test bed cable 11, maintain the current loading force F2 and continuously output for T hours.

[0117] Obtain the displacement of the turning actuation system through the displacement sensor in the turning actuation system.

[0118] If the displacement measured by the turning actuation system is > 0, it is considered that the current 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 obtained displacement is ≤ 0;

[0119] If the displacement measured by the turning actuation system is ≤ 0, the load force applied by the current test bed is recorded. The load force applied by the current test bed is the maximum pressure 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 bed is recorded, and step 4 is entered. The load force applied by the current test bed is the maximum pressure locking force.

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

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

[0124] II. Obtain the aircraft main wheel turning system with load turning rate

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

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

[0127] If the clockwise turning rate of the aircraft main wheel turning system is selected to be tested, go to step i;

[0128] If the counterclockwise turning rate of the aircraft main wheel turning system is selected to be tested, go to step ii;

[0129] i. Obtain the clockwise turning rate of the aircraft brake system, and the specific process is

[0130] Step 1: Set the test parameters

[0131] The test parameters include the load moment M2 required to be borne by the aircraft main wheel turning system and the horizontal distance L between the hinge joint 7 and the rotation center of the turning shaft 5.

[0132] When obtaining the clockwise turning rate of the aircraft brake system, the load moment M2 required to be borne by the aircraft main wheel turning system is set to 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 0.5 m.

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

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

[0135] The first loading point formed by the hinge joint 7 and the hinge ear 8 is located near the hydraulic source 17 side. The center distance between the first loading point and the rotation center of the turning shaft 5 is L;

[0136] Step 3, load test:

[0137] The host computer 1 of the test bench sets the loading instruction of the loading force 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 actuating system 13 to make the turning shaft rotate clockwise; the turning angle of the turning shaft when the airplane brake system turns clockwise is β1. The turning angle β1≤β max In this embodiment, β1=8°.

[0139] The airplane 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 clockwise turning speed V1 of the airplane brake system:

[0141] According to the displacement Z1 measured by the displacement sensor in the hydraulic cylinder 9, the clockwise turning angle β m1 of the airplane brake system is obtained by the formula β m1 =arcsin(Z1 / L). m1 The curve changing with time is used to calculate the clockwise turning speed of the airplane; the clockwise turning speed of the airplane brake system is obtained by the formula V1=Δβ m1 / Δt1; in the formula, V1 is the turning speed when turning clockwise; Δβ m1 is the variation of the turning angle when turning clockwise in a period of time Δt1.

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

[0143] ⅱObtain the counterclockwise turning speed of the airplane brake system, and the specific process is

[0144] Step 1: set test parameters

[0145] The test parameters include the load moment M2 required to be borne by the airplane main wheel turning system and the horizontal distance between the hinge joint 7 and the rotation center of the turning shaft 5. The set test parameters are the same as those when obtaining the clockwise turning speed of the airplane brake system.

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

[0147] The second loading point formed by the hinge joint 7 and the hinge lug 8 is located close to the test bench host computer 1 side. The center distance between the second loading point and the rotation center of the turning shaft 5 is L=0.5m,

[0148] Step 3, load test:

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

[0150] The host computer 18 of the control system sends a counterclockwise rotation instruction to the turning actuating system 13; the rotation angle of the turning shaft of the airplane brake system when turning counterclockwise is β 2； The rotation angle β2≤β max In this embodiment, β2=8°

[0151] The airplane main wheel turning system turns counterclockwise; the host computer 1 of the test bed records the displacement Z2 measured by the displacement sensor in the hydraulic cylinder 9

[0152] Step 4: Determine the counterclockwise turning rate V2 of the airplane brake system:

[0153] According to the displacement Z2 measured by the displacement sensor in the hydraulic cylinder 9, the counterclockwise turning angle β of the airplane brake system is obtained by the formula β m2 =arcsin(Z2 / L) m2 The curve of the change over time is used to calculate the counterclockwise turning rate of the airplane; the counterclockwise turning rate of the airplane brake system is obtained by the formula V2=Δβ m2 / Δt2; in the formula, V2 is the counterclockwise turning rate; Δβ m2 is the change amount 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] Thus, the test of the clockwise and counterclockwise turning rates of the airplane brake system with load is completed, and the clockwise turning rate V1 of the airplane brake system and the counterclockwise turning rate V2 of the airplane brake system are obtained.

Claims

1. A test apparatus for an aircraft main wheel steering system, characterized in that, It includes a test bench host computer (1), a test bench fixed 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). 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 host computer (1) sets the required load amount, controls the displacement of the hydraulic cylinder, and further controls the upward movement of the test bench loading platform to achieve the loading of the test load; the maximum load that the test bench can load is... The displacement sensor inside the hydraulic cylinder (9) measures the stroke of the hydraulic cylinder and returns it to the host computer (1) on the test bench via 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) by bolts at the rotation center; the wheel (6) is installed at both ends of the turning shaft, and the two are rotated together; a hinge joint (7) is fitted on the turning shaft, which is hinged to the hinge lug (8) on the loading platform (10) of the test bench, and the turning shaft rotates clockwise / counterclockwise, with a maximum unidirectional rotation angle of 1 / 2. The horizontal distance between the hinge joint and the rotation center of the turning shaft is L. The connection between the hinge lug (8) and the hinge joint forms a variable loading point for 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 clockwise or counterclockwise rotation of the turning shaft, forming a first loading point or a second loading point; When the maximum load torque of the main wheel steering system under test is Then L satisfies the following equation: （1）； The rotation center coincides with the center of the hinge point between the turning system bracket (4) and the turning shaft (5).

2. The test apparatus for the aircraft main wheel steering system as described in claim 1, characterized in that, The aircraft main wheel turning system includes 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 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 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 is hinged to the third end of the turning system crank; The oil outlet of the hydraulic power source (17) is mechanically connected to the oil inlet of the turning actuation system (13) through the oil inlet pipe (15), and the oil return port of the hydraulic power source is mechanically connected to the oil return port of the turning actuation system through the oil return pipe (16). The host computer (18) of the control system is electrically connected to the turning actuation system through the control cable (19); the host computer of the control system sets the turning command to control the turning actuation system to extend and retract, thereby realizing the clockwise and counterclockwise turning of the main wheel turning system of the aircraft; at the same time, the turning actuation system is equipped with a displacement sensor, and the measured displacement information is returned to the host computer (18) of the control system through the control cable.

3. A test method using the test apparatus of claim 2, characterized in that, The test included testing the locking force of the aircraft's main wheel steering system and obtaining the aircraft's main wheel steering system's turning rate under load; the specific process was as follows: Ⅰ Test the locking force of the aircraft's main wheel steering system: The locking force of the aircraft main wheel steering system includes the maximum pressure locking force and the maximum tension locking force; i. Maximum pressure locking force test: Step 1: Set the test parameters: The test parameters include the load torque required to withstand by the main wheel turning system of the aircraft, 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 torque M1 required to withstand by the aircraft main wheel turning system is set, the horizontal distance between the hinge joint and the rotation center of the turning shaft is L, and the initial angle between the turning actuation system and the turning shaft is α. Step 2: Install the first loading point: The first loading point formed by the hinge joint (7) and the hinge lug (8) is located on the side closer to the hydraulic source (17); Step 3: Loading Experiment: When testing the maximum pressure locking force of the aircraft's main wheel steering system, the loading force on the test bench was set to... The loading command is received, and the hydraulic cylinder is controlled via the test bench cable to output the loading force. and maintain this loading force. Continuous output for T hours; The displacement of the turning actuation system is obtained by a displacement sensor in the turning actuation system. If the displacement measured by the turning actuation system is greater than 0, then the currently set load force is considered to be... Exceeding the limits of the turning actuation system (13); reducing the load by 10%. Then return to step 2 to reload; until the displacement measured by the turning actuation system is ≤0; If the displacement measured by the turning actuation system is ≤0, then record the load force applied by the test bench at the current time; the load force applied by the test bench at the current time is the maximum pressure locking force. ii. Maximum tensile locking force test: Step 1, set the test parameters: Set the load torque required by the main wheel turning system, the horizontal distance between the hinge joint (7) and the center of rotation of the turning shaft (5), and the initial angle between the turning actuation system (13) and the turning shaft; the load torque required by the main wheel turning system, the horizontal distance between the hinge joint and the center of rotation 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 tension locking force when the maximum tension locking force is tested; 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 the second loading point; the second loading point is located on the side close to the host computer (1) on the test bench; the center distance between the second loading point and the rotation center of the turning shaft is L=0.5m; Step 3, Loading the experiment: The loading force is set to be determined by the host computer (1) on the test bench. The loading command is transmitted through the test bench cable (11) to control the hydraulic cylinder (9) to output the loading force. Maintain current loading force And continuously output T hours; The displacement of the turning actuation system is obtained by a displacement sensor in the turning actuation system. If the displacement measured by the turning actuation system is greater than 0, then the currently set load force is considered to be... Exceeding the limits of the turning actuation system (13); reducing the load by 10%. Then return to step 2 to reload; until the obtained displacement is ≤0; If the displacement measured by the turning actuation system is ≤0, then record the load force applied by the test bench at the current time; the load force applied by the test bench at the current time is the maximum tensile locking force. Thus, the tests on the pressure locking force and tension locking force of the aircraft braking system are completed, and the maximum pressure locking force and maximum tension locking force of the aircraft braking system are obtained. II. Obtain the load-bearing turning rate of the aircraft's main wheel turning system: The aircraft main wheel turning system's turning rate under load includes the aircraft braking system's clockwise turning rate V1 and the aircraft braking system's counterclockwise turning rate. According to the designed test outline, the rotation direction of the aircraft main wheel steering system is selected as either clockwise or counterclockwise. When the rotation direction of the aircraft main wheel steering system is clockwise, the clockwise turning rate is obtained; conversely, the counterclockwise turning rate is obtained. If you choose to test the clockwise turning rate of the aircraft's main wheel turning system, proceed to step i; If you choose to test the counterclockwise turning rate of the aircraft's main wheel turning system, proceed to step ii; i. Obtain the clockwise turning rate of the aircraft braking system. The specific process is as follows: Step 1: Set the test parameters: The test parameters include the load torque M2 required to be borne by the main wheel turning system of the aircraft and the horizontal distance L between the hinge joint (7) and the center of rotation of the turning shaft (5); Step 2, Install the first loading point: The first loading point formed by the hinge joint (7) and the hinge lug (8) is located on the side closer 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 the experiment: The loading force is set to be on the host computer of the test bench (1). The loading command is received, and the hydraulic cylinder (9) is controlled to output the loading force via the test bench cable (11). ; The control system's host computer sends a command to the turning actuation system (13) to rotate the turning shaft clockwise; when the aircraft braking system turns clockwise, the rotation angle of the turning shaft is... ; The aircraft's main wheel steering system rotates clockwise; the host computer (1) on the test bench records the displacement measured by the displacement sensor in the hydraulic cylinder (9). ; Step 4, determine the clockwise turning rate V1 of the aircraft braking system: The displacement measured by the displacement sensor in the hydraulic cylinder (9) Through formula Obtain the clockwise turning angle of the aircraft braking system The curve that changes over time is used to calculate the aircraft's clockwise turn rate; through the formula... The clockwise turning rate of the aircraft braking system is obtained; where, It is the turning speed when turning clockwise; The clockwise turning angle over a period of time The change in; ii. Obtain the counter-clockwise turning rate of the aircraft braking system. The specific process is as follows: Step 1: Set the test parameters: The test parameters include the load torque M2 required to be borne by the main wheel turning system of the aircraft and the horizontal distance between the hinge joint (7) and the center of rotation of the turning shaft (5); the test parameters set are the same as the test parameters when obtaining the clockwise turning rate of the aircraft braking system. Step 2, Install the second loading point: The second loading point, formed by the hinge joint (7) and the hinge lug (8), is located on the side closer to the host computer (1) on the test bench; the center distance between this second loading point and the center of rotation of the turning shaft (5) is L = 0.5m. Step 3, Loading the experiment: The loading force is set on the host computer of the test bench to be The loading command is received, and the hydraulic cylinder (9) is controlled to output the loading force via the test bench cable (11). ; The control system's host computer (18) sends a counterclockwise rotation command to the turning actuation system (13); when the aircraft braking system turns counterclockwise, the rotation angle of the turning shaft is β. 2； The rotation angle β2≤ The main wheel steering system of the aircraft rotates counterclockwise; the host computer on the test bench (1) records the displacement measured by the displacement sensor in the hydraulic cylinder (9). ; Step 4, determine the counterclockwise turning rate V2 of the aircraft braking system: The displacement measured by the displacement sensor in the hydraulic cylinder (9) Through formula Obtain the counterclockwise turning angle of the aircraft braking system The curve that changes over time is used to calculate the aircraft's counter-clockwise turn rate; through the formula... The counterclockwise turning rate of the aircraft braking system is obtained; where, It is the turning rate when turning counterclockwise; It is the change in the turning angle over a time period Δt2 when turning counterclockwise; Thus, the tests on the clockwise and counterclockwise turning rates of the loaded aircraft braking system were completed, and the clockwise turning rate V1 and the counterclockwise turning rate V2 of the aircraft braking system were obtained.

4. The test method using the test apparatus of claim 3, characterized in that, The specific process is as follows: In step 1 of testing the locking force of the aircraft's main wheel steering system, the load torque that the aircraft's main wheel steering system needs to withstand is set. 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... .

5. The test method using the test apparatus of claim 3, characterized in that, The specific process is as follows: In step 2, the center distance between the first loading point and the center of rotation of the turning shaft is L=0.5m.

6. The test method using the test apparatus of claim 4, characterized in that, The specific process is as follows: when obtaining the clockwise turning rate of the aircraft braking system, the set load torque that the aircraft main wheel turning system needs to withstand is... The horizontal distance between the hinge joint (7) and the rotation center of the turning shaft (5) is L=0.5m.

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