Large undercarriage main wheel turning mechanism test device and test method

Abstract

The invention provides a large undercarriage main wheel turning mechanism test device and test method, and belongs to the technical field of aircraft undercarriage tests, the turning mechanism test device comprises a support frame, a loading actuator, a cross beam, a turning loading mechanism, an aircraft wheel carrier assembly and a test bench; the loading actuator is arranged on the supporting frame, one end of the loading actuator is connected with the cross beam, the other end of the loading actuator is connected with the supporting frame, and the loading actuator is used for adjusting the pressure of the airplane wheel frame assembly on the test bed; the cross beam is pivoted on the support frame, one end of the cross beam is connected with the loading actuator, and the other end of the cross beam is provided with one or more airplane wheel frame assemblies; the turning loading mechanism is mounted on the cross beam and is used for applying turning torque to the wheel carrier assembly; the test bench is installed on the supporting frame and used for bearing the airplane wheel carrier assembly and measuring the pressure and turning torque of the airplane wheel carrier assembly on the test bench at the same time.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft landing gear testing, and in particular relates to a testing device and a testing method for a large landing gear main wheel turning mechanism. Background Art

[0002] Large landing gear is usually used in large aircraft, and it carries a heavy load. When the landing gear is turning, the torque required to operate the landing gear is also relatively large. There are many factors that affect the turning torque, such as main wheel load, tire deformation, main wheel track, and the control mechanism itself. In order to better measure the relationship between the above factors and the required control torque, a large landing gear main wheel turning mechanism test device is needed. Summary of the invention

[0003] The purpose of the present application is to provide a large landing gear main wheel turning mechanism testing device and testing method to solve or alleviate at least one problem in the background technology.

[0004] On the one hand, the technical solution of the present application is: a large landing gear main wheel turning mechanism test device, including: a support frame, a loading actuator, a crossbeam, a turning loading mechanism, a wheel frame assembly and a test bench;

[0005] The loading actuator is arranged on the support frame, one end of the loading actuator is connected to the cross beam, and the other end is connected to the support frame, and is used to adjust the pressure of the wheel frame assembly on the test bench;

[0006] The crossbeam is pivotally connected to the support frame, one end of which is connected to the loading actuator, and the other end is mounted with one or more wheel frame assemblies;

[0007] The turning loading mechanism is mounted on the cross beam and is used to apply a turning moment to the wheel frame assembly;

[0008] The test bench is installed on a support frame and is used to carry the wheel frame assembly and measure the pressure and turning moment of the wheel frame assembly on the test bench.

[0009] Preferably, the support frame is a frame structure.

[0010] Preferably, the loading actuator is a hydraulic actuator.

[0011] Preferably, the crossbeam is provided with a plurality of mounting holes along its length direction for adjusting the position of the crossbeam relative to the support frame or the wheel frame assembly.

[0012] Preferably, the wheel frame assembly includes a wheel and an axle, the axle passes through a mounting hole on the crossbeam 30 and is arranged on the test bench, and the distance between two adjacent wheel frame assemblies is adjusted through the mounting holes on the crossbeam.

[0013] Preferably, the distance between the wheels on the axle and the crossbeam can be adjusted.

[0014] Preferably, the turning loading mechanism includes a turning actuator, a connecting rod and a rocker arm, the turning actuator and the connecting rod are symmetrically connected to the mounting joints on both sides of the wheel axle, one end of the rocker arm is hinged to the cross beam, the other end is hinged to the turning actuator, and the middle end is hinged to the connecting rod, so that the turning actuator, connecting rod, rocker arm and wheel axle form a four-bar linkage.

[0015] Preferably, the torque M applied to the wheel axle by the turning actuator satisfies:

[0016] M=F zdt *L1+F zdt *L3 / L4*L2

[0017] In the formula, F zdt Output force for the turning actuator;

[0018] L1 is the turning actuator force arm;

[0019] L2 is the connecting rod force arm;

[0020] L3 is the rocker arm torque,

[0021] L4 is the moment of intersection between the connecting rod and the rocker arm.

[0022] Preferably, the test bench comprises a bottom table, a middle table and a top table, a first sensor is arranged between the bottom table and the middle table, and a second sensor is arranged between the middle table and the top table.

[0023] Preferably, the material of the top tabletop is replaced according to the use environment of the aircraft landing gear.

[0024] Preferably, the first sensor and the second sensor are of different sensor types.

[0025] Preferably, the first sensor is a torque sensor, and the second sensor is a three-force sensor.

[0026] On the other hand, the present application provides a method for testing using any of the above-mentioned large landing gear main wheel turning mechanism testing devices, comprising:

[0027] S10, installing one or more wheel frame assemblies on the crossbeam, applying tension through a loading actuator, causing the crossbeam to rotate around a fulcrum on the support frame, thereby applying a predetermined pressure on the test bench to the wheel frame assembly;

[0028] S20, applying a turning moment to the wheel axle of the wheel frame assembly through a turning actuator in a turning loading mechanism, and attaching a strain gauge to a connecting rod of the wheel frame assembly;

[0029] S30, obtaining the torque value applied by the turning actuator, the strain gauge value attached to the connecting rod, and the measurement values ​​of the first sensor and the second sensor in the test bench;

[0030] S40, the pressure of the wheel frame assembly applied by the loading actuator on the test bench and the turning moment applied by the turning actuator are inspected and verified by the first sensor and / or the second sensor, and the first sensor and the second sensor are mutually verified.

[0031] The large landing gear main wheel turning device test device provided in the present application can realize the turning torque test of multiple main wheels. The measured data is an independent test, which can better solve the loading problem of large loads on the main wheels. The test process can realize the measurable and controllable output torque and pressure of the turning actuator, and can realize stress monitoring of the connecting rod. The first sensor and the second sensor are mutually checked, and the measurement results are accurate and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0033] Figure 1 This is a schematic diagram of a large landing gear main wheel turning mechanism test device for this application.

[0034] Figure 2 This is a top view of the large landing gear main wheel turning mechanism testing device of the present application.

[0035] Figure 3 This is a schematic diagram of the turning loading mechanism of this application.

[0036] Figure 4 Schematic diagram of the test bench for this application.

[0037] Figure 5 This is a top view of the test bench for this application. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0039] like Figure 1 and Figure 2 As shown, the large landing gear main wheel turning mechanism testing device provided in the present application includes: a support frame 10, a loading actuator 20, a crossbeam 30, a turning loading mechanism 40, a wheel frame assembly 50 and a test bench 60.

[0040] The support frame 10 is a frame structure, which is installed and fixed on the ground of the test chamber for bearing.

[0041] The loading actuator 20 is vertically installed on the support frame 10. Its upper side is connected to the support frame 10, and its lower side is connected to the cross beam 30, for providing tensile load to the cross beam 30. In the preferred embodiment of the present application, the loading actuator 20 is a hydraulic actuator cylinder, so as to provide stable loading.

[0042] The cross beam 30 is arranged on the support frame 10. Its left side is connected to the loading actuator cylinder 20, its middle part is hinged to the support frame 10, and its right side is used for the installation of the wheel frame assembly 50. Wherein, a plurality of mounting holes are arranged along the length direction of the cross beam 30, for adjusting the position or distance of the cross beam 20 relative to the support frame 10 or the wheel frame assembly 50.

[0043] The wheel frame assembly 50 includes a wheel 51 and a wheel axle 52. The wheel axle 52 is arranged on the test bench 60 through the mounting hole on the cross beam 30. In some embodiments of the present application, the number of the wheel frame assemblies 50 can be two or more, and the distance between two adjacent wheel frame assemblies 50 can be adjusted through the mounting holes on the cross beam 30. Further, the distance between the wheels 51 on the wheel axle 52 relative to the cross beam 30 can be adjusted, that is, the distances between the wheels 51 on both sides of the cross beam 30 in a single wheel frame assembly 50 from the cross beam 30 can be the same or different.

[0044] As Figure 3 shown, the turning loading mechanism 40 includes a turning actuator 41, a connecting rod 42 and a rocker arm 43. Wherein, the turning actuator 41 and the connecting rod 42 are symmetrically connected to the mounting joint of the wheel axle 52. The rocker arm 3 is in a T shape. Its lower end is hinged to the cross beam 30, its upper end is hinged to the turning actuator 41, and its middle end point is hinged to the connecting rod 42. Thus, the turning actuator 41, the connecting rod 42, the rocker arm 43 and the wheel axle 52 form a four-bar linkage mechanism. The moment M applied to the wheel axle 52 by the turning actuator 41 satisfies:

[0045] M = F zdt *L1 + F zdt *L3 / L4*L2

[0046] In the formula, F zdt is the output force of the turning actuator;

[0047] L1 is the acting force arm of the turning actuator;

[0048] L2 is the acting force arm of the connecting rod;

[0049] L3 is the moment of the rocker arm,

[0050] L4 is the intersection moment of the connecting rod and the rocker arm.

[0051] Since the lever arm L3 is greater than the lever arm L4, the torque output by the turning actuator is amplified.

[0052] like Figure 4 and Figure 5 As shown, the test bench 60 includes a bottom table 61, a middle table 62 and a top table 63, wherein a first sensor 64 is arranged between the bottom table 61 and the middle table 62, and a second sensor 65 is arranged between the middle table 62 and the top table 63. In the present application, the first sensor 64 and the second sensor 65 are different sensor types.

[0053] In the present application, the material of the top table 63 can be replaced according to the use environment of the aircraft landing gear. For example, it can be set to an asphalt table, a concrete table, etc.

[0054] In some embodiments of the present application, the first sensor 64 is a torque sensor, and the second sensor is a three-force sensor. It is understandable that the first sensor 64 and the second sensor 65 can be interchanged in position.

[0055] On this basis, the present application also provides a method for testing based on the above landing gear main wheel turning mechanism testing device, including:

[0056] S10, installing one or more wheel frame assemblies 50 on the cross beam 30, applying tension through the loading actuator 10, so that the cross beam 30 rotates around the fulcrum on the support frame 10, so that the wheel frame assembly 50 applies a predetermined pressure to the test bench 60, and the pressure can be adjusted according to the load requirement of the landing gear;

[0057] For example, in the illustrated embodiment of the present application, there are two wheel frame assemblies 50 to be tested, which are arranged along the length direction of the crossbeam 30. It is understandable that there may also be three or more wheel frame assemblies 50 to be tested, which will not be described in detail here.

[0058] S20, applying a turning moment to the wheel axle 52 of the wheel frame assembly 50 through the turning actuator 41 in the turning loading mechanism 40, and attaching a strain gauge to the connecting rod 42 of the wheel frame assembly 50;

[0059] S30, obtaining the torque value applied by the turning actuator 41, the strain gauge value attached to the connecting rod 42, and the measurement values ​​of the first sensor 64 and the second sensor 65 in the test bench 60;

[0060] S40, the pressure of the wheel frame assembly 60 applied by the loading actuator 10 on the test bench and the turning moment applied by the turning actuator 41 are inspected and verified through the first sensor 64 and / or the second sensor 65, and the first sensor 64 and the second sensor 65 are also mutually verified.

[0061] The large landing gear main wheel turning device test device provided in the present application can realize the turning torque test of multiple main wheels. The measured data is an independent test, which can better solve the loading problem of large loads on the main wheels. The test process can realize the measurable and controllable output torque and pressure of the turning actuator, and can realize stress monitoring of the connecting rod. The first sensor and the second sensor are mutually checked, and the measurement results are accurate and reliable.

[0062] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A large landing gear main wheel turning mechanism test device, characterized in that: include: Support frame, loading actuator, crossbeam, turning loading mechanism, wheel frame assembly and test bench; The loading actuator is arranged on the support frame, one end of the loading actuator is connected to the crossbeam and the other end is connected to the support frame, and is used to adjust the pressure of the wheel frame assembly on the test bench; The crossbeam is pivotally connected to the support frame, one end of which is connected to the loading actuator, and the other end is mounted with one or more wheel frame assemblies; The turning loading mechanism is mounted on the cross beam and is used to apply a turning moment to the wheel frame assembly; The test bench is installed on a support frame and is used to carry the wheel frame assembly and measure the pressure and turning moment of the wheel frame assembly on the test bench.

2. The large landing gear main wheel turning mechanism testing device according to claim 1, characterized in that: The support frame is a frame structure.

3. The large landing gear main wheel turning mechanism testing device according to claim 1, characterized in that: The loading actuator is a hydraulic actuator.

4. The large landing gear main wheel turning mechanism testing device according to claim 1, characterized in that: The crossbeam is provided with a plurality of mounting holes along its length direction, which are used to adjust the position of the crossbeam relative to the support frame or the wheel frame assembly.

5. The large landing gear main wheel turning mechanism testing device as claimed in claim 4, characterized in that: The wheel frame assembly includes a wheel and an axle. The axle passes through a mounting hole on the crossbeam 30 and is arranged on the test bench. The distance between two adjacent wheel frame assemblies is adjusted through the mounting holes on the crossbeam.

6. The large landing gear main wheel turning mechanism testing device as claimed in claim 5, characterized in that: The distance of the wheels on the axle relative to the crossbeam can be adjusted.

7. The large landing gear main wheel turning mechanism testing device as claimed in claim 5, characterized in that: The turning loading mechanism includes a turning actuator, a connecting rod and a rocker arm. The turning actuator and the connecting rod are symmetrically connected to the mounting joints on both sides of the wheel axle. One end of the rocker arm is hinged on the crossbeam, the other end is hinged to the turning actuator, and the middle end is hinged to the connecting rod, so that the turning actuator, the connecting rod, the rocker arm and the wheel axle form a four-bar linkage.

8. The large landing gear main wheel turning mechanism testing device according to claim 7, characterized in that: The torque M applied to the wheel axle by the turning actuator satisfies: <h2 style=";text-align:left;direction:ltr">M=F<h2 style=";text-align:left;direction:ltr"> zdt <h2 style=";text-align:left;direction:ltr"> *L1+F<h2 style=";text-align:left;direction:ltr"> zdt <h2 style=";text-align:left;direction:ltr"> *L3 / L4*L2 In the formula, F zdt Output force for the turning actuator; L1 is the turning actuator force arm; L2 is the connecting rod force arm; L3 is the rocker arm torque, L4 is the moment of intersection between the connecting rod and the rocker arm.

9. The large landing gear main wheel turning mechanism testing device according to claim 1, characterized in that: The test bench comprises a bottom table, a middle table and a top table. A first sensor is arranged between the bottom table and the middle table, and a second sensor is arranged between the middle table and the top table.

10. The large landing gear main wheel turning mechanism testing device according to claim 9, characterized in that: The material of the top tabletop is changed according to the use environment of the aircraft landing gear.

11. The large landing gear main wheel turning mechanism testing device according to claim 9, characterized in that: The first sensor and the second sensor are of different sensor types.

12. The large landing gear main wheel turning mechanism testing device according to claim 11, characterized in that: The first sensor is a torque sensor, and the second sensor is a three-force sensor.

13. A method for testing a large landing gear main wheel turning mechanism using the large landing gear main wheel turning mechanism testing device as claimed in any one of claims 1 to 12, characterized in that: include: S10, installing one or more wheel frame assemblies on the crossbeam, applying tension through a loading actuator, causing the crossbeam to rotate around a fulcrum on the support frame, thereby applying a predetermined pressure on the test bench to the wheel frame assembly; S20, applying a turning moment to the wheel axle of the wheel frame assembly through a turning actuator in a turning loading mechanism, and attaching a strain gauge to a connecting rod of the wheel frame assembly; S30, obtaining the torque value applied by the turning actuator, the strain gauge value attached to the connecting rod, and the measurement values ​​of the first sensor and the second sensor in the test bench; S40, the pressure of the wheel frame assembly applied by the loading actuator on the test bench and the turning moment applied by the turning actuator are inspected and verified by the first sensor and / or the second sensor, and the first sensor and the second sensor are mutually verified.

Images