CN112340061A - Loading method and loading device for static test of undercarriage wheel - Google Patents
Loading method and loading device for static test of undercarriage wheel Download PDFInfo
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- CN112340061A CN112340061A CN202011422495.9A CN202011422495A CN112340061A CN 112340061 A CN112340061 A CN 112340061A CN 202011422495 A CN202011422495 A CN 202011422495A CN 112340061 A CN112340061 A CN 112340061A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention provides a loading method and a loading device for a static test of an undercarriage wheel. The loading device comprises a fixture, a clamping assembly, a vertical loading assembly, a side loading assembly and a navigation loading assembly; the vertical loading assembly is vertically arranged and is connected with the fixture and the clamping assembly; the clamping assembly is arranged on the corresponding position of the fixture through a connecting support; the side loading assembly and the aerial loading assembly are both horizontally arranged on the fixture, wherein the side loading assembly is arranged on two opposite sides of the bearing assembly, and the aerial loading assembly is arranged on one side of the bearing assembly and is vertical to the side loading assembly; and loading points are arranged at two ends of the bearing component and are respectively connected with the side loading component, or one of the loading points is connected with the aerial loading component. Compared with the related technology, the invention can better restore the real working condition and obtain the real and effective test data.
Description
Technical Field
The invention relates to the technical field of general tests, in particular to a loading method and a loading device for a static test of an undercarriage wheel.
Background
With the rapid development of aviation technology in China, the performance of the airplane is continuously improved, and new higher requirements are provided for the performance of the airplane wheel of the airplane landing gear. In order to verify the design and manufacturing strength of the airplane wheels before the airplane tries to fly, the airplane wheels need to be subjected to static test, the real radial load working condition and the radial-lateral combined load working condition of the airplane wheels are simulated in a static test airplane wheel loading device, whether the static strength and rigidity of the main airplane wheel and the brake device meet the design requirements or not is verified, the rationality of the structural design and strength design of the undercarriage airplane wheels and the brake device is verified, and the use safety of the undercarriage airplane wheels and the brake device is guaranteed.
The test is a trend for restoring the real working condition and simulating the actual working condition as much as possible. At present, in a general airplane wheel static force radial loading test, only the airplane wheel bears the designed radial load, but the airplane wheel is required to bear the maximum radial load when a real landing gear is landed, and the airplane wheel is also required to flexibly rotate on the ground, so that the current loading device cannot meet the test requirement and standard.
For example, the frame type catapult-assisted take-off carrier-based aircraft nose landing gear static test loading device disclosed in the patent publication No. CN103604619A is applied to the landing gear static test loading device in front of the frame type catapult-assisted take-off carrier-based aircraft, the test conditions are limited, and the problem that the landing gear wheel loading is truly simulated under different test requirement conditions cannot be solved
Disclosure of Invention
The invention aims to provide a loading method and a loading device for a static test of an undercarriage wheel, which are suitable for simulating and verifying a radial load working condition and a radial-lateral combined load working condition of the static test of the undercarriage wheel.
The technical scheme of the invention is as follows: a static test loading device for a landing gear wheel comprises a jig frame, a clamping assembly for mounting the landing gear wheel, a vertical loading assembly for applying a radial load to the landing gear wheel mounted in the clamping assembly, a side loading assembly for applying a side load to the landing gear wheel mounted in the clamping assembly and an aerial loading assembly for applying a heading load to the landing gear wheel mounted in the clamping assembly; the vertical loading assembly is vertically arranged, the upper end of the vertical loading assembly is connected with the profile frame, and the lower end of the vertical loading assembly is connected with the clamping assembly; the clamping assembly is arranged on the corresponding position of the fixture through a connecting support;
the fixture is characterized in that a bearing assembly is arranged on the fixture and is positioned below the clamping assembly; the side loading assembly and the aerial loading assembly are both horizontally arranged on the fixture, wherein the side loading assembly is arranged on two opposite sides of the bearing assembly, and the aerial loading assembly is arranged on one side of the bearing assembly and is vertical to the side loading assembly;
and loading points are arranged at two ends of the bearing component and are respectively connected with the side loading component, or one of the loading points is connected with the aerial loading component.
In the scheme, the bearing assembly is adjusted to switch between the side loading assembly and the aerial loading assembly, whether jamming exists in the inner structure of the airplane wheel after the airplane lands and whether the airplane wheel can flexibly rotate can be detected, the problem that the airplane wheel of the undercarriage is difficult to truly simulate under different test requirement conditions is solved, the true working condition can be better restored, and the test data is truly and effectively acquired. And the structure of the loading device is not limited to the machine type, and the applicability is wider.
Preferably, the bearing assembly comprises a side bearing joint, a friction plate, a bearing plate, a first sliding block, a first guide rail and a fixing plate; the fixed plate is connected with the fixture, the first guide rail is arranged on the fixed plate, and the first sliding block is connected with the first guide rail in a sliding manner; the bearing plate is fixedly connected with the first sliding block, and the friction plate is stacked at the upper end of the bearing plate; the two ends of the friction plate and the force bearing plate are respectively provided with the side-load joint, and the side-load joints are arranged in the sliding direction of the first sliding block along the first guide rail; the side load joint is the load point.
The friction plate has the function of generating friction force with the airplane wheel when a side load test is carried out, and simulating the real loading condition of the airplane wheel of the undercarriage so as to obtain more effective test data. Through the cooperation structure of guide rail and slider, the effective transmission load power.
For guaranteeing the stability of loading, the effectiveness of data transmission, and avoid the off tracking, first guide rail is in interval is provided with two on the fixed plate, every all cooperate two first sliders on the first guide rail.
In order to ensure the loading accuracy, the vertical loading assembly, the lateral loading assembly and the aerial loading assembly are all servo electric cylinders or servo hydraulic cylinders, and cylinder barrels of the vertical loading assembly, the lateral loading assembly and the aerial loading assembly are all connected with the type frame.
Preferably, the aerial carrier assembly is connected with the bearing assembly through a steel wire rope. The steel wire rope can better simulate the state in course.
Preferably, the undercarriage wheel compression device further comprises a pull wire sensor for collecting the compression amount of the undercarriage wheel, and the pull wire sensor is vertically connected between the jig and the undercarriage wheel installed in the clamping assembly. The compression amount of the airplane wheel can be effectively sensed through the pull wire sensor, and test data are effectively acquired and the load is effectively applied.
Preferably, the clamping assembly is of an inverted U-shaped structure, and a U-shaped cavity for mounting the undercarriage wheel is formed in the clamping assembly. The U-shaped structure simulates bilateral stress of the wheel fork.
Preferably, the clamping assembly comprises a loading flange plate, a top plate, a side plate, a second guide rail, a second sliding block and a wheel flange plate for mounting the undercarriage wheel; the top of the loading flange plate is connected with the vertical loading assembly, the bottom of the loading flange plate is connected with the top plate, and the side plates are vertically arranged at two ends of the top plate, so that an inverted U-shaped structure is formed between the side plates and the top plate, and a U-shaped cavity is formed in the side plates; the outer side walls, far away from the U-shaped cavity, of the two side plates are vertically provided with the second guide rails, each second guide rail is connected with the second sliding block in a sliding mode, and the second sliding blocks are connected with the connecting support; the wheel flange plate is arranged on the inner side wall of the side plate close to the U-shaped cavity.
Preferably, the clamping assembly is of an inverted L-shaped structure, and an L-shaped cavity for mounting the undercarriage wheel is formed in the clamping assembly. The L-shaped mechanism simulates unilateral stress of the wheel fork.
Preferably, the clamping assembly comprises a loading flange plate, a top plate, a side plate, a second guide rail, a second sliding block and a wheel flange plate for mounting the undercarriage wheel; the top of the loading flange plate is connected with the vertical loading assembly, the bottom of the loading flange plate is connected with the top plate, and the side plate is vertically arranged at one end of the top plate, so that an inverted L-shaped structure is formed between the side plate and the top plate, and the inside of the inverted L-shaped structure is provided with an L-shaped cavity; the outer side wall, far away from the L-shaped cavity, of the side plate is vertically provided with the second guide rail, the second guide rail is connected with the second sliding block in a sliding mode, and the second sliding block is connected with the connecting support; the wheel flange plate is arranged on the inner side wall of the side plate close to the L-shaped cavity.
According to the scheme, the changeable clamping assembly can simulate the bilateral loading of the wheel fork undercarriage and the half-wheel fork loading of the half-wheel fork undercarriage more truly.
The invention also provides a static test loading method for the undercarriage wheels, which is carried out by using the static test loading device for the undercarriage wheels and comprises the following steps:
firstly, mounting an undercarriage airplane wheel on a clamping assembly, and calibrating friction force before performing a radial load test and a radial-lateral combined load test;
step two, starting a radial load test: adjusting the direction of the bearing assembly to ensure that the loading point at one end of the bearing assembly is connected with the aerial load assembly and the loading point at the other end of the bearing assembly is not connected, and fixing the bearing assembly on the fixture; gradually applying radial load through the vertical load assembly, collecting the compression amount of the airplane wheel in real time, and applying the calculated course load to the navigation load assembly to check whether the airplane wheel rotates flexibly;
step three, starting a radial-lateral combined load test: adjusting the direction of the bearing component, namely connecting the loading points at the two ends of the bearing component with the side bearing component respectively, and fixing the bearing component on the fixture; radial load is applied through the vertical load assembly, and the inner side load and the outer side load pull a friction plate of the load bearing assembly through the lateral load assembly, so that the friction force generated between the friction plate and the tire of the airplane wheel is applied; the radial load and the lateral load are in coordinated loading in the radial-lateral combined load working condition;
and step four, completing the test.
In the scheme, the method for checking the flexibility of the wheel under the radial load working condition can detect whether the internal structure of the wheel of the airplane is blocked or not and whether the wheel can flexibly rotate or not after the airplane lands. The stay wire sensors are added under the radial load working condition and the radial-lateral load working condition to record the compression amount of the airplane wheel in real time, so that the problem that the undercarriage airplane wheel is difficult to truly simulate to load under different test requirements is solved.
Compared with the related technology, the invention has the beneficial effects that: the real working condition can be better restored, and the obtained test data is real and effective; the method is suitable for simulation and verification of loading tests of radial load and radial-lateral load of a wheel of a static testing machine, adopts a changeable clamping assembly to simulate bilateral loading of a wheel fork undercarriage and half-wheel fork loading of a half-wheel fork lifting frame, increases a method for checking the flexibility of a radial load wheel, increases a radial load and radial-lateral load stay wire sensor to record the compression amount of the wheel in real time, solves the problem that different test requirements simulate real undercarriage wheel loading, and obtains real and effective test data; the wheel loading device for the static test can simultaneously realize a plurality of working conditions, improve the test efficiency, greatly save the test cost, is simple to operate and has high applicability and reliability.
Drawings
FIG. 1 is a schematic structural diagram of a static test loading device for a landing gear wheel provided by the invention;
FIG. 2 is a schematic view of radial loading of a static test loading device;
FIG. 3 is a schematic view of radial-lateral combined load loading of a static test loading device;
FIG. 4 is a schematic front view of the load bearing assembly of FIG. 1;
FIG. 5 is a schematic top view of the carriage assembly of FIG. 1;
FIG. 6 is a schematic structural view of a landing gear wheel clamping assembly;
fig. 7 is a schematic structural view of a wheel clamping assembly of the half-wheel fork landing frame.
In the drawings: 1. a vertical loading assembly; 2. clamping the assembly; 3. a load bearing assembly; 4. an airborne component; 5. a side-loading assembly; 6. forming a frame; 7. a pull wire sensor; 8. connecting a bracket; 2-1 loading a flange plate; 2-2 a top plate; 2-3 reinforcing plates; 2-4, side plate; 2-5, linear guide rail; 2-6, sliding block; 2-7, a wheel flange plate; 3-1 side loading joint; 3-2 friction plates; 3-3 bearing plates; 3-4 sliding blocks; 3-5 guide rails; 3-6 fixing the plate.
Detailed Description
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. For convenience of description, the words "upper", "lower", "left" and "right" in the following description are used only to indicate the correspondence between the upper, lower, left and right directions of the drawings themselves, and do not limit the structure.
As shown in fig. 1 to 3, the landing gear wheel static test loading device provided by the embodiment includes a jig frame 6, a clamping assembly 2 for mounting a landing gear wheel, a vertical loading assembly 1 for applying a radial load to the landing gear wheel mounted in the clamping assembly 2, a side loading assembly 5 for applying a lateral load to the landing gear wheel mounted in the clamping assembly 2, a navigation loading assembly 4 for applying a heading load to the landing gear wheel mounted in the clamping assembly 2, and a pull wire sensor 7 for collecting a compression amount of the landing gear wheel.
The vertical loading assembly 1 is vertically arranged, the upper end of the vertical loading assembly 1 is connected with the profile frame 6, and the lower end of the vertical loading assembly 1 is connected with the clamping assembly 2. The clamping assembly 2 is arranged on the corresponding position of the fixture 6 through a connecting support 8.
And a bearing component 3 is arranged on the fixture 6, and the bearing component 3 is positioned below the clamping component 2. The side-carrying component 5 and the aerial-carrying component 4 are both horizontally arranged on the jig 6, wherein the side-carrying component 5 is arranged on two opposite sides of the bearing component 3, and the aerial-carrying component 4 is arranged on one side of the bearing component 3 and is perpendicular to the side-carrying component 5.
And loading points are arranged at two ends of the bearing component 3, and the two loading points are respectively connected with the side loading component 5, or one loading point is connected with the aerial loading component 4, and the other loading point is not connected.
In this embodiment, the vertical loading assembly 1, the lateral loading assembly 5 and the aerial loading assembly 4 are all servo electric cylinders or servo hydraulic cylinders, and cylinder barrels of the servo electric cylinders or servo hydraulic cylinders are all connected with the section frame 6. The aerial carrying component 4 is connected with the bearing component 3 through a steel wire rope.
The stay wire sensor 7 is vertically connected between the jig 6 and an undercarriage wheel installed in the clamping assembly 2.
As shown in fig. 1, 4 and 5, the bearing assembly 3 comprises a side bearing joint 3-1, a friction plate 3-2, a bearing plate 3-3, a first slide block 3-4, a first guide rail 3-5 and a fixed plate 3-6.
The fixed plate 3-6 is connected with the fixture 6, the first guide rail 3-5 is arranged on the fixed plate 3-6, and the first sliding block 3-4 is connected with the first guide rail 3-5 in a sliding mode. The first guide rails 3-5 ensure good guidance for side loading. The force bearing plate 3-3 is fixedly connected with the first sliding block 3-4, and the friction plate 3-2 is overlapped at the upper end of the force bearing plate 3-3 through a screw 3-3, so that the friction plate 3-2 is in fit contact with the force bearing plate 3-3. The friction plate 3-2 and the bearing plate 3-3 are provided with the side-load joints 3-1 at two ends, and the side-load joints 3-1 are arranged in the sliding direction of the first slide block 3-4 along the first guide rail 3-5. The side load joint 3-1 is the load point. The bearing component 3 is fixed with the fixture 6 through the fixing plates 3-6 by bolts.
When the radial load test is carried out, the installation direction of the bearing component 3 is turned, and the side load joint 3-1 is close to the aerial load component 4. And connecting the side-loading joint 3-1 close to the aerial carrier component 4 with the aerial carrier component 4 through a steel wire rope, and disconnecting the other side-loading joint 3-1 (shown in figure 2).
When the radial-lateral combined load test is carried out, the installation direction of the load bearing component 3 is turned again, so that the side load joint 3-1 is close to the side load component 5. The side-loading joints 3-1 on both sides are respectively connected with the corresponding side-loading assemblies 5 (shown in figure 3).
Two first guide rails 3-5 are arranged on the fixing plate 3-6 at intervals, and two first sliding blocks 3-4 are matched on each first guide rail 3-5.
The radial load of the bearing assembly 3 is applied through the wheel on the vertical load assembly 1 and the clamping assembly 2, and the inner side and the outer side loads are applied through the friction force generated between the friction plate 3-2 and the wheel tire by pulling the friction plate 3-2 of the bearing assembly 3 through the side load joint 3-1 of the side load assembly 5.
As shown in fig. 6, in an embodiment, the clamping assembly 2 is an inverted U-shaped structure, a U-shaped cavity for mounting the wheel of the landing gear is formed in the clamping assembly, a wheel fork of the landing gear is simulated, and a real working condition of bilateral loading of the wheel fork is realized.
The clamping assembly 2 comprises a loading flange 2-1, a top plate 2-2, side plates 2-4, a second guide rail 2-5, a second sliding block 2-6 and a wheel flange 2-7 for mounting the undercarriage wheels. The top of the loading flange 2-1 is connected with the vertical loading assembly 1, the bottom of the loading flange 2-1 is connected with the top plate 2-2, and the side plates 2-4 are vertically arranged at two ends of the top plate 2-2, so that an inverted U-shaped structure is formed between the side plates 2-4 and the top plate 2-2, and the U-shaped cavity is formed in the U-shaped structure.
The outer side walls, far away from the U-shaped cavity, of the two side plates 2-4 are vertically provided with the second guide rails 2-5, each second guide rail 2-5 is connected with the second sliding block 2-6 in a sliding mode, the second sliding blocks 2-6 are connected with the connecting support 8 through bolts, and the connecting support 8 is connected with the profile frame 6 through bolts. The second guide rails 2-5 on the two side plates 2-4 give good guidance for radial loading.
The airplane wheel flange plates 2-7 are arranged on the inner side wall, close to the U-shaped cavity, of the side plate 2-4. The landing gear wheels for test loading are mounted on the wheel flanges 2-7.
In another embodiment, as shown in fig. 7, the gripper assembly 2 is an inverted L-shaped structure, in which an L-shaped cavity for mounting the wheel of the landing gear is formed. The clamping assembly 2 comprises a loading flange 2-1, a top plate 2-2, a reinforcing plate 2-3, a side plate 2-4, a second guide rail 2-5, a second sliding block 2-6 and a wheel flange 2-7 for mounting the undercarriage wheels. The top of the loading flange 2-1 is connected with the vertical loading assembly 1, the bottom of the loading flange 2-1 is connected with the top plate 2-2, and the side plate 2-4 is vertically arranged at one end of the top plate 2-2, so that an inverted L-shaped structure is formed between the side plate 2-4 and the top plate 2-2, and the inside of the inverted L-shaped structure is provided with an L-shaped cavity.
The reinforcing plate 2-3 is connected between the top plate 2-2 and the side plate 2-4, and reinforces the connecting structure of the top plate 2-2 and the side plate 2-4.
The outer side wall, far away from the L-shaped cavity, of the side plate 2-4 is vertically provided with the second guide rail 2-5, the second guide rail 2-5 is connected with the second sliding block 2-6 in a sliding mode, the second sliding block 2-6 is connected with the connecting support 8 through bolts, and the connecting support 8 is connected with the profile frame 6 through bolts. The airplane wheel flange plates 2-7 are arranged on the inner side wall, close to the L-shaped cavity, of the side plate 2-4.
The radial load test and the radial-lateral load test are exemplified by a half-wheel fork landing gear wheel.
As shown in FIG. 2, in a radial loading test of a semi-fork static tester wheel, a vertical load assembly 1, a load bearing assembly 3 and a navigation load assembly 4 are installed on a jig 6, and radial load and heading load are applied by two servo cylinders. The joint of a servo cylinder of the vertical loading component 1 is connected with a 2-1 loading flange plate and the clamping component 2, and the side loading joint 3-1 of the bearing component 3 is connected with the aerial loading component 4 through a steel wire rope.
As shown in figure 3, the wheel of the half-wheel fork machine is loaded with radial-lateral combined load, a vertical load assembly 1, a bearing assembly 3 and a lateral load assembly 4 are arranged on a frame 6, the radial load and the internal and external lateral loads are applied by three servo cylinders, a joint of the servo cylinder of the vertical load assembly 1 and a 2-1 loading flange plate are connected with a clamping assembly 2, and the bearing assembly 3 is connected with the lateral load assembly 4 through two lateral load joints 3-1.
Based on the description of the mechanical structure and the working principle of the device, the specific implementation steps are as follows:
s1, judging whether a wheel fork of the undercarriage is a wheel fork or a single wheel fork according to a test piece and a static test requirement, wherein a wheel fork wheel clamping assembly adopts an inverted U-shaped structure formed by a top plate and a side plate and simulates the two-side loading real working condition of the undercarriage; two first guide rails 2-5 are arranged on the two side plates 2-4 of the two side plates to ensure that radial loading has good guidance. And arranging, designing and installing fixture tools. The semi-wheel fork machine wheel is loaded with radial-lateral combined loads, the vertical load assembly 1, the bearing assembly 3 and the lateral load assembly 4 are arranged on a profile frame 6, the radial loads and the internal and external lateral loads are applied by three servo cylinders, a joint of the servo cylinder of the vertical load assembly 1 is connected with a 2-1 loading flange plate and a clamping assembly 2, and the bearing assembly 3 is connected with the lateral load assembly 4 through two lateral load joints 3-1.
S2, mounting a test fixture and debugging and mounting the servo cylinder, wherein in order to ensure loading accuracy, field testing personnel measure the verticality and the levelness of the servo cylinder by using a levelmeter before testing and adjust the verticality and the levelness within a control range.
And S3, before starting a radial load test and a radial-lateral combined load test, calibrating friction force. The radial load is directly applied through a radial loading cylinder, and the side load is applied through the friction force generated between the friction plate 3-2 and the wheel by pulling the bearing assembly 3 through the side load assembly 5. However, when a side load is applied, two sets of ball guide rails exist between the bearing component 3 and the fixed plates 3-6, and a friction force f in the opposite direction also exists, so that the friction force of the first guide rail 3-5 in the bearing component 3 is calibrated before a test.
And S4, starting a radial load test. Adjusting the bearing component 3 to enable a side load joint 3-1 of the bearing component 3 to be connected with the aerial load component 4 and fixed on the jig 6, applying radial load to the airplane wheel step by step through a servo cylinder by the vertical load component 1, acquiring the tire compression amount in real time by the stay wire sensor 7, and applying calculated course load to the aerial load component 4 to check whether the airplane wheel rotates flexibly when 80%, 90% and 100% of loads are applied.
And S5, starting a radial-lateral combined load test. And adjusting the bearing assembly to enable the side load joint 3-1 of the bearing assembly 3 to be connected with the side load assembly 5 and fixed on the jig 6, wherein the radial load is applied through a servo cylinder of the vertical load assembly 1, and the inner side and the outer side loads are applied through the friction force generated between the friction plate 3-2 and the wheel tire by pulling the friction plate 3-2 of the bearing assembly 3 through the side load assembly 5. And the radial load and the side load are loaded in a coordinated manner in the combined radial-side load working condition.
And S6, completing the test.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The landing gear wheel static test loading device is characterized by comprising a jig (6), a clamping assembly (2) for mounting a landing gear wheel, a vertical loading assembly (1) for applying a radial load to the landing gear wheel mounted in the clamping assembly (2), a side loading assembly (5) for applying a lateral load to the landing gear wheel mounted in the clamping assembly (2), and an aviation loading assembly (4) for applying a heading load to the landing gear wheel mounted in the clamping assembly (2); the vertical loading assembly (1) is vertically arranged, the upper end of the vertical loading assembly (1) is connected with the profile frame (6), and the lower end of the vertical loading assembly (1) is connected with the clamping assembly (2); the clamping assembly (2) is arranged on the corresponding position of the fixture (6) through a connecting support (8);
a bearing component (3) is arranged on the fixture (6), and the bearing component (3) is positioned below the clamping component (2); the side loading assembly (5) and the aerial loading assembly (4) are both horizontally arranged on the fixture (6), wherein the side loading assembly (5) is arranged on two opposite sides of the bearing assembly (3), and the aerial loading assembly (4) is arranged on one side of the bearing assembly (3) and is vertical to the side loading assembly (5);
and loading points are arranged at two ends of the bearing component (3), and the two loading points are respectively connected with the side loading component (5), or one of the loading points is connected with the navigation loading component (4).
2. The landing gear wheel static test loading device for the landing gear according to claim 1, wherein the bearing assembly (3) comprises a side bearing joint (3-1), a friction plate (3-2), a bearing plate (3-3), a first sliding block (3-4), a first guide rail (3-5) and a fixing plate (3-6); the fixed plate (3-6) is connected with the fixture (6), the first guide rail (3-5) is arranged on the fixed plate (3-6), and the first sliding block (3-4) is in sliding connection with the first guide rail (3-5); the bearing plate (3-3) is fixedly connected with the first sliding block (3-4), and the friction plate (3-2) is overlapped at the upper end of the bearing plate (3-3); the two ends of the friction plate (3-2) and the force bearing plate (3-3) are respectively provided with the side-load joint (3-1), and the side-load joint (3-1) is arranged in the sliding direction of the first sliding block (3-4) along the first guide rail (3-5); the side load joint (3-1) is the load point.
3. The landing gear wheel static test loading device according to claim 2, wherein the number of the first guide rails (3-5) on the fixing plates (3-6) is two, and two first sliding blocks (3-4) are matched on each first guide rail (3-5).
4. The landing gear wheel static test loading device for the landing gear according to claim 1, is characterized in that the vertical loading assembly (1), the side loading assembly (5) and the aerial loading assembly (4) are all servo electric cylinders or servo hydraulic cylinders, and cylinder barrels of the servo electric cylinders or servo hydraulic cylinders are all connected with the jig (6); the aerial load component (4) is connected with the bearing component (3) through a steel wire rope.
5. The landing gear wheel static test loading device according to claim 1, characterized by further comprising a pull wire sensor (7) for collecting the compression amount of the landing gear wheel, wherein the pull wire sensor (7) is vertically connected between the jig frame (6) and the landing gear wheel installed in the clamping assembly (2).
6. A loading device for a static test of a wheel of a landing gear according to any one of claims 1 to 5, characterized in that the clamping assembly (2) is of an inverted U-shaped structure, and a U-shaped cavity for mounting a wheel of the landing gear is formed in the clamping assembly.
7. The landing gear wheel static test loading device according to claim 6, wherein the clamping assembly (2) comprises a loading flange (2-1), a top plate (2-2), a side plate (2-4), a second guide rail (2-5), a second sliding block (2-6) and a wheel flange (2-7) for mounting a landing gear wheel; the top of the loading flange plate (2-1) is connected with the vertical loading assembly (1), the bottom of the loading flange plate (2-1) is connected with the top plate (2-2), the side plates (2-4) are vertically arranged at two ends of the top plate (2-2), an inverted U-shaped structure is formed between the side plates (2-4) and the top plate (2-2), and the U-shaped cavity is formed inside the inverted U-shaped structure; the outer side walls, far away from the U-shaped cavity, of the two side plates (2-4) are vertically provided with second guide rails (2-5), each second guide rail (2-5) is connected with a second sliding block (2-6) in a sliding mode, and the second sliding blocks (2-6) are connected with the connecting support (8); the airplane wheel flange plates (2-7) are arranged on the inner side wall, close to the U-shaped cavity, of the side plates (2-4).
8. A loading device for a static test of a wheel of a landing gear according to any one of claims 1 to 5, characterized in that the clamping assembly (2) is of an inverted L-shaped structure, and an L-shaped cavity for mounting a wheel of the landing gear is formed in the clamping assembly.
9. The landing gear wheel static test loading device according to claim 8, wherein the clamping assembly (2) comprises a loading flange (2-1), a top plate (2-2), a side plate (2-4), a second guide rail (2-5), a second sliding block (2-6) and a wheel flange (2-7) for mounting a landing gear wheel; the top of the loading flange plate (2-1) is connected with the vertical loading assembly (1), the bottom of the loading flange plate (2-1) is connected with the top plate (2-2), and the side plate (2-4) is vertically arranged at one end of the top plate (2-2), so that an inverted L-shaped structure is formed between the side plate (2-4) and the top plate (2-2), and the interior of the inverted L-shaped structure is provided with an L-shaped cavity; the second guide rail (2-5) is vertically arranged on the outer side wall, away from the L-shaped cavity, of the side plate (2-4), the second guide rail (2-5) is connected with the second sliding block (2-6) in a sliding mode, and the second sliding block (2-6) is connected with the connecting support (8); the airplane wheel flange plates (2-7) are arranged on the inner side wall, close to the L-shaped cavity, of the side plates (2-4).
10. A landing gear wheel static test loading method is carried out by using the landing gear wheel static test loading device according to any one of claims 1 to 9, and is characterized by comprising the following steps:
firstly, mounting an undercarriage airplane wheel on a clamping assembly (2), and calibrating friction force before performing a radial load test and a radial-lateral combined load test;
step two, starting a radial load test: adjusting the direction of the bearing component (3) to ensure that the loading point at one end of the bearing component is connected with the aerial carrier component (4) and the loading point at the other end of the bearing component is not connected, and fixing the bearing component (3) on the fixture (6); radial loads are applied step by step through the vertical loading assembly (1), the compression amount of the airplane wheel is collected in real time, and the calculated course load is applied to the aerial loading assembly (4) to check whether the airplane wheel rotates flexibly;
step three, starting a radial-lateral combined load test: adjusting the direction of the bearing component (3) to ensure that loading points at two ends of the bearing component (3) are respectively connected with the side loading component (5) and the bearing component (3) is fixed on the fixture (6); radial load is applied through the vertical load assembly (1), and the friction force generated between the friction plate (3-2) and the tire of the airplane wheel is applied by pulling the friction plate (3-2) of the load-bearing assembly (3) through the side load assembly (5) under the condition that the inner side load and the outer side load are applied; the radial load and the lateral load are in coordinated loading in the radial-lateral combined load working condition;
and step four, completing the test.
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| CN112340061B (en) | 2022-10-04 |
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