Bearing test device for front landing frame structure

Abstract

The invention discloses a front landing frame structure bearing test device which comprises a test bed, and a test piece is installed on the test bed. The false wheel clamp is assembled on a test piece and is of a double-L-shaped structure, a pair of first pull pieces and a pair of second pull pieces are installed on the two L-shaped structures, a plurality of load interfaces are formed in the first pull pieces and the second pull pieces, lateral load interfaces are formed in the first pull pieces, and lateral load interfaces are formed in the second pull pieces. The load interface combination of the first pull piece and the second pull piece is configured to receive stress loads in at least three directions; the loading actuator cylinders are distributed based on the preset direction, the loading actuator cylinders are used for loading, the execution ends of the actuator cylinders in all the directions are connected with the corresponding interfaces, simultaneous loading of two loading points in three directions can be achieved only through three actuator cylinders, the number of the required actuator cylinders is reduced, and the loading efficiency is improved. And the problem of low loading precision caused by too small load of a single loading point is solved.

Description

Technical Field

[0001] The invention relates to the technical field of front landing gear testing, and in particular to a front landing gear structure load-bearing testing device. Background Art

[0002] The load-bearing structure of a reusable aircraft body not only needs to withstand the vibration and impact of the engine, but also needs to adapt to the load environment from the aircraft. The effectiveness and life of the load-bearing structure play a vital role in the aircraft's take-off and landing process.

[0003] As one of the key systems of the horizontal recovery vehicle, the front landing gear system is the premise and basis for ensuring the reusability of the vehicle. Unlike the vertical landing method, the horizontal landing vehicle not only has a vertical sinking speed, but also has a very large horizontal landing speed, so it needs to absorb vertical energy and horizontal energy at the same time. The front landing gear is an important component of the reusable aircraft. It is the component that interacts with the ground and plays an important role in the aircraft's reentry process.

[0004] At present, the front landing gear components of reusable aircraft are all made of metal materials, among which ultra-high strength steel is a type of material widely used in the manufacturing process of the front landing gear. However, the repeated large impact loads in the operation of reusable aircraft have a great impact on the yield strength, tensile strength limit and fracture failure of ultra-high strength steel. This harsh loading mode will further affect the load-bearing capacity and durability of the aircraft's ultra-high strength steel components, and then cause the aircraft to lose its working ability. Therefore, in order to be able to horizontally recover the carrier and ensure the safety of the aircraft, it is necessary to study the structural load-bearing strength of the front landing gear. Summary of the invention

[0005] The purpose of the present invention is to provide a front landing gear structure load-bearing test device, which can effectively solve the problems existing in the above-mentioned prior art.

[0006] In order to solve the above technical problems, the present invention adopts the following technical solutions: a front landing gear structure load-bearing test device, comprising: A test bench, on which a test piece is installed; A dummy wheel fixture is assembled on the test piece, the dummy wheel fixture is a double L-shaped structure, including a first L-shaped component and a second L-shaped component, a pair of first pull tabs and a pair of second pull tabs are installed on the first L-shaped component and the second L-shaped component, a plurality of load interfaces are opened on the first pull tab and the second pull tab, and a lateral load interface is opened on the first pull tab, and the load interface combination of the first pull tab and the second pull tab is configured to receive force loading in at least three directions; A plurality of loading actuators are distributed based on preset directions. The loading actuators are used for loading, and the actuator ends of the actuators in each direction are connected to corresponding interfaces.

[0007] Preferably, the test piece includes a wheel axle, a rotating sleeve, a pillar, a retractable actuator and a strut, the wheel axle is installed at one end of the pillar, the other end of the pillar is movably connected to the test bench through the retractable actuator, the rotating sleeve is coaxially sleeved on the pillar, and the strut is supported at an oblique angle between the pillar and the test bench.

[0008] Preferably, an outer cylinder fixture is installed on the test bench, and the outer cylinder fixture includes a pair of triangular support plates, the two triangular support plates are connected by reinforcing ribs, and the retractable actuator cylinder is movably connected to the triangular support plates.

[0009] Preferably, the first L-shaped component and the second L-shaped component are both installed with a anti-rotation plate, and a protrusion structure is provided inside the anti-rotation plate. The wheel axle is inserted between the first L-shaped component and the second L-shaped component, and the protrusion structure is configured to limit the first L-shaped component and the second L-shaped component from rotating around the axis of the wheel axle after engaging with the wheel axle.

[0010] Preferably, at least two vertical load interfaces are provided on the first pull tab, and at least two axial load interfaces are provided on the second pull tab.

[0011] Preferably, the first pull tab is provided with a first vertical load interface and a second vertical load interface, and the second pull tab is provided with a first azimuth load interface and a second azimuth load interface; and The force distribution between the first vertical load interface and the first azimuth load interface is 50:50, and the force distribution between the second vertical load interface and the second azimuth load interface is 30:70.

[0012] Preferably, the loading actuator comprises a lateral loading actuator, a vertical loading actuator and a yaw loading actuator, the lateral loading actuator is connected to the lateral load interface, the vertical loading actuator is connected to one of the vertical load interfaces; the yaw loading actuator is connected to one of the yaw load interfaces; and The three loading rams are configured to load the first L-shaped component and the second L-shaped component in three directions simultaneously.

[0013] Preferably, the device also includes a beam support frame, which includes a side beam, a front beam, a top beam and a rear beam. The top beam is installed between the front beam and the rear beam, and a plurality of pairs of mounting positions are provided on the mounting surfaces of the front beam and the rear beam in the vertical direction. Both ends of the top beam are installed on any pair of mounting positions, and loading actuators are installed on the side beams, the top beam and the rear beam.

[0014] Preferably, one end of the loading actuator is connected to the beam support frame through a universal joint, and the other end is connected to the load interface through a fisheye bearing.

[0015] Beneficial effect: The double L structure is adopted in the present invention, which is connected by four pull-tabs, so that only three actuators are needed to load two loading points in three directions at the same time. This not only reduces the number of actuators required, but also solves the problem of loading accuracy caused by too small load on a single loading point; wherein, the setting and distribution of each load interface can be simulated from multiple directions and levels, thereby improving data diversity and being more in line with the actual situation of the aircraft.

[0016] In addition, through the setting of the anti-rotation plate, a protruding structure is provided on the anti-rotation plate, and the dummy wheel clamp can be mounted on the machine wheel axle at the angle required by the working conditions. The position of the dummy wheel clamp is adjusted so that the protruding structure on the anti-rotation plate engages with the machine wheel axle, so that the dummy wheel clamp will not rotate around the axis of the machine wheel axle, thereby improving the simulation accuracy.

[0017] In the present invention, one end of the loading actuator adopts a universal joint form, and the other end adopts a fisheye bearing form, which can realize stable load loading and ensure that the load direction does not change under small deformation conditions. In conjunction with the beam support frame, support is provided when the load direction changes, thereby improving the bearing capacity and stability of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0019] In the attached picture: Figure 1 It is a three-dimensional overall structural axial view of the device of the present invention; Figure 2 It is a three-dimensional structural axial view of the dummy wheel fixture of the present invention; Figure 3 It is a schematic diagram of the structure of the test piece in the present invention; Figure 4 This is the axis view of the loading state of the fake wheel fixture under normal working conditions; Figure 5 Mount the shaft view for the outer barrel clamp.

[0020] In the figure: 1. test bench; 2. side beam; 3. front beam; 4. top beam; 5. rear beam; 6. test piece; 7. outer tube fixture; 8. strut fixture; 9. dummy wheel fixture; 10. heading load actuator; 11. lateral load actuator; 12. vertical load actuator; 13. raised structure; 14. first vertical load interface; 15. second vertical load interface; 16. first heading load interface; 17. second heading load interface; 18. lateral load interface; 19. wheel shaft; 20. rotating sleeve; 21. pillar; 22. retractable actuator; 23. strut; 24. first L-shaped component; 25. second L-shaped component; 26. first pull tab; 27. second pull tab; 28. anti-rotation plate. DETAILED DESCRIPTION

[0021] The embodiments of the present invention are described below in conjunction with the drawings in the embodiments of the present invention. The terms used in the implementation mode of the present invention are only used to explain the specific embodiments of the present invention, and are not intended to limit the present invention. The embodiments of the present application are described below in conjunction with the drawings.

[0022] like Figure 1 As shown, a front landing gear structure load-bearing test device comprises a test bench 1 and a beam support frame, the beam support frame comprises a side beam 2, a front beam 3, a top beam 4 and a rear beam 5, the front beam 3 and the rear beam 5 are arranged at the front and rear ends of the test bench 1, the side beam 2 is arranged on one side of the test bench 1, the top beam 4 is installed at the top between the front beam 3 and the rear beam 5 and is arranged on the top of the test bench 1, an outer cylinder clamp 7 is arranged on the test bench 1, a test piece 6 is clamped on the outer cylinder clamp 7, a dummy wheel clamp 9 is installed on the test piece 6, and a loading actuator for loading the dummy wheel clamp 9 is arranged on the top beam 4, the rear beam 5 and the side beam 2; For dummy wheel fixtures, refer to Figure 2 As shown, the dummy wheel clamp 9 is a double L-shaped structure, including a first L-shaped component 24 and a second L-shaped component 25, a pair of first pull tabs 26 and a pair of second pull tabs 27 are installed on the first L-shaped component 24 and the second L-shaped component 25, a plurality of load interfaces are provided on the first pull tab 26 and the second pull tab 27, and a lateral load interface is provided on the first pull tab 26, and the load interfaces of the first pull tab 26 and the second pull tab 27 and the lateral load interface 18 are combined and configured to receive force loading in at least three directions.

[0023] For the test piece, refer to Figure 3 As shown, the test piece 6 includes a wheel shaft 19, a rotating sleeve 20, a support 21, a retractable actuator 22 and a strut 23. The wheel shaft 19 is mounted on one end of the support 21. The other end of the support 21 is movably connected to the test bench 1 through the retractable actuator 22. The rotating sleeve 20 is coaxially sleeved on the support 21. The strut 23 is supported at an oblique angle between the support 21 and the test bench 1. The strut 23 is fixed to the test bench 1 through a strut clamp 8. Figure 5As shown, an outer cylinder fixture 7 is installed on the test bench 1, and the outer cylinder fixture 7 includes a pair of triangular support plates, the two triangular support plates are connected by reinforcing ribs, and the retractable actuator cylinder is movably connected to the triangular support plates.

[0024] Among them, reference Figure 4 As shown, a stop plate 28 is installed on the first L-shaped component 24 and the second L-shaped component 25, a protrusion structure 13 is provided inside the stop plate 28, the wheel axle 19 is inserted between the first L-shaped component 24 and the second L-shaped component 25, and the protrusion structure 13 is configured to limit the rotation of the first L-shaped component 24 and the second L-shaped component 25 around the axis of the wheel axle 19 after engaging with the wheel axle 19.

[0025] In a specific embodiment 1, at least two vertical load interfaces are provided on the first pull tab 26 , and at least two axial load interfaces are provided on the second pull tab 27 .

[0026] Among them, in a specific embodiment 2, reference Figure 2 As shown, the first pull tab 26 is provided with a first vertical load interface 14 and a second vertical load interface 15, and the second pull tab 27 is provided with a first azimuth load interface 16 and a second azimuth load interface 17; and the force distribution of the first vertical load interface 14 and the first azimuth load interface 16 is 50:50, and the force distribution of the second vertical load interface 15 and the second azimuth load interface 17 is 30:70.

[0027] Based on the above, reference Figure 1 As shown, the loading actuator includes a lateral loading actuator 11, a vertical loading actuator 12 and a yaw loading actuator 10, the lateral loading actuator 11 is connected to the lateral load interface 18, the vertical loading actuator 12 is connected to one of the vertical load interfaces; the yaw loading actuator 10 is connected to one of the yaw load interfaces; and the three loading actuators are configured to load the first L-shaped component 24 and the second L-shaped component 25 in three directions at the same time; refer to Figure 1 As shown, a lateral loading actuator 11, a vertical loading actuator 12 and a heading loading actuator 10 are respectively installed on the side beam 2, the top beam 4 and the rear beam 5. One end of the heading loading actuator 10 is fixed to the rear beam 5 through a universal joint, and the other end is hinged to the first heading load interface 16 or the second heading load interface 17 of the dummy wheel fixture 9 through a fisheye bearing; one end of the vertical loading actuator 12 is fixed to the top beam 4 through a universal joint, and the other end is hinged to the first vertical load interface 14 or the second vertical load interface 15 of the dummy wheel fixture 9 through a fisheye bearing; one end of the lateral loading actuator 11 is fixed to the side beam 2 through a universal joint, and the other end is hinged to the lateral load interface 18 of the dummy wheel fixture 9 through a fisheye bearing; During the test: install the test bench according to the front landing gear loading condition, fix the front landing gear on the test bench through the strut clamp 8 and the outer cylinder clamp 7, so that the axis of the wheel shaft 19 is consistent with the loading axis of the vertical loading actuator 12; put the dummy wheel clamp 9 on the wheel shaft 19 according to the angle required by the working condition, adjust the position of the dummy wheel clamp 9, so that the protruding structure 13 on the anti-rotation plate 28 is engaged with the wheel shaft 19, so that the dummy wheel clamp 9 will not rotate around the axis of the wheel shaft 19; respectively install the loading actuators in three directions (vertical, heading, and lateral) through the base and bolts. Install and fix, and ensure that the axis direction of the actuator is consistent with the three load directions of the wheel shaft 19; fix the displacement meter according to the test requirements, check and record the measurement direction and measurement position of each displacement meter, and preliminarily judge whether the displacement of the measurement position will exceed the measuring range; apply the load according to the corresponding working conditions and load application requirements of the task book, including heading load, vertical load and lateral load; after each structural loading test condition is completed, take a photo to record the status of the test piece. If the test piece has no cracks or damage, proceed to the next working condition test until all working condition tests are completed.

[0028] The overall loading in three directions (vertical, heading, and lateral) is realized. The base of the actuator adopts a universal joint, and the end adopts a fisheye bearing, which can realize stable load loading and ensure that the load direction does not change under small deformation conditions; Figure 1 The top beam 4 shown is supported by studs between the front beam 3 and the rear beam 5, which can facilitate the adjustment of the upper and lower heights of the top beam and provide support when the load direction changes, thereby improving the bearing capacity and stability of the structure.

[0029] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. For ordinary technicians in this technical field, after knowing the contents recorded in the present invention, they can make several equivalent changes and substitutions without departing from the principle of the present invention. These equivalent changes and substitutions should also be regarded as belonging to the protection scope of the present invention.

Claims

1. A front landing gear structure load-bearing test device, characterized in that: include: A test bench, on which a test piece is installed; A dummy wheel fixture is assembled on the test piece, the dummy wheel fixture is a double L-shaped structure, including a first L-shaped component and a second L-shaped component, a pair of first pull tabs and a pair of second pull tabs are installed on the first L-shaped component and the second L-shaped component, a plurality of load interfaces are provided on the first pull tab and the second pull tab, and a lateral load interface is provided on the first pull tab, and the load interface combination of the first pull tab and the second pull tab is configured to receive force loading in at least three directions; A plurality of loading actuators are distributed based on preset directions. The loading actuators are used for loading, and the actuator ends of the actuators in each direction are connected to corresponding interfaces.

2. A front landing gear structure load-bearing test device according to claim 1, characterized in that: The test piece includes a wheel axle, a rotating sleeve, a pillar, a retractable actuator and a strut. The wheel axle is installed at one end of the pillar, and the other end of the pillar is movably connected to the test bench through the retractable actuator. The rotating sleeve is coaxially sleeved on the pillar, and the strut is supported at an oblique angle between the pillar and the test bench.

3. A front landing gear structure load-bearing test device according to claim 2, characterized in that: An outer cylinder fixture is installed on the test bench, and the outer cylinder fixture includes a pair of triangular support plates. The two triangular support plates are connected by reinforcing ribs, and the retractable actuator cylinder is movably connected to the triangular support plates.

4. A front landing gear structure load-bearing test device according to claim 2, characterized in that: The first L-shaped component and the second L-shaped component are both installed with a anti-rotation plate, and a protrusion structure is arranged inside the anti-rotation plate. The wheel axle is inserted between the first L-shaped component and the second L-shaped component. The protrusion structure is configured to limit the first L-shaped component and the second L-shaped component from rotating around the axis of the wheel axle after engaging with the wheel axle.

5. The front landing gear structure load-bearing test device according to claim 1, characterized in that: The first pull tab is provided with at least two vertical load interfaces, and the second pull tab is provided with at least two azimuth load interfaces.

6. A front landing gear structure load-bearing test device according to claim 5, characterized in that: The first pull tab is provided with a first vertical load interface and a second vertical load interface, and the second pull tab is provided with a first azimuth load interface and a second azimuth load interface; as well as The force distribution of the first vertical load interface and the first azimuth load interface is 50:50, and the force distribution of the second vertical load interface and the second azimuth load interface is 30:

70.

7. A front landing gear structure load-bearing test device according to claim 5, characterized in that: The loading actuator includes a lateral loading actuator, a vertical loading actuator and a yaw loading actuator, wherein the lateral loading actuator is connected to the lateral load interface, the vertical loading actuator is connected to one of the vertical load interfaces; and the yaw loading actuator is connected to one of the yaw load interfaces; as well as The three loading rams are configured to load the first L-shaped component and the second L-shaped component in three directions simultaneously.

8. A front landing gear structure load-bearing test device according to claim 7, characterized in that: The device also includes a beam support frame, which includes side beams, a front beam, a top beam and a rear beam. The top beam is installed between the front beam and the rear beam, and a plurality of pairs of mounting positions are provided on the mounting surfaces of the front beam and the rear beam in the vertical direction. Both ends of the top beam are installed on any pair of mounting positions, and loading actuators are installed on the side beams, the top beam and the rear beam.

9. A front landing gear structure load-bearing test device according to claim 8, characterized in that: One end of the loading actuator is connected to the beam support frame through a universal joint, and the other end is connected to the load interface through a fisheye bearing.

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