A front landing gear structure bearing test device

Abstract

The present invention discloses a bearing test device for a front landing gear structure, which includes a test bench, and a test piece is installed on the test bench; a dummy wheel fixture is assembled on the test piece, and the dummy wheel fixture is of a double L-shaped structure. A pair of first pull tabs and a pair of second pull tabs are installed on the two L-shaped structures. A plurality of load interfaces are provided on both the first pull tab and the second pull tab, and a lateral load interface is provided on the first pull tab. The load interfaces of the first pull tab and the second pull tab are configured to receive force loading in at least three directions; a plurality of loading actuators are distributed based on a preset direction. The loading actuators are used for loading, and the execution ends of the actuators in each direction are connected to the corresponding interfaces, which can achieve simultaneous loading in three directions at two loading points with only three actuators. This not only reduces the required number of actuators, but also solves the problem of loading accuracy caused by too small load at a single loading point.

Description

Technical Field

[0001] The present invention relates to the technical field of front landing gear test, and particularly to a structural bearing test device for a front landing gear. Background Art

[0002] The load-bearing structure of a reusable aircraft fuselage 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 its load-bearing structure play a crucial role in the takeoff and landing process of the aircraft.

[0003] As one of the key systems of a horizontal recovery launch vehicle, the front landing gear system is the prerequisite and foundation for ensuring the reusability of the launch vehicle. Different from the vertical landing method, a horizontally landing launch vehicle not only has a vertical sinking speed but also has a very high horizontal landing speed. Therefore, it is necessary to absorb both vertical energy and horizontal energy simultaneously. The front landing gear is an important part of a reusable aircraft and is the component for the aircraft to interact with the ground, undertaking important functions during the aircraft reentry process.

[0004] Currently, the front landing gear components of reusable aircraft are all made of metal materials, and ultra-high-strength steel is a type of material widely used in the manufacture of front landing gears. However, the repeated large impact loads during the operation of reusable aircraft have a great impact on the yield strength, ultimate tensile strength, and fracture failure of ultra-high-strength steel. This severe loading method will further affect the load-bearing capacity and durability of the ultra-high-strength steel components of the aircraft, and then cause the aircraft to lose its working ability. Therefore, in order to be able to horizontally recover the launch vehicle and ensure the safety of aircraft use, it is necessary to study the structural bearing strength of the front landing gear. Summary of the Invention

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

[0006] To solve the above technical problems, the present invention adopts the following technical solutions: A structural bearing test device for a front landing gear, comprising:

[0007] A test bench, on which a test piece is installed;

[0008] A dummy wheel fixture, assembled on the test piece. The dummy wheel fixture is of 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 both the first pull tabs and the second pull tabs, and a lateral load interface is provided on the first pull tab. The load interfaces of the first pull tabs and the second pull tabs are configured to receive force loading in at least three directions;

[0009] A number of loading actuators, distributed based on a preset direction, are used for loading, and the execution ends of the actuators in each direction are connected to corresponding interfaces.

[0010] Preferably, the test piece includes a wheel axle, a rotating sleeve, a strut, a retracting actuator, and a strut rod. The wheel axle is installed at one end of the strut, and the other end of the strut is movably connected to the test bench through the retracting actuator. The rotating sleeve is coaxially sleeved on the strut, and the strut rod is obliquely supported between the strut and the test bench.

[0011] Preferably, an outer cylinder fixture is installed on the test bench. The outer cylinder fixture includes a pair of triangular support plates, and the two triangular support plates are connected by a reinforcing rib. The retracting actuator is movably connected to the triangular support plate.

[0012] Preferably, anti-rotation plates are installed on both the first L-shaped component and the second L-shaped component. A convex 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. After the convex structure is configured to engage with the wheel axle, it restricts the first L-shaped component and the second L-shaped component from rotating around the axis of the wheel axle.

[0013] Preferably, at least two vertical load interfaces are provided on the first pull tab, and at least two lateral load interfaces are provided on the second pull tab.

[0014] Preferably, a first vertical load interface and a second vertical load interface are provided on the first pull tab, and a first lateral load interface and a second lateral load interface are provided on the second pull tab; and

[0015] The force distribution between the first vertical load interface and the first lateral load interface is 50-50, and the force distribution between the second vertical load interface and the second lateral load interface is 30-70.

[0016] Preferably, the loading actuators include a lateral loading actuator, a vertical loading actuator, and a lateral 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 lateral loading actuator is connected to one of the lateral load interfaces; and

[0017] The three loading actuators are configured to load the first L-shaped component and the second L-shaped component in three directions simultaneously.

[0018] Preferably, the device further 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 number of pairs of installation positions are provided along the vertical direction on the installation surfaces of the front beam and the rear beam. Both ends of the top beam are installed on any pair of installation positions, and loading actuators are installed on the side beam, the top beam, and the rear beam.

[0019] Preferably, one end of the loading actuator is connected to the beam support through a universal joint, and the other end is connected to the load interface through a spherical bearing.

[0020] Advantages: In the present invention, a double-L structure is adopted and connected by four tabs, which can achieve simultaneous loading in three directions at two loading points with only three actuators. This not only reduces the required number of actuators but also solves the problem of loading accuracy caused by too small a load at a single loading point. Among them, the setting and distribution of each load interface can simulate from multiple directions and levels, improve data diversity, and better fit the actual situation of the aircraft.

[0021] In addition, through the setting of the anti-rotation piece, a convex structure is provided on the anti-rotation piece. When the dummy wheel fixture is sleeved on the wheel axle at the angle required by the working condition and the position of the dummy wheel fixture is adjusted, the convex structure on the anti-rotation piece engages with the wheel axle, so that the dummy wheel fixture will not rotate around the axis of the wheel axle, improving the simulation accuracy.

[0022] In the present invention, one end of the loading actuator adopts the form of a universal joint, and the other end adopts the form of a spherical bearing, which can achieve stable loading of the load and ensure that the load direction does not change under small deformation conditions. Cooperating with the beam support, it provides support when the load direction changes, improving the load-bearing capacity and stability of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention.

[0024] In the drawings:

[0025] Figure 1 is the three-dimensional overall structural axonometric view of the device of the present invention;

[0026] Figure 2 is the three-dimensional structural axonometric view of the dummy wheel fixture in the present invention;

[0027] Figure 3 is the structural schematic diagram of the test piece in the present invention;

[0028] Figure 4 is the axonometric view of the loading state of the dummy wheel fixture under normal working conditions;

[0029] Figure 5 is the axonometric view of the installation of the outer cylinder fixture.

[0030] In the figure: 1. Test bench; 2. Side beam; 3. Front beam; 4. Top beam; 5. Rear beam; 6. Test piece; 7. Outer cylinder fixture; 8. Strut fixture; 9. False wheel fixture; 10. Heading loading actuator; 11. Lateral loading actuator; 12. Vertical loading actuator; 13. Protruding 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 axle; 20. Rotating sleeve; 21. Strut; 22. Retracting and extending actuator; 23. Strut; 24. First L-shaped component; 25. Second L-shaped component; 26. First pull tab; 27. Second pull tab; 28. Anti-rotation tab. Detailed implementation mode

[0031] The embodiments of the present invention will be described below in conjunction with the accompanying drawings in the embodiments of the present invention. The terms used in the implementation part 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 will be described below in conjunction with the drawings.

[0032] As Figure 1 shown, a front landing gear structure bearing test device includes a test bench 1 and a beam support frame. The beam support frame includes 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 surface 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 fixture 7 is arranged on the test bench 1, a test piece 6 is clamped on the outer cylinder fixture 7, a false wheel fixture 9 is installed on the test piece 6, and loading actuators for loading the false wheel fixture 9 are arranged on the top beam 4, the rear beam 5 and the side beam 2;

[0033] For the false wheel fixture, refer to Figure 2 shown, the false wheel fixture 9 is of 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 number of load interfaces are opened on the first pull tab 26 and the second pull tab 27, and a lateral load interface is opened on the first pull tab 26. The load interfaces of the first pull tab 26 and the second pull tab 27 and the lateral load interface 18 are configured to receive force loading in at least three directions.

[0034] For the test piece, refer to Figure 3As shown, the test piece 6 includes a wheel axle 19, a rotating sleeve 20, a strut 21, a retraction and extension actuator 22, and a strut 23. The wheel axle 19 is installed at one end of the strut 21. The other end of the strut 21 is movably connected to the test bench 1 through the retraction and extension actuator 22. The rotating sleeve 20 is coaxially sleeved on the strut 21. The strut 23 is obliquely supported between the strut 21 and the test bench 1, and the strut 23 is fixed to the test bench 1 through a strut clamp 8. Refer to Figure 5 As shown, an outer cylinder clamp 7 is installed on the test bench 1. The outer cylinder clamp 7 includes a pair of triangular support plates, and the two triangular support plates are connected by a reinforcing rib. The retraction and extension actuator is movably connected to the triangular support plate.

[0035] Among them, refer to Figure 4 As shown, anti-rotation pieces 28 are installed on both the first L-shaped part 24 and the second L-shaped part 25. A convex structure 13 is provided inside the anti-rotation piece 28. The wheel axle 19 is inserted between the first L-shaped part 24 and the second L-shaped part 25. After the convex structure 13 is configured to engage with the wheel axle 19, it restricts the first L-shaped part 24 and the second L-shaped part 25 from rotating around the axis of the wheel axle 19.

[0036] Among them, in a specific embodiment 1, at least two vertical load interfaces are provided on the first tab 26, and at least two course load interfaces are provided on the second tab 27.

[0037] Among them, in a specific embodiment 2, refer to Figure 2 As shown, a first vertical load interface 14 and a second vertical load interface 15 are provided on the first tab 26, and a first course load interface 16 and a second course load interface 17 are provided on the second tab 27; and the force distribution of the first vertical load interface 14 and the first course load interface 16 is fifty-fifty, and the force distribution of the second vertical load interface 15 and the second course load interface 17 is thirty-seventy.

[0038] Based on the above, refer to Figure 1 As shown, the loading actuator includes a lateral loading actuator 11, a vertical loading actuator 12, and a course 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 course loading actuator 10 is connected to one of the course load interfaces; and the three loading actuators are configured to load the first L-shaped part 24 and the second L-shaped part 25 in three directions at the same time; refer to Figure 1As shown in the figure, a lateral loading actuator 11, a vertical loading actuator 12, and a yaw loading actuator 10 are respectively installed on the side beam 2, the top beam 4, and the rear beam 5. One end of the yaw loading actuator 10 is fixed to the rear beam 5 through a universal joint, and the other end is hinged to the first yaw load interface 16 or the second yaw load interface 17 of the dummy wheel fixture 9 through a fish-eye 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 fish-eye 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 fish-eye bearing.

[0039] During the test: Install the test bench according to the front landing gear loading condition. Fix the front landing gear to the test bench through the strut fixture 8 and the outer cylinder fixture 7, so that the axis of the wheel axle 19 is consistent with the loading axis of the vertical loading actuator 12; put the dummy wheel fixture 9 on the wheel axle 19 at the angle required by the working condition, and adjust the position of the dummy wheel fixture 9 so that the convex structure 13 on the anti-rotation piece 28 engages with the wheel axle 19, so that the dummy wheel fixture 9 will not rotate around the axis of the wheel axle 19; install and fix the loading actuators in three directions (vertical, yaw, and lateral) through the base and bolts respectively, and ensure that the axis direction of the actuator is consistent with the three load directions required to be loaded on the wheel axle 19; fix the displacement gauges according to the test requirements, check and record the measurement directions and measurement positions of each displacement gauge, and preliminarily judge whether the displacement at the measurement position will exceed the range; apply loads according to the load application requirements corresponding to the working condition and the task book, including yaw load, vertical load, and lateral load; after each structural loading test working condition is completed, take pictures to record the state of the test piece. If no cracks or damages appear on the test piece, then conduct the next working condition test until all working condition tests are completed.

[0040] Overall, the bases of the loading actuators in three directions (vertical, yaw, and lateral) adopt the form of universal joints, and the ends adopt the form of fish-eye bearings, which can realize stable load loading and ensure that the load direction does not change under small deformation conditions; the support between the top beam 4 and the front beam 3 and the rear beam 5 adopts the form of studs as shown in Figure 1 the figure, which can conveniently adjust the height of the top beam up and down, and give support when the load direction changes, improving the bearing capacity and stability of the structure.

[0041] The embodiments of the present invention have been described in detail above in conjunction with the accompanying drawings. However, the present invention is not limited to the above embodiments. For those of ordinary skill in the art in this technical field, after learning the content recorded in the present invention, without departing from the principle of the present invention, several equivalent transformations and substitutions can still be made, and these equivalent transformations 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; The test piece includes a wheel shaft, a rotating sleeve, a pillar, a retractable actuator and a strut, the wheel shaft is mounted on 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; The test bench is equipped with an outer cylinder fixture, which includes a pair of triangular support plates, the two triangular support plates are connected by reinforcing ribs, and the retractable actuator is movably connected to the triangular support plates; The first L-shaped component and the second L-shaped component are both provided with a rotation-stopping plate, wherein a protruding structure is provided inside the rotation-stopping plate, the machine wheel axle is inserted between the first L-shaped component and the second L-shaped component, and the protruding structure is configured to restrict the first L-shaped component and the second L-shaped component from rotating around the axis of the machine wheel axle after being engaged with the machine wheel axle; 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; 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 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; 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.

2. A front landing gear structure load-bearing test device according to claim 1, 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.

3. A front landing gear structure load-bearing test device according to claim 2, 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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