A front landing gear fatigue test device capable of adjusting the compression amount of a buffer strut

Abstract

The application provides a front landing gear fatigue test device capable of adjusting the compression amount of a buffer strut, and belongs to the technical field of front landing gear test. The device comprises: a support frame arranged on a test site and used for supporting a simulation test piece; a follow-up device installed on the support frame and used for hoisting the simulation test piece and transmitting the displacement force of a position control actuator in a loading assembly to the simulation test piece; a simulation test piece hoisted on the follow-up device; and a loading assembly used for applying a load with a predetermined compression amount to the buffer strut of the simulation test piece, and simultaneously applying a heading test load, a lateral test load and a vertical test load to the simulation test piece, so as to perform a fatigue test on the front landing gear. The front landing gear fatigue test device can complete the fatigue test on the front landing gear under the variable compression amount of the buffer strut.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing, and specifically relates to a fatigue testing device for nose landing gear with adjustable buffer strut compression. Background Technology

[0002] The nose landing gear is a crucial component of an aircraft structure, and its fatigue life is a key indicator of aircraft performance. Fatigue testing of the nose landing gear is the most important way to determine its fatigue life. During takeoff and landing, the aircraft experiences different loads under varying conditions, and the nose landing gear struts also experience different compression levels. During nose landing gear fatigue testing, vertical, directional, and lateral loads need to be applied to the nose landing gear while adjusting the compression level of the struts in a timely manner. Current nose landing gear fatigue testing involves mounting the nose landing gear on a support base with the fuselage end pointing downwards and the tire end pointing upwards. The support base is then fixed to the load-bearing ground of the test site. Vertical, directional, and lateral loads are applied at the nose landing gear wheel locations using struts and actuators. This testing method not only occupies a large area of ​​the load-bearing ground but also has poor loading accuracy, a low frequency of fatigue tests, and cannot adjust the compression level of the nose landing gear struts in a timely manner. Summary of the Invention

[0003] The purpose of this application is to provide a front landing gear fatigue testing device with adjustable buffer strut compression to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of this application is: a fatigue testing device for a nose landing gear with adjustable buffer strut compression, comprising:

[0005] A support frame, which is set on the test site, is used to support the simulated test specimen;

[0006] A follow-up device is installed on the support frame and is used to hoist the simulated test piece and transmit the displacement force of the position control actuator in the loading component to the simulated test piece;

[0007] A simulated test specimen, which is suspended on the follower device;

[0008] A loading assembly is used to apply a predetermined amount of compressive load to the buffer strut of the simulated test specimen, while simultaneously applying yaw, lateral, and vertical test loads to the simulated test specimen to conduct fatigue tests on the nose landing gear.

[0009] Preferably, the support frame includes a support base and a top frame. The support base includes a long crossbeam, a short crossbeam, a short column, and a long column. The long crossbeam, short crossbeam, and short column are fixedly connected to form a bottom frame structure. The bottom frame structure is fixed to the ground of the test site. The bottom of the long column is set on the bottom frame structure and is vertically arranged. The top frame has a main through hole in the middle for the position control actuator to pass through. The top frame is fixed to the top of the long column, thereby connecting with the long column to form an integral whole.

[0010] Preferably, the long crossbeam, short crossbeam, short column, long column and / or top frame are made of Q345 steel.

[0011] Preferably, the follower device includes a follower frame, a support base, a support connector, a follower beam, and a guide rail slider assembly. The upper side of the follower frame has a double-ear structure for connecting a position control actuator. The two sides of the double-ear structure are provided with through holes for the loading assembly to pass through. The support base is fixedly connected to the lower side of the follower frame. The support connector is fixedly installed below the support base for suspending the simulated test piece. The follower beam is fixedly installed on the edge of the follower frame. The guide rail slider assembly is slidably installed on the long column of the support frame. The follower beam is connected to the guide rail slider assembly, thereby enabling the follower frame to move along the height direction of the long column.

[0012] Preferably, the guide rail slider assembly includes a guide rail and a slider, the guide rail is fixedly mounted on a long column, and the slider is fixedly connected to the follower beam and slidably mounted on the guide rail.

[0013] Preferably, the cross-section of the guide rail and the slider is rectangular or trapezoidal.

[0014] Preferably, the simulated test piece includes an outer cylinder, a buffer support, a crossbeam, a wheel axle, and a simulated machine wheel. The outer cylinder is fitted onto the buffer support, the crossbeam is located at the upper end of the outer cylinder, the wheel axle is located at the lower end of the buffer support, and the simulated machine wheel is located at both ends of the wheel axle.

[0015] The simulator wheel 35 is provided with application holes for applying vertical and directional loads, and a lateral load application joint extending along the wheel axle axis is provided on the simulator wheel.

[0016] Preferably, the loading component includes: a position control actuator, a vertical actuator, a lateral actuator, and a yaw actuator. The position control actuator connects the top beam of the test building to the top frame in the support frame and is used to provide a compressive load of a predetermined amount of compression to the simulated test specimen.

[0017] The vertical actuator, lateral actuator, and yaw actuator are connected to the simulated wheels of the test specimen and are used to provide yaw, lateral, and vertical fatigue loads to the test specimen.

[0018] Preferably, the vertical actuator includes a left wheel axle vertical actuator and a right wheel axle vertical actuator, which are connected to the application holes of the simulated wheels of the simulated test piece, and apply vertical loads to the left and right wheels of the simulated test piece through the left wheel axle vertical actuator and the right wheel axle vertical actuator;

[0019] The lateral actuators include a left wheel axle lateral actuator, a left wheel tire contact point lateral actuator, a right wheel axle lateral actuator, and a right wheel tire contact point lateral actuator. The left wheel axle lateral actuator and the left wheel tire contact point lateral actuator are connected to the left simulated wheel and are used to apply left-side axle load and wheel tire contact point load, respectively. The right wheel axle lateral actuator and the right wheel tire contact point lateral actuator are connected to the right simulated wheel and are used to apply right-side axle load and wheel tire contact point load.

[0020] The yaw actuator includes a left wheel axle forward actuator, a left wheel axle rear actuator, a left wheel tire contact point rearward actuator, a right wheel axle forward actuator, a right wheel axle rear actuator, and a right wheel tire contact point rearward actuator. The left wheel axle forward actuator and the right wheel axle forward actuator are respectively connected to the left and right simulated wheels, and are used to apply forward left wheel axle load and right wheel axle load, respectively. The left wheel axle rear actuator and the right wheel axle rear actuator are respectively connected to the left and right simulated wheels, and are used to apply backward left wheel axle load and right wheel axle load, respectively. The left wheel tire contact point rearward actuator and the right wheel tire contact point rearward actuator are respectively connected to the left and right simulated wheels, and are used to apply backward left wheel tire contact point load and right wheel tire contact point load, respectively.

[0021] Preferably, the lateral actuator is connected to the simulated test piece via a rigid connection, while the vertical actuator and the yaw actuator are connected to the simulated test piece via a flexible connection.

[0022] The landing gear fatigue testing device provided in this application is easy to manufacture and low in cost through the use of welded steel profiles; the self-balancing integrated follow-up frame ensures safe and reliable assembly; one end of the nose landing gear tire contact point is installed below, and the other end of the nose landing gear suspension is installed above, ensuring reliable support for the nose landing gear and a clear mechanical state, enabling both static and fatigue tests to be performed; during fatigue testing, it is convenient to deduct the weight of the wheels and loading equipment, resulting in higher loading accuracy and a higher fatigue test frequency, and it can perform fatigue tests on the variable buffer strut compression of the nose landing gear. Attached Figure Description

[0023] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0024] Figure 1 This is a schematic diagram of the overall front landing gear fatigue testing device of this application.

[0025] Figure 2 This is a schematic diagram of the supporting framework in this application.

[0026] Figure 3 This is a schematic diagram of the follower device in this application.

[0027] Figure 4 This is a schematic diagram of the follower frame in this application.

[0028] Figure 5 This is a schematic diagram of the guide rail slider assembly in this application.

[0029] Figure 6 This is a schematic diagram of the simulated test specimen in this application.

[0030] Figure 7 This is a schematic diagram of the loading component in this application.

[0031] Figures 8 to 17 This is a schematic diagram of the assembly process of the front landing gear fatigue testing device of this application. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0033] like Figure 1 As shown, this application provides a front landing gear fatigue testing device with adjustable buffer strut compression. The front landing gear fatigue testing device 100 includes a support frame 10, a follower device 20, a simulation test piece 30, and a loading assembly 40.

[0034] like Figure 2As shown, the support frame 10 includes a support base 11 and a top frame 12. The support base 11 is mainly composed of a long crossbeam 111, a short crossbeam 112, a short column 113, and a long column 114. The long crossbeam 111, short crossbeam 112, and short column 113 are connected by welding or bolts to form the bottom frame structure, which is fixed to the ground of the test site. The bottom of the long column 114 is set on the bottom frame structure, and it is vertically arranged. The top of the long column 114 is fixedly connected to the top frame by welding or bolts.

[0035] In some embodiments of this application, the long crossbeam 111 has the same structural features as the follower crossbeam 24 and is used to mount the lateral actuator and the yaw actuator.

[0036] In some embodiments of this application, the short crossbeam 112 is made of rectangular cross-section thick-walled square steel profile, with the left and right ends flush and welded together, and is used for the vertical connection and installation of the bottom structure of the front landing gear fatigue test device.

[0037] In some embodiments of this application, the structural features and geometric dimensions of the short column 113 are exactly the same as or similar to those of the short crossbeam 112, only the position is different, and it is used for the vertical connection and installation of the bottom structure of the front landing gear fatigue testing device.

[0038] In some embodiments of this application, the long column 114 is processed from a thick-walled square steel profile with a rectangular cross section. Its upper and lower end faces are sealed and welded. The material can be Q345 steel. The four sides of the long column 114 can be processed with connecting through holes and assembly reserved holes. The follower frame 21 and guide rail slider assembly 25 are installed at approximately the middle position. The top frame 12 is installed at the top, and the short crossbeam 112 and short column 113 are installed at the bottom.

[0039] The top frame 12 has a main through hole 121 in the middle for the position control actuator 41 to pass through. The top frame 12 is fixed to the top of the long column 114, and the top frame 12 and the long column 114 can be connected by bolts to form an integral unit. The left wheel axle vertical actuator 421 and the right wheel axle vertical actuator 422 in the loading assembly 40 are installed below the top frame 12. In some embodiments of this application, the top frame 12 is a welded steel plate component, and it is generally best to choose a steel plate with a thickness of 20 mm or more, and the material can be Q345 steel.

[0040] like Figure 3 As shown, the follower device 20 includes a follower frame 21, a support base 22, a support joint 23, a follower beam 24, and a guide rail slider assembly 25. The follower device 20 is used to hoist the simulated test piece 30 and transmit the displacement force of the position control actuator 41 to the simulated test piece 30.

[0041] like Figure 4As shown, the upper side of the follower frame 21 has a double-ear structure 211 for connecting the position control actuator 41. Through holes 212 are provided on both sides of the double-ear structure 211 for the vertical actuator in the loading assembly 40 to pass through. The support base 22 is fixedly connected to the lower side of the follower frame 21 by bolts. The support joint 23 is fixedly installed below the support base 22 by bolts. The simulated test piece 30 is suspended below the support base 22 through the support joint 23. When the position control actuator 41 applies a displacement force to the follower frame 21, the buffer support 32 in the simulated test piece 30 can be compressed or extended. Four follower beams 24 are fixedly installed on the edges of the follower frame 21. Figure 3 The image only shows one of the following crossbeams 24 on the right side, which is connected to the guide rail slider assembly 25.

[0042] In some embodiments of this application, the follower frame 21 is made of welded steel plate, typically steel plate with a thickness of 20 mm or more, and Q345 steel. The follower frame 21 is bolted to four follower beams 24 around its perimeter, and the support base 22 is bolted to the bottom of the follower frame 21.

[0043] In some embodiments of this application, the support base 22 is a welded steel plate component with the same structural features as the top frame 12. The support base 22 is installed below the follower frame 21 by bolts.

[0044] In some embodiments of this application, the support connector 23 is an integrally machined part, made of 30CrMnSiA steel with a heat treatment level of 1080MPa, and is installed below the support base 22 by bolts.

[0045] In some embodiments of this application, the follower beam 24 is made of a rectangular cross-section thick-walled square steel profile, which can be made of Q345 steel. It has four sides with connecting through holes. The horizontal through holes are used to connect with the slider of the guide rail slider assembly 25, and the vertical through holes are used to connect with the connecting follower frame 21.

[0046] like Figure 5 As shown, the guide rail and slider assembly 25 includes a guide rail 251 and a slider 252. The guide rail 251 is bolted to the long column 114 in the support frame 10 and is approximately at the same height. The slider 252 is disposed at both ends of the follower beam 24, and the two are bolted together. The guide rail 251 and the slider 252 can slide relative to each other, thereby allowing the follower device 20 to move on the long column 114 of the support frame 10.

[0047] In some embodiments of this application, the cross section of the guide rail 251 and the slider 252 can be rectangular or trapezoidal.

[0048] like Figure 6As shown, the simulated test piece 30 includes an outer cylinder 31, a buffer support 32, a crossbeam 33, a wheel axle 34, and a simulated wheel 35. The outer cylinder 31 is fitted onto the buffer support 32, the crossbeam 33 is located at the upper end of the outer cylinder 31, the wheel axle 34 is located at the lower end of the buffer support 32, and the simulated wheel 35 is located at both ends of the wheel axle 34. In this embodiment of the application, the simulated wheel 35 uses a metal plate structure instead of a real wheel structure. Vertical and directional loads are applied to the simulated wheel 35 through application holes 351. Vertical and directional actuators can be connected to the application holes 351 to apply vertical and directional loads to the simulated wheel 35. Meanwhile, a lateral load application joint 352 extending along the wheel axle axis is provided on the simulator wheel 35. There are two lateral load joints 352. One lateral load joint 352 is coincident with the wheel axle axis 34, and the other lateral load joint 352 is arranged parallel to the bottom of the simulator wheel 35. The lateral actuator can be connected to the lateral load application joint 352 to apply lateral load to the simulator wheel 35, thereby achieving the application of vertical, lateral and yaw loads at the wheel position.

[0049] like Figure 7 As shown, the loading component 40 includes: a position control actuator 41, a vertical actuator 42, a lateral actuator 43, and a yaw actuator 44.

[0050] The actuator 41 connects the top beam of the test chamber to the top frame 12 in the support frame 10, and is used to provide a predetermined compression load to the buffer support 33 of the simulated test specimen 30. In some embodiments of this application, the actuator 41 can be an existing test equipment in the test chamber. During the test, the actuator 41 is used to compress the buffer support of the simulated test specimen 30, thus bearing the compression load. The actuator 41's ability to bear the compression load is nearly three times its ability to bear the tensile load. Typically, an actuator 41 with a tensile load capacity of not less than 40 tons is selected.

[0051] The vertical actuator 42 includes a left wheel axle vertical actuator 421 and a right wheel axle vertical actuator 422, which are connected to the application holes 351 of the simulated wheel 35 of the simulated test piece 30. A vertical H-load can be applied to the left and right wheels via the left wheel axle vertical actuator 421 and the right wheel axle vertical actuator 422.

[0052] The lateral actuator 43 includes a left wheel axle lateral actuator 431, a left wheel tire contact point lateral actuator 432, a right wheel axle lateral actuator 433, and a right wheel tire contact point lateral actuator 434. The left wheel axle lateral actuator 431 and the left wheel tire contact point lateral actuator 432 are connected to the left simulated wheel 35 and are used to apply a left-side axle load (L) and a wheel tire contact point load, respectively. The right wheel axle lateral actuator 433 and the right wheel tire contact point lateral actuator 434 are connected to the right simulated wheel 35 and are used to apply a right-side axle load (R) and a wheel tire contact point load, respectively.

[0053] The yaw actuator 44 includes a left wheel axle forward actuator 441, a left wheel axle rear actuator 442, a left wheel tire contact point rear actuator 443, a right wheel axle forward actuator 444, a right wheel axle rear actuator 445, and a right wheel tire contact point rear actuator 446. The left wheel axle forward actuator 441 and the right wheel axle forward actuator 444 are respectively connected to the left simulated wheel 35 and the right simulated wheel 35, and are used to apply the forward F axle load of the left wheel and the right wheel respectively. The left wheel axle rear actuator 442 and the right wheel axle rear actuator 445 are respectively connected to the left simulated wheel 35 and the right simulated wheel 35, and are used to apply the left wheel axle load and the right wheel axle load in the rearward direction B, respectively; the left wheel tire contact point rear actuator 443 and the right wheel tire contact point rear actuator 446 are respectively connected to the left simulated wheel 35 and the right simulated wheel 35, and are used to apply the left wheel tire landing point load and the right wheel tire landing point load in the rearward direction B, respectively.

[0054] In a preferred embodiment of this application, the lateral actuator 43 is connected to the simulated test piece 30 via a rigid connection. That is, the four actuators, namely the left wheel axle lateral actuator 431, the left wheel tire contact point lateral actuator 432, the right wheel axle lateral actuator 433, and the right wheel tire contact point lateral actuator 434, are connected to the simulated wheel 35 through an application joint, which can apply both tensile and compressive loads. The vertical actuator 42 and the yaw actuator 44 are connected to the simulated test piece 30 via a soft connection. Specifically, the left wheel axle vertical actuator 421, the right wheel axle vertical actuator 422, the left wheel axle forward actuator 441, the left wheel axle rear actuator 442, the left wheel tire contact point rear actuator 443, the right wheel axle forward actuator 444, the right wheel axle rear actuator 445, and the right wheel tire contact point rear actuator 446 are softly connected to the simulated wheel 35 via a pull plate 423, so that only tensile loads can be applied.

[0055] In some embodiments of this application, the material of the pull plate 423 can be 30CrMnSiA steel with a heat treatment level of 1080MPa, used to connect the loading actuator to the loading wheel.

[0056] Position control actuator 41 is fixedly mounted on top frame 12. Its retractable single ear is connected to the double ear structure 211 of follower frame 21. The extension and retraction of position control actuator 41 can adjust the up and down movement of follower frame 21. The up and down movement of follower frame 21 can further adjust the stroke of frame buffer support 32. When position control actuator 41 is extended, the compression of buffer support 32 of simulated test piece 30 increases; when position control actuator 41 is shortened, the compression of buffer support 32 of simulated test piece 30 decreases. In the extended or shortened state of position control actuator 41, fatigue test of variable compression of simulated test piece 30 can be completed by vertical actuator 42, lateral actuator 43 and yaw actuator 44.

[0057] In this application, the left wheel axle vertical actuator 421 and the right wheel axle vertical actuator 422 apply tensile loads, while the position control actuator 41 bears compressive loads. The position control actuator 41's ability to bear compressive loads is nearly three times its ability to bear tensile loads.

[0058] The assembly process of the front landing gear fatigue testing device in this application is as follows:

[0059] 1) On the ground of the test site, assemble 8 long crossbeams 111, 16 short crossbeams 112, 4 short columns 113, and 4 long columns 114 into a single unit. Figure 8 The bottom loading frame is shown;

[0060] 2) On the eight long crossbeams 111 of the bottom loading frame, install the following actuators: right wheel axle lateral actuator 433, right wheel tire contact point lateral actuator 434, right wheel axle rearward actuator 445, right wheel tire contact point rearward actuator 446, left wheel tire contact point rearward actuator 443, left wheel axle rearward actuator 442, left wheel tire contact point lateral actuator 432, left wheel axle lateral actuator 431, left wheel axle forward actuator 441, and left wheel axle vertical actuator 421. Figure 9 As shown;

[0061] 3) Install 8 guide rail slider assemblies 25 at the center of each of the 4 long columns 114, such as... Figure 10 As shown;

[0062] 4) Install four follower beams 24 on the slider 252 of the eight guide rail slider assembly 25, as follows: Figure 11 As shown;

[0063] 5) Install a support base 22 below the follower frame 21, install a support connector 23 below the support base 22, and simulate test piece 30 below the support connector 23, such as... Figure 12 As shown;

[0064] 6) The assembly of the follower frame 21, support base 22, support connector 23, and simulated test piece 30 is inserted from above and installed as follows: Figure 17 Above the moving crossbeam 24 of the structure shown, as Figure 13 As shown;

[0065] 7) Fix the follower frame 21 to the four follower beams 24 with bolts, so that the follower frame 21 and the four follower beams 24 become a whole structure.

[0066] 8) Install the right wheel axle vertical actuator 422 and the left wheel axle vertical actuator 421 below the top frame 12, as follows: Figure 14 As shown;

[0067] 9) Install the top frame 12, which houses the right wheel axle vertical actuator 422 and the left wheel axle vertical actuator 421, as shown in the image. Figure 13 The structure shown consists of four long columns 114 on top of each other, connected by bolts, as shown. Figure 15 As shown;

[0068] 10) Install the position control actuator 41 at the center of the top frame 12, such as Figure 16 As shown;

[0069] 11) The position-controlled actuator 41 is connected to the follower frame 21; all actuators are connected to the simulation test piece 30, such as... Figure 17 As shown.

[0070] The landing gear fatigue testing device provided in this application is easy to manufacture and low in cost through the use of welded steel profiles; the self-balancing integrated follow-up frame ensures safe and reliable assembly; one end of the nose landing gear tire contact point is installed below, and the other end of the nose landing gear suspension is installed above, ensuring reliable support for the nose landing gear and a clear mechanical state, enabling both static and fatigue tests to be performed; during fatigue testing, it is convenient to deduct the weight of the wheels and loading equipment, resulting in higher loading accuracy and a higher fatigue test frequency, and it can perform fatigue tests on the variable buffer strut compression of the nose landing gear.

[0071] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A nose landing gear fatigue test apparatus capable of adjusting the compression amount of a shock strut, characterized by, The application relates to a front landing gear fatigue test device. The support frame is arranged on a test site and used for supporting a simulation test piece, and comprises a support base and a top frame; the support base comprises long cross beams, short cross beams, short columns and long columns; the long cross beams, the short cross beams and the short columns are fixedly connected to form a bottom frame structure; the bottom frame structure is fixed on the ground of the test site; the bottom of the long column is arranged on the bottom frame structure and is arranged vertically; the middle part of the top frame is provided with a main through hole through which a position control actuator passes; and the top frame is fixed on the top of the long column, thereby being connected with the long column to form an integral whole. The follower device is installed on the support frame and used for hoisting the simulation test piece and transmitting the displacement force of the position control actuator in the loading assembly to the simulation test piece; the follower device comprises a follower frame, a support base, a support joint, a follower cross beam and a guide rail sliding block assembly; the upper side of the follower frame is provided with a double-ear structure connected with the position control actuator; the two sides of the double-ear structure are provided with through holes through which the loading assembly passes; the support base is fixedly connected to the lower side of the follower frame; the support joint is fixedly installed below the support base and used for suspending the simulation test piece; the follower cross beam is fixedly installed on the edge of the follower frame; and the guide rail sliding block assembly is slidably installed on the long column of the support frame; the follower cross beam is connected with the guide rail sliding block assembly, thereby enabling the follower frame to move along the height direction of the long column. The simulation test piece is hoisted on the follower device; the simulation test piece comprises an outer cylinder, a buffer column, a cross beam, an axle and simulation wheels; the outer cylinder is sleeved on the buffer column; the cross beam is arranged on the upper end of the outer cylinder; the axle is arranged on the lower end of the buffer column; and the simulation wheels are arranged on the two ends of the axle; wherein the simulation wheels are provided with applying holes for applying vertical load and heading load; and the simulation wheels are provided with lateral load applying joints extending along the axial direction of the axle. The loading assembly is used for applying a load with a predetermined compression amount to the buffer column of the simulation test piece and simultaneously applying heading load, lateral load and vertical test load to the simulation test piece, so as to perform a fatigue test on the front landing gear.

2. The adjustable cushion strut compression amount front landing gear fatigue test device of claim 1, wherein, The long cross beams, the short cross beams, the short columns, the long columns and / or the top frame are made of Q345 steel.

3. The adjustable cushioning strut compression amount front landing gear fatigue test device of claim 2, wherein, The guide rail sliding block assembly comprises a guide rail and a sliding block; the guide rail is fixedly installed on the long column; and the sliding block is fixedly connected with the follower cross beam and slidably installed on the guide rail.

4. The adjustable cushioning strut compression amount front landing gear fatigue test device of claim 3, wherein, The matching section of the guide rail and the sliding block is rectangular or trapezoidal.

5. The adjustable cushioning strut compression amount front landing gear fatigue test device of claim 1, wherein, The loading assembly comprises a position control actuator, a vertical actuator, a lateral actuator and a heading actuator; the position control actuator is connected with the top cross beam of the test workshop and the top frame in the support frame and used for providing a compression load with a predetermined compression amount of the buffer column to the simulation test piece; The vertical actuator, the lateral actuator and the heading actuator are connected with the simulation wheels of the simulation test piece and used for providing heading load, lateral load and vertical fatigue load to the simulation test piece.

6. The adjustable cushioning strut compression amount front landing gear fatigue test device of claim 5, wherein, The vertical actuators include left wheel axle vertical actuators and right wheel axle vertical actuators, which are connected to the application holes of the simulation test piece simulation wheels, and apply vertical loads to the left and right simulation test piece wheels through the left and right wheel axle vertical actuators; The lateral actuators include left wheel axle lateral actuators, left wheel tire contact point lateral actuators, right wheel axle lateral actuators and right wheel tire contact point lateral actuators, which are connected to the left simulation wheels, and are used to apply left lateral axle loads and wheel tire contact point loads, respectively; the right wheel axle lateral actuators and right wheel tire contact point lateral actuators are connected to the right simulation wheels, and are used to apply right lateral axle loads and wheel tire contact point loads, respectively. The lateral actuators include left wheel axle lateral actuators, left wheel tire contact point lateral actuators, right wheel axle lateral actuators and right wheel tire contact point lateral actuators, which are connected to the left simulation wheels, and are used to apply left lateral axle loads and wheel tire contact point loads, respectively; the right wheel axle lateral actuators and right wheel tire contact point lateral actuators are connected to the right simulation wheels, and are used to apply right lateral axle loads and wheel tire contact point loads, respectively.

7. The adjustable cushioning strut compression amount front landing gear fatigue test device of claim 5, wherein, The lateral actuators include left wheel axle lateral actuators, left wheel tire contact point lateral actuators, right wheel axle lateral actuators and right wheel tire contact point lateral actuators, which are connected to the left simulation wheels, and are used to apply left lateral axle loads and wheel tire contact point loads, respectively; the right wheel axle lateral actuators and right wheel tire contact point lateral actuators are connected to the right simulation wheels, and are used to apply right lateral axle loads and wheel tire contact point loads, respectively. The lateral actuators are connected to the simulation test piece through a hard connection mode, and the vertical actuators and the heading actuators are connected to the simulation test piece through a soft connection mode.

Images