An aircraft landing gear drop test tower based on hydraulic system control

Abstract

The application discloses a landing gear drop test tower based on hydraulic system control and relates to the technical field of landing gear drop test towers.The landing gear drop test tower comprises a support, the support is fixedly connected to the top of a bottom plate, a guide assembly is arranged in the support, the guide assembly is fixedly connected to the top of the bottom plate, a falling assembly is arranged directly above the bottom plate, the falling assembly is slidably connected to the guide assembly, a landing gear is hung directly below the falling assembly, the landing gear is fixedly connected to the side of the falling assembly close to the bottom plate, a driving assembly is fixedly connected to the top of the bottom plate, the side of the driving assembly away from the bottom plate is fixedly connected to the bottom of the falling assembly, a detection assembly is arranged directly below the landing gear, and the detection assembly is fixedly connected to the top of the bottom plate.The arc trajectory during airplane landing is simulated, so that the experimental state is close to the real state, the experiment is accurate and reliable, the detection assembly records the impact intensity of the landing gear, and the shock absorption performance of the landing gear is evaluated.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing gear drop test tower technology, and specifically to an aircraft landing gear drop test tower based on hydraulic system control. Background Technology

[0002] Aircraft landing gear is an accessory device located at the bottom of an aircraft, used to support the aircraft during takeoff, landing, or taxiing and for ground movement. It is the only component that supports the entire aircraft, making it an indispensable part. Without it, the aircraft cannot move on the ground. After takeoff, the landing gear can be retracted depending on flight performance. Therefore, the performance of the aircraft landing gear is crucial to the aircraft's safety. After using the aircraft landing gear or after a period of use, its comprehensive performance needs to be tested.

[0003] Currently, simple mechanical test towers are mainly used for testing. However, existing test towers have low testing accuracy and cannot conduct tests on the landing gear's shock absorption performance, braking performance, etc., in one go. Furthermore, the simulated landing conditions have low realism. Therefore, we propose an aircraft landing gear landing test tower based on hydraulic system control. Summary of the Invention

[0004] To solve the above-mentioned technical problems, the present invention provides an aircraft landing gear drop test tower based on a hydraulic system control, comprising:

[0005] A base plate, the top of which is fixedly connected to a tower ladder;

[0006] An experimental tower mechanism is fixedly connected to the top of the base plate, and the tower ladder is arranged around the outside of the experimental tower mechanism;

[0007] The experimental tower mechanism includes:

[0008] A bracket is fixedly connected to the top of a base plate, and a guide assembly is provided inside the bracket, which is fixedly connected to the top of the base plate.

[0009] A falling assembly is disposed directly above the base plate, and the falling assembly is slidably connected to the guide assembly;

[0010] The landing gear is suspended directly below the landing assembly and is fixedly connected to the side of the landing assembly near the base plate.

[0011] A drive assembly is fixedly connected to the top of the base plate, and the side of the drive assembly away from the base plate is fixedly connected to the bottom of the falling assembly;

[0012] A detection component is located directly below the landing gear and is fixedly connected to the top of the base plate.

[0013] The aircraft landing gear to be tested is suspended below the landing assembly. The landing assembly descends vertically along the guide assembly while simultaneously driving the landing gear to move horizontally, simulating the arc trajectory of an aircraft during landing to achieve a near-realistic experimental state. The accuracy and reliability of the experimental data are ensured. The drive assembly is driven by a hydraulic system to bring the landing assembly and landing gear to a predetermined height and drive the landing gear to descend at the speed of an aircraft during landing, simulating a real landing state. The aircraft impact detection assembly records the impact force of the landing gear to evaluate its shock absorption performance.

[0014] Furthermore, the guiding assembly includes four guide rods, all of which are fixedly connected to the top of the base plate. A support frame is provided at the end of each guide rod away from the base plate, and the support frame is fixedly connected to the ends of the four guide rods away from the base plate. The four guide rods are respectively located at the four corners of the support frame. The inner side of the falling assembly is slidably connected to the surface of the guide rods. The guide rods guide the vertical falling direction of the landing gear, preventing the landing gear from shaking during the falling experiment and thus avoiding affecting the accuracy of the experimental results.

[0015] Furthermore, a triangular plate is fixedly connected to the side of the support frame near the base plate, and the side of the triangular plate is fixedly connected to the surface of the support. A hydraulic lock is provided at the center of the support frame, and the crossbeam of the support frame passes through the hydraulic lock. The surface of the support frame is fixedly connected to the inner side of the hydraulic lock. The hydraulic lock is driven by a hydraulic system. During the experiment, it can lock the falling component. After the experiment is prepared, the falling component is released and the falling experiment is carried out. The hydraulic lock avoids the hydraulic system from holding the falling component at a fixed height for a long time, reducing energy waste during the experiment preparation stage.

[0016] Furthermore, the falling assembly includes a falling frame, with the ends of the four guide rods away from the base plate passing through the falling frame, and the surfaces of the guide rods slidably connected to the inner surfaces of the falling frame. The falling frame is positioned at the interval between the support frame and the base plate, and a latch is fixedly connected to the side of the falling frame away from the base plate. The latch is adapted to a hydraulic lock. The falling frame slides on the surface of the guide rods to limit the vertical fall of the falling experiment. The latch locks with the hydraulic lock, reducing the energy consumption of the hydraulic system during the preparation stage.

[0017] Furthermore, a transverse hydraulic slide rail is fixedly connected to the side of the landing gear closest to the base plate, and a hook is fixedly connected to the side of the transverse hydraulic slide rail away from the base plate. The hook is fixedly connected to the output end of the transverse hydraulic slide rail, and the end of the hook away from the transverse hydraulic slide rail is fixedly connected to the shock-absorbing strut of the landing gear by bolts. During vertical descent, the hydraulic system drives the transverse hydraulic slide rail to start, and the output end of the transverse hydraulic slide rail drives the hook to perform horizontal feeding, which drives the landing gear to move horizontally. In conjunction with the vertical descent, the arc trajectory of the aircraft during landing is simulated, simulating the real movement process of the landing gear during landing, and obtaining more realistic experimental results.

[0018] Furthermore, a connecting plate is fixedly connected to the side of the transverse hydraulic slide rail near the base plate. The connecting plate is set at an acute angle to the transverse hydraulic slide rail, and the connecting plate is inclined towards the side closer to the landing gear. The end of the connecting plate away from the transverse hydraulic slide rail is rotatably connected to the torsion arm of the landing gear through a rotating rod. The torsion arm of the landing gear is rotatably connected to the shock absorber strut. The hook drives the shock absorber strut to move horizontally, and the shock absorber strut pulls the torsion arm. The two ends of the torsion arm rotate around the connecting plate and the shock absorber strut, respectively. Under the reaction force, the shock absorber strut extends and retracts, simulating the landing gear's falling trajectory while testing the extension and retraction performance of the shock absorber strut to obtain a more comprehensive experimental result.

[0019] Furthermore, the drive assembly includes a vertical hydraulic slide rail, which is fixedly connected to the top of the base plate. Two vertical hydraulic slide rails are provided, and the two vertical hydraulic slide rails are symmetrically arranged with the landing gear as the center. A hydraulic rod is slidably connected to the inner side of the vertical hydraulic slide rail, and the hydraulic rod is fixedly connected to the output end of the vertical hydraulic slide rail. The end of the hydraulic rod away from the base plate is fixedly connected to the side of the landing gear close to the base plate. The vertical hydraulic slide rail is driven by a hydraulic system. The output end of the vertical hydraulic slide rail drives the hydraulic rod to rise and fall, thereby driving the landing gear to rise and fall. In the experimental preparation stage, the landing gear is first fixed to the hook, and then the hydraulic rod drives the landing gear to rise. The latch on the landing gear is locked with the hydraulic lock. In the experimental stage, the vertical hydraulic slide rail drives the hydraulic rod to fall, and finally drives the landing gear to simulate the aircraft's falling speed to fall, simulating the real falling environment.

[0020] Furthermore, each of the two vertical hydraulic slide rails is provided with a connecting rod on its side. The connecting rod is fixedly connected to the output end of the vertical hydraulic slide rail. A CCD camera is fixedly connected to the side of the connecting rod near the landing gear. The CCD camera moves with the hydraulic rod, and the wide-angle lens of the CCD camera always captures the connection between the landing gear wheel and the shock absorber strut to obtain the contraction and rebound of the shock absorber strut during the landing test. This determines whether it can effectively absorb the energy of the aircraft landing and reduce the impact on the aircraft structure and equipment, so as to evaluate its shock absorption performance. Moreover, the two CCD cameras serve as a comparison to obtain more accurate experimental data.

[0021] Furthermore, the detection component includes a frame fixedly connected to the top of the base plate. A sliding plate is slidably connected to the top of the frame, and an experimental plate made of rubber is embedded inside the sliding plate. The surface of the experimental plate is fixedly connected to the inner side of the sliding plate, and four experimental plates are provided. The four experimental plates are respectively positioned directly below the four landing gear wheels. The landing gear wheels contact the experimental plates, and the experimental plates drive the sliding plate to slide until the landing gear's kinetic energy is exhausted. The sliding of the sliding plate is recorded by a CCD camera, which directly reflects the landing gear's taxiing length and assesses whether the landing gear braking system can quickly and effectively decelerate the aircraft after landing. The rubber material of the experimental plate can increase the friction with the wheels, avoid slippage, and obtain a more accurate taxiing length.

[0022] Furthermore, a magnetic levitation track is symmetrically arranged inside the frame. The magnetic levitation track is fixedly connected to the inner side of the frame. A connecting frame is provided on the side of the magnetic levitation track near the experimental board. The connecting frame is fixedly connected to the output end of the magnetic levitation track. The side of the connecting frame away from the magnetic levitation track is fixedly connected to the side of the experimental board near the bottom plate. A pressure sensor is provided at the interval between the connecting frame and the experimental board. The pressure sensor is fixedly connected to the surface of the connecting frame. The side of the pressure sensor away from the connecting frame is fixedly connected to the side of the experimental board near the bottom plate. The landing gear wheels contact the experimental board, and the experimental board drives the connecting frame to move. The output end of the magnetic levitation track moves, and at the same time, the wheels squeeze the experimental board, and the experimental board squeezes the pressure sensor. The pressure sensor obtains the pressure when the landing gear falls, that is, the pressure data of the shock absorber strut, to evaluate its shock absorption performance. After the experiment is completed, the output end of the magnetic levitation track drives the connecting frame, the experimental board, and the sliding plate to reset, preparing for the next experiment. The magnetic levitation track has no friction between the wheel and the rail, and the resistance is small, which can obtain a more realistic landing gear sliding distance and a more realistic braking force capability of the landing gear braking system during landing gear descent.

[0023] The beneficial effects of this invention are as follows:

[0024] 1. This invention sets up a test tower mechanism, in which the falling component falls vertically along the guide component, while the falling component drives the landing gear to make horizontal feed, simulating the arc trajectory of an aircraft landing, so as to achieve a near-realistic experimental state. The experiment is highly accurate and reliable. The detection component records the impact force of the landing gear and evaluates the shock absorption performance of the landing gear.

[0025] 2. This invention, by setting up a guiding component and a guide rod, guides the landing gear in the vertical descent direction, avoiding landing gear swaying during the descent experiment and preventing it from affecting the accuracy of the experimental results. The hydraulic lock setting prevents the hydraulic system from holding the landing component at a fixed height for a long time, reducing energy waste in the experimental preparation stage, driving the landing gear to move horizontally, and coordinating with the vertical descent to simulate the arc trajectory of the aircraft during landing, simulating the real movement process of the landing gear during descent, and obtaining more realistic experimental results.

[0026] 3. By setting a connecting plate, the hook drives the shock absorber column to move horizontally. The shock absorber column pulls the torsion arm, and the two ends of the torsion arm rotate around the connecting plate and the shock absorber column respectively. Under the reaction force, the shock absorber column extends and retracts, simulating the landing gear's falling trajectory, while testing the extension and retraction performance of the shock absorber column, thus obtaining a more comprehensive experimental result.

[0027] 4. By setting up a driving component, the wide-angle lens of the CCD camera continuously captures images of the connection between the landing gear wheels and the shock absorber struts, obtaining the contraction and rebound of the shock absorber struts during the landing test. This determines whether the struts can effectively absorb the energy during aircraft landing and reduce the impact on the aircraft structure and equipment, thereby evaluating their shock absorption performance. Furthermore, the two CCD cameras serve as a comparison, enabling the acquisition of more accurate experimental data.

[0028] 5. This invention, through the setting of detection components, records the sliding of the slide plate by a CCD camera, intuitively reflecting the landing gear sliding length, and evaluating whether the landing gear braking system can quickly and effectively decelerate the aircraft after landing. The rubber experimental plate can increase the friction with the wheels, avoid slippage, and obtain a more accurate sliding length. The pressure sensor obtains the pressure when the landing gear falls, that is, the pressure data of the shock absorber strut, to evaluate its shock absorption performance. The magnetic levitation track has no friction between the wheel and the rail, and has low resistance, which can obtain a more realistic landing gear sliding distance and a more realistic braking force capability of the landing gear braking system during the landing gear descent. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the aircraft landing gear drop test tower based on hydraulic system control according to the present invention.

[0030] Figure 2 This is a schematic diagram of the cross-sectional structure of the bracket of the present invention.

[0031] Figure 3 This is a schematic diagram of the experimental tower mechanism of the present invention.

[0032] Figure 4 For the present invention Figure 2 Enlarged view of part A.

[0033] Figure 5 For the present invention Figure 3 Enlarged view of part B.

[0034] Figure 6 This is a schematic diagram of the landing gear structure of the present invention.

[0035] Figure 7 This is a schematic diagram of the experimental component structure of the present invention.

[0036] Figure 8 This is a schematic diagram of the cross-sectional structure of the frame of the present invention.

[0037] In the diagram: 1. Base plate; 2. Tower ladder; 3. Experimental tower mechanism; 31. Support frame; 32. Guide assembly; 321. Guide rod; 322. Support frame; 323. Triangular plate; 324. Hydraulic lock; 33. Falling assembly; 331. Falling frame; 332. Horizontal hydraulic slide rail; 333. Hook; 334. Lock; 335. Connecting plate; 34. Landing gear; 35. Drive assembly; 351. Vertical hydraulic slide rail; 352. Hydraulic rod; 353. Connecting rod; 354. CCD camera; 36. Detection assembly; 361. Frame; 362. Slide plate; 363. Experimental plate; 364. Magnetic levitation track; 365. Connecting frame; 366. Pressure sensor. Detailed Implementation

[0038] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. The embodiments of the present invention are given for illustrative and descriptive purposes only, and are not intended to be exhaustive or to limit the invention to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art. The embodiments were chosen and described to better illustrate the principles and practical application of the invention, and to enable those skilled in the art to understand the invention and design various embodiments with various modifications suitable for a particular purpose.

[0039] Example 1, please refer to Figures 1-5 This invention relates to an aircraft landing gear drop test tower based on a hydraulic system control, comprising:

[0040] The base plate 1 has a tower ladder 2 fixedly connected to its top.

[0041] Experimental tower mechanism 3 is fixedly connected to the top of the base plate 1, and the tower ladder 2 is arranged around the outside of the experimental tower mechanism 3.

[0042] Among them, experimental tower mechanism 3 includes:

[0043] The bracket 31 is fixedly connected to the top of the base plate 1. The bracket 31 is provided with a guide component 32, which is fixedly connected to the top of the base plate 1.

[0044] The falling component 33 is located directly above the base plate 1 and is slidably connected to the guide component 32.

[0045] The landing gear 34 is suspended directly below the landing assembly 33, and the landing gear 34 is fixedly connected to the side of the landing assembly 33 near the base plate 1.

[0046] Drive assembly 35 is fixedly connected to the top of base plate 1, and the side of drive assembly 35 away from base plate 1 is fixedly connected to the bottom of falling assembly 33.

[0047] The detection component 36 is located directly below the landing gear 34 and is fixedly connected to the top of the base plate 1.

[0048] The landing gear 34 of the aircraft to be tested is suspended below the landing assembly 33. The landing assembly 33 falls vertically along the guide assembly 32, while the landing assembly 33 drives the landing gear 34 to move horizontally, simulating the arc trajectory of the aircraft during landing, so as to achieve a near-realistic experimental state and ensure the accuracy and reliability of the experimental data. The drive assembly 35 is driven by the hydraulic system to drive the landing assembly 33 and the landing gear 34 to a predetermined height, and drives the landing gear 34 to fall at the speed of the aircraft during landing, simulating the real landing state. The aircraft contact detection assembly 36 records the impact force of the landing gear 34 and evaluates the shock absorption performance of the landing gear 34.

[0049] The guide assembly 32 includes four guide rods 321, all of which are fixedly connected to the top of the base plate 1. A support frame 322 is provided at the end of the guide rod 321 away from the base plate 1. The support frame 322 is fixedly connected to the end of the four guide rods 321 away from the base plate 1, and the four guide rods 321 are respectively located at the four corners of the support frame 322. The inner side of the drop assembly 33 is slidably connected to the surface of the guide rod 321. The guide rods 321 are provided to guide the vertical drop direction of the landing gear 34, so as to avoid the landing gear 34 shaking during the drop experiment and avoid affecting the accuracy of the experimental results.

[0050] A triangular plate 323 is fixedly connected to the side of the support frame 322 near the base plate 1. The side of the triangular plate 323 is fixedly connected to the surface of the bracket 31. A hydraulic lock 324 is provided at the center of the support frame 322, and the crossbeam of the support frame 322 passes through the hydraulic lock 324. The surface of the support frame 322 is fixedly connected to the inner side of the hydraulic lock 324. The hydraulic lock 324 is driven by a hydraulic system. During the experiment, it can lock the falling component 33. After the experiment is prepared, the falling component 33 is released and the falling experiment is carried out. The setting of the hydraulic lock 324 avoids the hydraulic system from holding the falling component 33 at a fixed height for a long time, reducing the energy waste in the experiment preparation stage.

[0051] The drop assembly 33 includes a drop frame 331. Four guide rods 321 extend through the drop frame 331 at their ends away from the base plate 1, and the surfaces of the guide rods 321 are slidably connected to the inner surfaces of the drop frame 331. The drop frame 331 is positioned at the interval between the support frame 322 and the base plate 1. A latch 334 is fixedly connected to the side of the drop frame 331 away from the base plate 1, and the latch 334 is compatible with the hydraulic lock 324. The drop frame 331 slides on the surface of the guide rods 321 to limit the vertical drop of the drop experiment. The latch 334 locks with the hydraulic lock 324, reducing the energy consumption of the hydraulic system during the preparation stage.

[0052] A transverse hydraulic slide rail 332 is fixedly connected to the side of the landing gear 331 closest to the base plate 1. A hook 333 is fixedly connected to the side of the transverse hydraulic slide rail 332 away from the base plate 1, and the hook 333 is fixedly connected to the output end of the transverse hydraulic slide rail 332. The end of the hook 333 away from the transverse hydraulic slide rail 332 is fixedly connected to the shock-absorbing strut of the landing gear 34 by bolts. When the aircraft is falling vertically, the hydraulic system drives the transverse hydraulic slide rail 332 to start. The output end of the transverse hydraulic slide rail 332 drives the hook 333 to make horizontal feed, which drives the landing gear 34 to move horizontally. In conjunction with the vertical fall, the arc trajectory of the aircraft during landing is simulated, and the actual movement process of the landing gear 34 during the landing process is simulated to obtain more realistic experimental results.

[0053] A connecting plate 335 is fixedly connected to the side of the transverse hydraulic slide rail 332 near the base plate 1. The connecting plate 335 and the transverse hydraulic slide rail 332 are set at an acute angle, and the connecting plate 335 is inclined towards the side closer to the landing gear 34. The end of the connecting plate 335 away from the transverse hydraulic slide rail 332 is rotatably connected to the torque arm of the landing gear 34 through a rotating rod. The torque arm of the landing gear 34 is rotatably connected to the shock absorber strut. The hook 333 drives the shock absorber strut to move horizontally. The shock absorber strut pulls the torque arm. The two ends of the torque arm rotate around the connecting plate 335 and the shock absorber strut, respectively. Under the reaction force, the shock absorber strut extends and retracts. While simulating the falling trajectory of the landing gear 34, the extension and retraction performance of the shock absorber strut is tested to obtain a more comprehensive experimental result.

[0054] Example 2, please refer to Figures 1-8The drive assembly 35 includes a vertical hydraulic slide rail 351, which is fixedly connected to the top of the base plate 1. Two vertical hydraulic slide rails 351 are provided, symmetrically arranged around the landing gear 34. A hydraulic rod 352 is slidably connected to the inner side of each vertical hydraulic slide rail 351, and the hydraulic rod 352 is fixedly connected to the output end of the vertical hydraulic slide rail 351. The end of the hydraulic rod 352 away from the base plate 1 is fixedly connected to the side of the lower landing gear 331 closest to the base plate 1. The vertical hydraulic slide rail 351 is driven by a hydraulic system. The output end of the vertical hydraulic slide rail 351 drives the hydraulic rod 352 to rise and fall, which in turn drives the landing gear 331 to rise and fall. In the preparation stage of the experiment, the landing gear 34 is first fixed to the hook 333. Then the hydraulic rod 352 drives the landing gear 331 to rise. The latch 334 on the landing gear 331 is locked with the hydraulic lock 324. In the experimental stage, the vertical hydraulic slide rail 351 drives the hydraulic rod 352 to fall, and finally drives the landing gear 34 to simulate the aircraft's falling speed and simulate the real falling environment.

[0055] Both vertical hydraulic slide rails 351 are equipped with connecting rods 353 on their sides. The connecting rods 353 are fixedly connected to the output end of the vertical hydraulic slide rails 351. A CCD camera 354 is fixedly connected to the side of the connecting rod 353 near the landing gear 34. The CCD camera 354 moves together with the hydraulic rod 352. The wide-angle lens of the CCD camera 354 always captures the connection between the landing gear 34 wheel and the shock absorber strut to obtain the contraction and rebound of the shock absorber strut during the landing test. This determines whether it can effectively absorb the energy of the aircraft landing and reduce the impact on the aircraft structure and equipment, so as to evaluate its shock absorption performance. Moreover, the two CCD cameras 354 serve as a comparison for each other, which can obtain more accurate experimental data.

[0056] The detection component 36 includes a frame 361, which is fixedly connected to the top of the base plate 1. A sliding plate 362 is slidably connected to the top of the frame 361. An experimental plate 363 is embedded inside the sliding plate 362. The experimental plate 363 is made of rubber and its surface is fixedly connected to the inner side of the sliding plate 362. There are four experimental plates 363, which are respectively positioned directly below the four wheels of the landing gear 34. When the wheels of the landing gear 34 contact the experimental plates 363, the experimental plates 363 drive the sliding plate 362 to slide until the kinetic energy of the landing gear 34 is exhausted. The sliding of the sliding plate 362 is recorded by the CCD camera 354, which directly reflects the taxiing length of the landing gear 34 and evaluates whether the braking system of the landing gear 34 can quickly and effectively decelerate the aircraft after landing. The rubber material of the experimental plate 363 can increase the friction with the wheels, avoid slippage, and obtain a more accurate taxiing length.

[0057] A magnetic levitation track 364 is symmetrically arranged inside the frame 361. The magnetic levitation track 364 is fixedly connected to the inner side of the frame 361. A connecting frame 365 is provided on the side of the magnetic levitation track 364 near the experimental plate 363. The connecting frame 365 is fixedly connected to the output end of the magnetic levitation track 364. The side of the connecting frame 365 away from the magnetic levitation track 364 is fixedly connected to the side of the experimental plate 363 near the base plate 1. A pressure sensor 366 is provided at the interval between the connecting frame 365 and the experimental plate 363. The pressure sensor 366 is fixedly connected to the surface of the connecting frame 365. The side of the pressure sensor 366 away from the connecting frame 365 is fixedly connected to the side of the experimental plate 363 near the base plate 1. The landing gear 34's wheels are in contact with... Experimental board 363 moves connecting frame 365, and the output end of magnetic levitation track 364 moves. Simultaneously, the wheels press against experimental board 363, which in turn presses against pressure sensor 366. Pressure sensor 366 obtains the pressure of landing gear 34 during descent, i.e., the pressure data of the shock absorber strut, to evaluate its shock absorption performance. After the experiment, the output end of magnetic levitation track 364 drives connecting frame 365, experimental board 363, and sliding plate 362 to reset, preparing for the next experiment. Magnetic levitation track 364 has no friction between wheels and rails, resulting in low resistance and enabling the acquisition of a more realistic landing gear 34 sliding distance and a more realistic braking force capability of the landing gear 34 braking system during descent.

[0058] In use, the vertical hydraulic slide rail 351 is driven by a hydraulic system. The output end of the vertical hydraulic slide rail 351 drives the hydraulic rod 352 to rise and fall, thereby driving the landing gear 331 to rise and fall. In the experimental preparation stage, the landing gear 34 is first fixed to the hook 333. Then, the hydraulic rod 352 drives the landing gear 331 to rise, and the latch 334 on the landing gear 331 locks with the hydraulic lock 324. In the experimental stage, the vertical hydraulic slide rail 351 drives the hydraulic rod 352 to fall, and finally drives the landing gear 34 to simulate the aircraft's descent speed. As the aircraft descends, the hydraulic system drives the lateral hydraulic slide rail 332 to start. The output end of the lateral hydraulic slide rail 332 drives the hook 333 to perform horizontal feeding, causing the landing gear 34 to move horizontally. The torsion arm of the landing gear 34 is rotatably connected to the shock absorber strut. The hook 333 drives the shock absorber strut to move horizontally, and the shock absorber strut pulls the torsion arm. The two ends of the torsion arm rotate around the connecting plate 335 and the shock absorber strut, respectively. Under the reaction force, the shock absorber strut extends and retracts, simulating the descent trajectory of the landing gear 34 while simultaneously testing the extension and retraction performance of the shock absorber strut. During testing, the CCD camera 354 moves along with the hydraulic rod 352. The wide-angle lens of the CCD camera 354 continuously captures images of the connection between the landing gear 34 wheels and the shock absorber strut, obtaining data on the contraction and rebound of the shock absorber strut during the drop test. The landing gear 34 wheels contact the test plate 363, which in turn causes the sliding plate 362 to slide until the landing gear 34's kinetic energy is exhausted. Then, the landing gear 34 wheels contact the test plate 363 again, which in turn causes the connecting frame 365 to move. The magnetic levitation track 364... The output end moves while the wheels press against the test plate 363, which in turn presses against the pressure sensor 366. The pressure sensor 366 obtains the pressure when the landing gear 34 falls. The sliding of the slide plate 362 is recorded by the CCD camera 354, which directly reflects the sliding length of the landing gear 34 and evaluates whether the braking system of the landing gear 34 can quickly and effectively decelerate the aircraft after landing. After the experiment is completed, the output end of the magnetic levitation track 364 drives the connecting frame 365, the test plate 363, and the slide plate 362 to reset, preparing for the next experiment.

[0059] Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art and related fields based on the embodiments of the present invention without inventive effort should fall within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described and explained in the present invention, unless otherwise specified or limited, shall be implemented according to conventional means in the art.

Claims

1. A test tower for aircraft landing gear disembarkation based on a hydraulic system control, characterized in that, include: A base plate (1) is fixedly connected to a tower ladder (2) on its top. The experimental tower mechanism (3) is fixedly connected to the top of the base plate (1), and the tower ladder (2) is arranged around the outside of the experimental tower mechanism (3); The experimental tower mechanism (3) includes: A bracket (31) is fixedly connected to the top of the base plate (1). A guide component (32) is provided inside the bracket (31). The guide component (32) is fixedly connected to the top of the base plate (1). A falling assembly (33) is disposed directly above the base plate (1) and is slidably connected to a guide assembly (32). The guide assembly (32) includes four guide rods (321), all of which are fixedly connected to the top of the base plate (1). A support frame (322) is provided at the end of each guide rod (321) away from the base plate (1). The support frame (322) is fixedly connected to the end of each of the four guide rods (321) away from the base plate (1), and the four guide rods (321) are respectively disposed on the support frame (322). At the four corners, the inner side of the falling assembly (33) is slidably connected to the surface of the guide rod (321); a triangular plate (323) is fixedly connected to the side of the support frame (322) near the base plate (1), the side of the triangular plate (323) is fixedly connected to the surface of the bracket (31), a hydraulic lock (324) is provided at the center of the support frame (322), and the crossbeam of the support frame (322) passes through the hydraulic lock (324), the surface of the support frame (322) is fixedly connected to the inner side of the hydraulic lock (324); the falling assembly (33) includes a falling frame (331), and the four guide rods (321) are far from the base plate (1). 1) One end of the guide rod (321) passes through the lowering frame (331), and the surface of the guide rod (321) is slidably connected to the inner side of the lowering frame (331). The lowering frame (331) is set at the interval between the support frame (322) and the base plate (1). A latch (334) is fixedly connected to the side of the lowering frame (331) away from the base plate (1), and the latch (334) is compatible with the hydraulic lock (324). A transverse hydraulic slide rail (332) is fixedly connected to the side of the lowering frame (331) near the base plate (1). A hook (333) is fixedly connected to the side of the transverse hydraulic slide rail (332) away from the base plate (1), and the hook (333) 333) is fixedly connected to the output end of the transverse hydraulic slide rail (332). The end of the hook (333) away from the transverse hydraulic slide rail (332) is fixedly connected to the shock-absorbing strut of the landing gear (34) by bolts. A connecting plate (335) is fixedly connected to the side of the transverse hydraulic slide rail (332) near the bottom plate (1). The connecting plate (335) is set at an acute angle with the transverse hydraulic slide rail (332), and the connecting plate (335) is inclined to the side near the landing gear (34). The end of the connecting plate (335) away from the transverse hydraulic slide rail (332) is rotatably connected to the torque arm of the landing gear (34) through a rotating rod. The landing gear (34) is suspended directly below the landing assembly (33) and the landing gear (34) is fixedly connected to the side of the landing assembly (33) near the base plate (1). A drive assembly (35) is fixedly connected to the top of the base plate (1), and the side of the drive assembly (35) away from the base plate (1) is fixedly connected to the bottom of the falling assembly (33). The detection component (36) is located directly below the landing gear (34) and is fixedly connected to the top of the base plate (1).

2. The aircraft landing gear drop test tower based on hydraulic system control according to claim 1, characterized in that: The drive assembly (35) includes a vertical hydraulic slide rail (351), which is fixedly connected to the top of the base plate (1). There are two vertical hydraulic slide rails (351), and the two vertical hydraulic slide rails (351) are symmetrically arranged with the landing gear (34) as the center. A hydraulic rod (352) is slidably connected to the inner side of the vertical hydraulic slide rail (351), and the hydraulic rod (352) is fixedly connected to the output end of the vertical hydraulic slide rail (351). The end of the hydraulic rod (352) away from the base plate (1) is fixedly connected to the side of the lower landing gear (331) close to the base plate (1).

3. The aircraft landing gear drop test tower based on hydraulic system control according to claim 2, characterized in that: Both vertical hydraulic slide rails (351) are provided with connecting rods (353) on their sides. The connecting rods (353) are fixedly connected to the output end of the vertical hydraulic slide rails (351). A CCD camera (354) is fixedly connected to the side of the connecting rods (353) near the landing gear (34).

4. The aircraft landing gear drop test tower based on hydraulic system control according to claim 3, characterized in that: The detection component (36) includes a frame (361), which is fixedly connected to the top of the base plate (1). A slide plate (362) is slidably connected to the top of the frame (361). An experimental plate (363) is embedded inside the slide plate (362). The experimental plate (363) is made of rubber. The surface of the experimental plate (363) is fixedly connected to the inner side of the slide plate (362). There are four experimental plates (363), which are respectively located directly below the four wheels of the landing gear (34).

5. The aircraft landing gear drop test tower based on hydraulic system control according to claim 4, characterized in that: A magnetic levitation track (364) is symmetrically arranged inside the frame (361). The magnetic levitation track (364) is fixedly connected to the inner side of the frame (361). A connecting frame (365) is provided on the side of the magnetic levitation track (364) near the experimental board (363). The connecting frame (365) is fixedly connected to the output end of the magnetic levitation track (364). The side of the connecting frame (365) away from the magnetic levitation track (364) is fixedly connected to the side of the experimental board (363) near the bottom plate (1). A pressure sensor (366) is provided at the interval between the connecting frame (365) and the experimental board (363). The pressure sensor (366) is fixedly connected to the surface of the connecting frame (365). The side of the pressure sensor (366) away from the connecting frame (365) is fixedly connected to the side of the experimental board (363) near the bottom plate (1).

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