A fatigue test device for a landing gear buffer and its test method

Abstract

The present invention discloses a fatigue testing device and testing method for landing gear buffers, belonging to the field of landing gear technology. The device comprises a motion mechanism comprising a swinging shaft movably disposed between a vertical plate and a mounting frame, a swinging plate simulating left and right swinging provided in the middle of the swinging shaft, a linkage frame movably disposed on the moving slide, a tripod movably mounted within an engagement frame, and a landing gear to be tested detachably mounted on the bottom of the mounting boss. The turntable mechanism comprises a base positioned below a detection chamber, a friction platform movably disposed on the top of the base, the friction platform comprising multiple landing areas with different friction coefficients, and a detection chamber within each landing area, wherein a pressure sensor is installed. The present invention allows the friction platform to be rotated by means of a locking block and a locking hoop, thereby simulating the effects of different friction coefficients on fatigue. The nozzle and the spray head can also simulate the effects of strong wind and rain on fatigue. The structure is stable and effective, and also improves the freedom and practicality of the testing device.

Description

Technical Field

[0001] The present invention relates to the technical field of landing gears, in particular to a fatigue testing device and a testing method for a landing gear buffer. Background Art

[0002] Aircraft landing gear is a vital component of an aircraft, primarily providing support on the ground and in the air. Its primary functions include supporting the aircraft's weight, facilitating takeoff and landing, and ensuring stability during taxiing. Landing gear typically consists of the main landing gear, nose landing gear, and a shock absorption system. The main landing gear is located on each side of the aircraft, while the nose landing gear is located at the front. The shock absorption system is designed to absorb the impact of landing, reducing the impact on the aircraft and passengers, and ensuring a smooth flight. Prolonged use of the landing gear can cause metal fatigue, which can affect the aircraft's overall safety performance and operational stability. Therefore, fatigue testing of the landing gear is crucial to ensuring safe operation of the aircraft.

[0003] Patent application publication number CN114543672A discloses a landing gear form and position tolerance inspection platform, comprising: a support assembly comprising a first support member and a second support member supporting the landing gear; a scanning assembly comprising a scanning element and a scanning driver, the scanning driver being connected to the scanning element to drive the scanning element to move relative to the first support member, the scanning element having a detection end for detecting the first support member; a contact assembly comprising a contact head, a contact driver, and a distance sensor, the contact driver being connected to the contact head to drive the contact head to move relative to the second support member, the contact head having a contact end that presses against the landing gear, and the distance sensor detecting the spatial position of the contact end. A data processor is electrically connected to the scanning element and the distance sensor, respectively, and is used to receive images scanned by the scanning element and spatial position information collected by the distance sensor to obtain the dimensional parameters of the landing gear. By visually measuring some of the dimensional parameters of the landing gear and using the contact assembly for supplementary measurements, the dimensional parameters of the landing gear can be measured efficiently and quickly.

[0004] The aforementioned landing gear testing platform has a limited degree of automation and flexibility. It cannot perform compression friction tests on the front and side surfaces of tires from multiple angles during landing gear testing. Furthermore, its limited testing mode prevents the flexibility to select various surfaces with different friction coefficients or simulate landing and takeoff conditions in different weather conditions. Therefore, in response to these limitations, there is an urgent need to develop a fatigue testing device for landing gear shock absorbers to overcome these shortcomings in current practical applications. Summary of the Invention

[0005] The purpose of the present invention is to provide a fatigue testing device and a testing method for a landing gear buffer in order to solve the problems that the existing landing gear testing platform has a low degree of automation and a low degree of freedom, cannot perform extrusion friction tests on the front and side of the tire from multiple angles when testing the landing gear, and has a single testing mode and cannot freely select a variety of ground surfaces with different friction coefficients or simulate landing and taking-off conditions of the landing gear in different weather conditions according to actual needs.

[0006] To achieve the above-mentioned purpose, the technical solution of the present invention is: a fatigue test device for a landing gear buffer, comprising a mounting frame, a motion mechanism and a turntable mechanism, a vertical plate fixedly provided on the inner side of the mounting frame, the motion mechanism comprising a swing shaft movably provided between the vertical plate and the mounting frame, a swing plate simulating left and right swinging is provided in the middle of the swing shaft, a detection cavity is provided on the swing plate; a motion slide simulating forward and backward motion is slidably provided on the swing plate, a linkage frame is swung on the motion slide, the linkage frame consists of two parts: a swing arm and an engagement frame; three parts are movably provided in the engagement frame The tripod is provided with a mounting boss at the front end of the engagement frame, the bottom of the mounting boss is detachably mounted with the landing gear to be tested, and the bottom of the mounting boss is mounted with a fatigue sensor; the turntable mechanism includes a base located below the detection cavity, the top of the base is movably provided with a friction table, and the friction table includes a plurality of landing areas with different friction coefficients; a detection chamber is provided inside the landing area, and a pressure sensor is installed in the detection chamber; when the tripod rotates in the engagement frame and the swing plate swings left and right, a landing simulation test can be performed on the bottom and both sides of the landing gear to be tested.

[0007] As a further solution of the present invention: a rotating shaft is movably installed on the inner wall of the mounting frame, a swing frame is provided in the middle of the rotating shaft, and sector teeth are provided on the outer side of the rotating shaft; a swing gear meshing with the sector teeth is fixedly connected to the inner side of the swing shaft.

[0008] As a further solution of the present invention: a swing motor is further installed on the outside of the mounting frame, and a driving arm is provided at the output end of the swing motor. The driving arm passes through the mounting frame and engages with the inside of the swing frame.

[0009] As a further solution of the present invention: a water tank is installed on the top of the mounting frame, a high-pressure pump is provided on the top of the water tank, and the output end of the high-pressure pump is provided with nozzles located on both sides of the friction table; arc plates are provided on both sides of the base, a fan is installed on the outer wall of the arc plate, and multiple groups of nozzles are provided on the inner wall of the arc plate.

[0010] As a further solution of the present invention: a T-shaped slide groove is provided on the swing plate, and a T-shaped slide seat cooperating therewith is fixedly provided on the bottom of the moving skateboard; a swing seat and a limit frame are also fixedly provided on the moving skateboard, and the swing seat is located on the inner side of the limit frame; the linkage frame is movably installed on the swing seat through the swing arm; a drive shaft is fixedly provided at one of the diagonals of the tripod, and a linkage shaft is fixedly provided in the middle of one group of sides of the tripod, and the linkage shaft is located on the opposite side of the drive shaft; the linkage shaft is slidably provided in the limit frame.

[0011] As a further solution of the present invention: a mounting plate located on the side of the moving skateboard is fixedly provided on the swing plate, a driving motor is installed on the mounting plate, and the output end of the driving motor is fixedly connected to the driving shaft; the bottom of the mounting boss is provided with a locking structure that cooperates with the landing gear to be tested.

[0012] As a further solution of the present invention: multiple groups of cylinders are installed at the bottom of the base, a mounting column is provided at the bottom of the friction table, and a mounting cavity cooperating therewith is also provided on the base; multiple groups of locking blocks are arranged at intervals on the outer wall of the mounting column, and multiple groups of locking hoops cooperating with the locking blocks are provided on the inner wall of the mounting cavity.

[0013] As a further solution of the present invention: a drying chamber located above the friction table is fixedly provided on the outer side of the swing shaft, and a drying motor is provided on the top of the drying chamber.

[0014] As a further solution of the present invention: a bearing that cooperates with the rotating shaft is installed on the vertical plate, and a control panel is also provided on the mounting frame.

[0015] As a further solution of the present invention: a testing method for a fatigue testing device for a landing gear buffer, comprising: S1. fixing the landing gear to be tested to the mounting boss by a locking structure, and then selecting one group of landing areas on the friction table; S2. simulating the vertical landing and tilted landing conditions of the landing gear to be tested when the swing plate and the moving slide plate move; S3. visually observing the fatigue degree and critical pressure value of the landing gear to be tested through data from the fatigue sensor and the pressure sensor; S4. rotating the friction table and re-testing the landing areas with different friction coefficients, thereby simulating the influence of different friction coefficients on fatigue.

[0016] The present invention provides an improved fatigue test device and test method for a landing gear buffer. Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present invention utilizes a locking block and a locking hoop to rotate the friction table, thereby simulating the effects of varying friction coefficients on fatigue. Furthermore, the combination of a nozzle and a sprinkler head can simulate the effects of windy and rainy weather on landing gear fatigue. This stable and effective structure enhances the flexibility and practicality of the landing gear buffer fatigue test device.

[0018] 2. The present invention can drive the swing frame and the sector gear to swing back and forth relative to the mounting frame through a swing motor, because the tripod is a triangular structure and the linkage shaft is slidably arranged in the limit frame. Therefore, when the tripod rotates, the moving slide will reciprocate along the T-shaped slide, and the linkage frame will also swing back and forth relative to the swing seat. When the moving slide reciprocates, it can drive the landing gear to be tested at the front end to drag and squeeze the friction table below. And when the swing plate is in a horizontal position, the landing gear to be tested moves vertically downward to simulate normal take-off and landing conditions. When the swing plate tilts to the left, it can simulate the take-off and landing conditions when the landing gear to be tested tilts to the right. When the swing plate tilts to the right, it can simulate the take-off and landing conditions when the landing gear to be tested tilts to the left. This design improves the automation level of the fatigue test device of the landing gear buffer. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further explained below in conjunction with the accompanying drawings and examples:

[0020] Figure 1 It is a three-dimensional structural diagram of the present invention;

[0021] Figure 2 It is the three-dimensional structure of the mounting frame in the present invention Figure 1 ;

[0022] Figure 3 It is the three-dimensional structure of the mounting frame in the present invention Figure 2 ;

[0023] Figure 4 It is a three-dimensional structural diagram of the friction table in the present invention;

[0024] Figure 5 is a cross-sectional view of the friction table of the present invention;

[0025] Figure 6 It is a three-dimensional structural diagram of the motion mechanism of the present invention;

[0026] Figure 7 It is a three-dimensional structural diagram of the swing plate in the present invention;

[0027] Figure 8 It is a three-dimensional structural diagram of the sports skateboard of the present invention;

[0028] Figure 9 It is a three-dimensional structural diagram of the linkage frame in the present invention.

[0029] Description of reference numerals:

[0030] 1. Mounting frame; 101. Vertical plate; 102. Bearing; 103. Swing motor; 104. Drive arm; 105. Rotating shaft; 106. Swing frame; 107. Sector gear; 108. Water tank; 109. High-pressure pump; 110. Sprinkler; 111. Control panel;

[0031] 2. Motion mechanism; 201. Swing shaft; 202. Swing gear; 203. Drying chamber; 204. Drying motor; 205. Swing plate; 206. Detection chamber; 207. Motion slide; 208. Swing seat; 209. Limit frame; 210. Linkage frame; 211. Swing arm; 212. Engagement frame; 213. Mounting boss; 214. Locking structure; 215. Landing gear to be tested; 216. Tripod; 217. Drive shaft; 218. Linkage shaft; 219. Mounting plate; 220. Drive motor; 221. T-type slide; 222. T-type slide; 223. Fatigue sensor;

[0032] 3. Turntable mechanism; 301. Base; 302. Cylinder; 303. Friction table; 304. Landing area; 305. Inspection chamber; 306. Pressure sensor; 307. Mounting column; 308. Locking block; 309. Mounting cavity; 310. Locking hoop; 311. Arc plate; 312. Fan; 313. Nozzle. DETAILED DESCRIPTION

[0033] The following will be combined with the Figures 1 to 9 The technical solutions of the present invention are clearly and completely described. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0034] The present invention provides a fatigue test device for landing gear buffer by improvement. Figures 1-9As shown, it includes a mounting frame 1, a motion mechanism 2 and a turntable mechanism 3. A vertical plate 101 is fixedly provided on the inner side of the mounting frame 1. The motion mechanism 2 includes a swing shaft 201 movably provided between the vertical plate 101 and the mounting frame 1. A swing plate 205 simulating left and right swinging is provided in the middle of the swing shaft 201. A detection cavity 206 is provided on the swing plate 205. A motion slide 207 simulating forward and backward motion is slidably provided on the swing plate 205. A linkage frame 210 is swingably provided on the motion slide 207. The linkage frame 210 consists of a swing arm 211 and an engagement frame 212. A tripod 216 is movably provided in the engagement frame 212. A mounting Boss 213, the bottom of which is detachably mounted a landing gear 215 to be tested, and a fatigue sensor 223 is mounted on the bottom of the mounting boss 213; the turntable mechanism 3 includes a base 301 located below the detection chamber 206, and a friction platform 303 is movably provided on the top of the base 301, and the friction platform 303 includes multiple landing areas 304 with different friction coefficients; a detection chamber 305 is provided inside the landing area 304, and a pressure sensor 306 is installed in the detection chamber 305; when the tripod 216 rotates in the engagement frame 212 and the swing plate 205 swings left and right, a landing simulation test can be performed on the bottom and both sides of the landing gear 215 to be tested.

[0035] In this embodiment, the fatigue testing apparatus for landing gear buffers consists of three main components: a mounting frame 1, a motion mechanism 2, and a turntable mechanism 3. To operate, the landing gear 215 to be tested is first mounted on the locking structure 214. The swing motor 103 and the drive motor 220 are then activated. As the drive motor 220 rotates the tripod 216, the motion slide 207 reciprocates along the T-shaped slot 221, and the linkage frame 210 also oscillates relative to the swing seat 208. The front landing gear 215 to be tested then drags and compresses the friction platform 303 below. Data from the fatigue sensor 223 and the pressure sensor 306 can be used to visually measure the fatigue level and critical damage pressure of the landing gear 215 to be tested. As the sector teeth 107 drive the swing gear 202 to oscillate back and forth, the contact point between the tire at the bottom of the landing gear 215 to be tested and the friction platform 303 can be adjusted. When the swing plate 205 tilts to the left, it can simulate the landing condition of the landing gear 215 to be tested tilted to the right. When the swing plate 205 tilts to the right, it can simulate the landing condition of the landing gear 215 to be tested tilted to the left. When different weather conditions need to be simulated, the high-pressure pump 109 and the fan 312 can be controlled to open and close to simulate sunny days, rainy days, and strong winds.

[0036] See attached Figure 1 and attached Figure 6A rotating shaft 105 is movably mounted on the inner wall of the mounting frame 1, a swing frame 106 is provided in the middle of the rotating shaft 105, and a sector tooth 107 is provided on the outer side of the rotating shaft 105; a swing gear 202 meshing with the sector tooth 107 is fixedly connected to the inner side of the swing shaft 201.

[0037] In this embodiment, when the sector teeth 107 drive the swing gear 202 to swing back and forth, the contact point between the tire at the bottom of the landing gear 215 to be tested and the friction platform 303 can be adjusted, thereby simulating the landing situation of a helicopter with a swaying fuselage in an emergency.

[0038] See attached Figure 1 -Attached Figure 2 A swing motor 103 is also installed on the outside of the mounting frame 1. A driving arm 104 is provided at the output end of the swing motor 103. The driving arm 104 passes through the mounting frame 1 and engages with the inside of the swing frame 106.

[0039] In this embodiment, driven by the swing motor 103 , the driving arm 104 rotates and drives the swing frame 106 and the sector teeth 107 to swing back and forth.

[0040] See attached Figure 1 -Attached Figure 3 A water tank 108 is installed on the top of the mounting frame 1, and a high-pressure pump 109 is provided on the top of the water tank 108. The output end of the high-pressure pump 109 is provided with nozzles 110 located on both sides of the friction table 303; arc plates 311 are provided on both sides of the base 301, and a fan 312 is installed on the outer wall of the arc plate 311, and multiple groups of nozzles 313 are provided on the inner wall of the arc plate 311.

[0041] In this embodiment, to further increase the degree of freedom and thus simulate takeoff and landing conditions in different weather conditions, a nozzle 110 and a nozzle 313 structure are designed. When sunny weather needs to be simulated, the high-pressure pump 109 and the fan 312 are both turned off. When windy weather needs to be simulated, the high-pressure pump 109 is turned off and the fan 312 is turned on. When rainy weather needs to be simulated, the high-pressure pump 109 is turned on and the fan 312 is turned off. When windy and rainy weather needs to be simulated, the high-pressure pump 109 and the fan 312 are both turned on. In addition, different weather conditions and the friction table 303 with different friction coefficients can simulate landing gear fatigue in various conditions.

[0042] See attached Figure 6 -Attached Figure 9A T-shaped slide 221 is provided on the swing plate 205, and a T-shaped slide 222 is fixedly provided at the bottom of the moving skateboard 207; a swing seat 208 and a limit frame 209 are also fixedly provided on the moving skateboard 207, and the swing seat 208 is located on the inner side of the limit frame 209; the linkage frame 210 is movably mounted on the swing seat 208 through the swing arm 211; a drive shaft 217 is fixedly provided at one of the diagonal parts of the tripod 216, and a linkage shaft 218 is fixedly provided in the middle of one group of sides of the tripod 216, and the linkage shaft 218 is located on the opposite side of the drive shaft 217; the linkage shaft 218 is slidably set in the limit frame 209.

[0043] In this embodiment, because the tripod 216 has a triangular structure and the linkage shaft 218 is slidably mounted within the limiting frame 209, when the tripod 216 rotates, the moving slide 207 reciprocates along the T-shaped slot 221, and the linkage frame 210 also oscillates relative to the swinging base 208. The front landing gear 215 under test drags and compresses the friction platform 303 below. The motion trajectory of the landing gear 215 under test is relatively complex, but can be simplified to horizontal reciprocating sliding and reciprocating swinging relative to the swinging base 208. Because the motion trajectory of the landing gear 215 under test is arc-shaped, the pressure exerted by the landing gear 215 on the bottom friction platform 303 varies. Furthermore, when the swinging plate 205 is horizontal, the landing gear 215 under test moves vertically downward, simulating a normal takeoff and landing. When the swinging plate 205 tilts to the left, it simulates a takeoff and landing condition when the landing gear 215 tilts to the right. When the swing plate 205 tilts to the right, it can simulate the landing condition of the landing gear 215 to be tested tilting to the left.

[0044] See attached Figure 6 -Attached Figure 9 A mounting plate 219 located on the side of the moving skateboard 207 is also fixedly provided on the swing plate 205, and a driving motor 220 is installed on the mounting plate 219. The output end of the driving motor 220 is fixedly connected to the driving shaft 217; the bottom of the mounting boss 213 is provided with a locking structure 214 that cooperates with the landing gear 215 to be tested.

[0045] In this embodiment, a driving motor 220 is provided to drive the tripod 216 to rotate, and a locking structure 214 is provided to facilitate rapid assembly and disassembly of the landing gear 215 to be tested.

[0046] See attached Figure 2 and attached Figure 4Multiple groups of cylinders 302 are installed at the bottom of the base 301, and a mounting column 307 is provided at the bottom of the friction table 303. The base 301 is also provided with a mounting cavity 309 that cooperates with it; multiple groups of locking blocks 308 are arranged at intervals on the outer wall of the mounting column 307, and multiple groups of locking hoops 310 that cooperate with the locking blocks 308 are provided on the inner wall of the mounting cavity 309.

[0047] In this embodiment, to further increase the degree of flexibility and allow for adjustments to landing zones 304 with varying friction coefficients based on actual needs, a cooperating locking block 308 and locking hoop 310 structure is designed. Since there are four sets of landing zones 304, there are also four sets of locking blocks 308 and locking hoops 310. When a locking block 308 locks with an adjacent locking hoop 310, the friction platform 303 rotates 90 degrees clockwise or counterclockwise. The height of the friction platform 303 can be adjusted via the cylinder 302, further adjusting the distance between the landing gear 215 under test and the friction platform 303. This structure allows for adjustable compressive force during testing.

[0048] See attached Figure 1 and attached Figure 6 A drying chamber 203 located above the friction platform 303 is fixedly provided on the outside of the swing shaft 201 , and a drying motor 204 is provided on the top of the drying chamber 203 .

[0049] In this embodiment, when the nozzle 110 is turned on to simulate the effect of rain on the landing gear, a large amount of water stains will remain on the friction table 303. In order to dry them and avoid interference with subsequent tests, a coordinated drying chamber 203 is designed.

[0050] See attached Figure 1 -Attached Figure 2 A bearing 102 that cooperates with the rotating shaft 105 is installed on the vertical plate 101, and a control panel 111 is also provided on the mounting frame 1.

[0051] In this embodiment, a control panel 111 is designed to control the operation of the device.

[0052] The operating principle of the present invention is as follows: During operation, the landing gear 215 to be tested is first mounted on the locking structure 214. The swing motor 103 and drive motor 220 are then activated. As the drive motor 220 drives the tripod 216 to rotate, the moving slide 207 reciprocates along the T-shaped slot 221, and the linkage frame 210 also oscillates relative to the swing seat 208. The front landing gear 215 to be tested then drags and compresses the friction platform 303 below. Data from the fatigue sensor 223 and pressure sensor 306 can then be used to visually measure the fatigue level and critical damage pressure of the landing gear 215 to be tested. As the sector teeth 107 drive the swing gear 202 to oscillate back and forth, the contact point between the tire at the bottom of the landing gear 215 to be tested and the friction platform 303 can be adjusted. When the swing plate 205 tilts to the left, it simulates the landing and take-off conditions of the landing gear 215 to be tested tilting to the right. When the swing plate 205 tilts to the right, the landing condition of the landing gear 215 to be tested tilting to the left can be simulated. When different weather conditions need to be simulated, the high pressure pump 109 and the fan 312 can be controlled to open and close to simulate sunny days, rainy days and strong winds.

[0053] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and inventive features disclosed herein.

Claims

1. A fatigue test device for a landing gear buffer, comprising a mounting frame (1), a motion mechanism (2) and a turntable mechanism (3), characterized in that: A vertical plate (101) is fixedly provided on the inner side of the mounting frame (1); the motion mechanism (2) comprises a swing shaft (201) movably provided between the vertical plate (101) and the mounting frame (1); a swing plate (205) simulating left and right swinging is provided in the middle of the swing shaft (201); a detection cavity (206) is provided on the swing plate (205); A motion slide plate (207) simulating forward and backward motion is slidably provided on the swing plate (205); a linkage frame (210) is swingably provided on the motion slide plate (207); the linkage frame (210) is composed of a swing arm (211) and an engagement frame (212); a tripod (216) is movably installed in the engagement frame (212); a mounting boss (213) is provided at the front end of the engagement frame (212); a landing gear (215) to be tested is detachably mounted on the bottom of the mounting boss (213); a fatigue sensor (223) is installed at the bottom of the mounting boss (213); a swing seat (208) and a limit frame (209) are also fixedly provided on the motion slide plate (207); the swing seat (208) is located inside the limit frame (209); The turntable mechanism (3) comprises a base (301) located below the detection chamber (206); a friction platform (303) is movably provided on the top of the base (301); the friction platform (303) comprises a plurality of landing areas (304) with different friction coefficients; a detection chamber (305) is provided inside the landing area (304); a pressure sensor (306) is installed in the detection chamber (305); when the tripod (216) rotates in the engagement frame (212) and the swing plate (205) swings left and right, a landing simulation test can be performed on the bottom and both sides of the landing gear (215) to be tested.

2. A fatigue testing device for a landing gear buffer according to claim 1, characterized in that: A rotating shaft (105) is movably mounted on the inner wall of the mounting frame (1), a swing frame (106) is provided in the middle of the rotating shaft (105), and sector teeth (107) are provided on the outer side of the rotating shaft (105); a swing gear (202) meshing with the sector teeth (107) is fixedly connected to the inner side of the swing shaft (201).

3. A fatigue testing device for a landing gear buffer according to claim 2, characterized in that: A swing motor (103) is also installed on the outside of the mounting frame (1), and a driving arm (104) is provided at the output end of the swing motor (103). The driving arm (104) passes through the mounting frame (1) and engages with the inside of the swing frame (106).

4. A fatigue testing device for a landing gear buffer according to any one of claims 1 to 3, characterized in that: A water tank (108) is installed on the top of the mounting frame (1), a high-pressure pump (109) is provided on the top of the water tank (108), and nozzles (110) are provided at the output end of the high-pressure pump (109) and are located on both sides of the friction table (303); arc plates (311) are provided on both sides of the base (301), a fan (312) is installed on the outer wall of the arc plate (311), and multiple groups of nozzles (313) are provided on the inner wall of the arc plate (311).

5. A fatigue testing device for a landing gear buffer according to any one of claims 1 to 3, characterized in that: The swing plate (205) is provided with a T-shaped slide groove (221), and the bottom of the moving slide plate (207) is fixedly provided with a T-shaped slide seat (222) matched therewith; the linkage frame (210) is movably mounted on the swing seat (208) through the swing arm (211); a driving shaft (217) is fixedly provided at one of the diagonal positions of the tripod (216), and a linkage shaft (218) is fixedly provided at the middle of one group of sides of the tripod (216), and the linkage shaft (218) is located on the opposite side of the driving shaft (217); the linkage shaft (218) is slidably provided in the limit frame (209).

6. A fatigue testing device for a landing gear buffer according to claim 5, characterized in that: The swing plate (205) is further fixedly provided with a mounting plate (219) located on the side of the moving slide plate (207); a driving motor (220) is mounted on the mounting plate (219); an output end of the driving motor (220) is fixedly connected to the driving shaft (217); and a locking structure (214) is provided at the bottom of the mounting boss (213) for cooperating with the landing gear (215) to be tested.

7. A fatigue testing device for a landing gear buffer according to any one of claims 1 to 3, characterized in that: The bottom of the base (301) is equipped with multiple groups of cylinders (302), the bottom of the friction platform (303) is provided with a mounting column (307), and the base (301) is also provided with a mounting cavity (309) that cooperates with the mounting column; multiple groups of locking blocks (308) are arranged at intervals on the outer wall of the mounting column (307), and multiple groups of locking hoops (310) that cooperate with the locking blocks (308) are arranged on the inner wall of the mounting cavity (309).

8. The fatigue testing device for landing gear buffer according to claim 1, characterized in that: A drying chamber (203) located above the friction platform (303) is fixedly provided on the outer side of the swing shaft (201), and a drying motor (204) is provided on the top of the drying chamber (203).

9. The fatigue testing device for landing gear buffer according to claim 2, characterized in that: A bearing (102) that cooperates with the rotating shaft (105) is installed on the vertical plate (101), and a control panel (111) is also provided on the mounting frame (1).

10. A testing method for a fatigue testing device for a landing gear buffer according to any one of claims 1 to 9, characterized in that: S1. The landing gear to be tested (215) is fixed to the mounting boss (213) by the locking structure (214), and then a set of landing areas (304) on the friction table (303) is selected; S2. When the swing plate (205) and the motion slide (207) are in motion, the vertical take-off and landing conditions and the tilted take-off and landing conditions of the landing gear (215) to be tested are simulated; S3. The fatigue level and the critical pressure value of the landing gear (215) to be tested are visually observed through the data of the fatigue sensor (223) and the pressure sensor (306); S4. The friction table (303) is rotated to retest the landing area (304) with different friction coefficients, thereby simulating the influence of different friction coefficients on fatigue.

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