Fatigue test device for undercarriage buffer and test method thereof

Abstract

The invention discloses a fatigue test device for an undercarriage buffer and a test method thereof, and belongs to the technical field of undercarriages, a motion mechanism comprises a swing shaft movably arranged between a vertical plate and a mounting rack, a swing plate for simulating left-right swing is arranged in the middle of the swing shaft, and a linkage frame is arranged on a motion sliding plate in a swing mode; a tripod is movably mounted in the meshing frame, and a to-be-tested undercarriage is detachably mounted at the bottom of the mounting boss; the rotary table mechanism comprises a base located below the detection cavity, a friction table is movably arranged at the top of the base, and the friction table comprises a plurality of falling areas with different friction coefficients; a detection bin is formed in the landing area, and a pressure sensor is installed in the detection bin. The friction table can be rotated through the locking block and the locking hoop, so that the influence of different friction coefficients on the fatigue degree is simulated, the influence of strong wind and rain on the fatigue degree can be simulated through the spray head and the spray nozzle, the structure is stable and effective, and the degree of freedom and practicability of the test device are also improved.

Description

Technical Field

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

[0002] The aircraft landing gear is an important part of the aircraft, mainly used to provide support on the ground and in the air. Its main functions include supporting the weight of the aircraft, helping takeoff and landing, and ensuring stability when taxiing on the ground. The landing gear usually includes the main landing gear, the front landing gear and the shock absorption system. The main landing gear is located on both sides of the aircraft, and the front landing gear is located at the front of the aircraft. The shock absorption system is designed to absorb the impact force generated during landing, reduce the impact on the fuselage and passengers, and ensure the stability of the flight. After long-term use, the landing gear will produce metal fatigue, which will affect the overall safety performance and operational stability of the aircraft. Therefore, fatigue testing of the landing gear is a crucial link to ensure the safe operation of the aircraft.

[0003] The patent application with publication number CN114543672A discloses a landing gear shape and position tolerance detection platform, which includes: a support assembly including a first support member and a second support member supporting the landing gear; a scanning assembly including a scanning member and a scanning driving member, the scanning driving member is connected to the scanning member in a transmission manner to drive the scanning member to move relative to the first support member, and the scanning member has a detection end for detecting the first support member; a contact assembly including a contact head, a contact driving member and a distance sensor, the contact driving member is connected to the contact head in a transmission manner to drive the contact head to move relative to the second support member, the contact head has a contact end for pressing the landing gear, and the distance sensor detects the spatial position of the contact end. A data processor is electrically connected to the scanning member and the distance sensor respectively, and is used to receive the image scanned by the scanning member and the spatial position information collected by the distance sensor to obtain the dimensional parameters of the landing gear. The dimensional parameters of the landing gear are measured efficiently and quickly by visually measuring some dimensional parameters of the landing gear and using the contact assembly for supplementary measurement.

[0004] The above-disclosed landing gear inspection platform has a general degree of automation and freedom. When inspecting the landing gear, it is not possible to perform extrusion friction tests on the front and side of the tire from multiple angles. In addition, the inspection mode is single and it is not possible to freely select a variety of ground surfaces with different friction coefficients or simulate the landing and take-off conditions of the landing gear in different weather conditions according to actual needs. Therefore, in view of the above status quo, it is urgent to develop a fatigue test device for the landing gear buffer to overcome the shortcomings in current practical applications. Summary of the invention

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

[0006] To achieve the above-mentioned purpose, the technical scheme 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, wherein a vertical plate is fixedly arranged on the inner side of the mounting frame, the motion mechanism comprises a swing shaft movably arranged between the vertical plate and the mounting frame, a swing plate simulating left and right swinging is arranged in the middle of the swing shaft, and a detection cavity is provided on the swing plate; a motion slide plate simulating forward and backward motion is slidably arranged on the swing plate, a linkage frame is swingably arranged on the motion slide plate, and the linkage frame consists of two parts: a swing arm and an engagement frame; three parts are movably installed 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 a landing gear to be tested, and a fatigue sensor is installed at the bottom of the mounting boss; the turntable mechanism includes a base located below the detection cavity, a friction table is movably arranged on the top of the base, 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 also installed on the outer side 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 arranged 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 arranged on both sides of the base, a fan is installed on the outer wall of the arc plate, and multiple groups of nozzles are arranged 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 with the T-shaped slide seat 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 driving 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 driving 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 sports skateboard is fixedly arranged 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; a locking structure cooperating with the landing gear to be tested is arranged at the bottom of the mounting boss.

[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 matching the mounting column is 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 matching the locking blocks are arranged 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 matched with the rotating shaft is installed on the vertical plate, and a control panel is also arranged on the mounting frame.

[0015] As a further solution of the present invention: a test method for a fatigue test 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 inclined 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 the data of 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 a fatigue test device and a test method for a landing gear buffer through improvement. Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention can rotate the friction table through the cooperation of the locking block and the locking hoop, thereby simulating the influence of different friction coefficients on fatigue. In addition, the cooperation of the nozzle and the nozzle can simulate the influence of windy weather and rainy weather on the fatigue of the landing gear. The structure is stable and effective, and also improves the freedom and practicality of the fatigue test device of the landing gear buffer.

[0017] 2. The present invention can drive the swing frame and the fan-shaped teeth 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 plate will reciprocate along the T-shaped slide groove, and the linkage frame will also swing back and forth relative to the swing seat. When the moving slide plate 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 a normal landing condition. When the swing plate tilts to the left, it can simulate the landing condition of the landing gear to be tested when it tilts to the right. When the swing plate tilts to the right, it can simulate the landing condition of the landing gear to be tested when it 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

[0018] The present invention will be further explained below in conjunction with the accompanying drawings and embodiments: Figure 1 It is a three-dimensional structural diagram of the present invention; Figure 2 It is the three-dimensional structure of the mounting frame in the present invention Figure 1 ; Figure 3 It is the three-dimensional structure of the mounting frame in the present invention Figure 2 ; Figure 4 It is a three-dimensional structural diagram of the friction table in the present invention; Figure 5 is a cross-sectional view of the friction table of the present invention; Figure 6 It is a three-dimensional structural diagram of the motion mechanism in the present invention; Figure 7 It is a three-dimensional structural diagram of the swing plate in the present invention; Figure 8 It is a three-dimensional structural diagram of the sports skateboard of the present invention; Fig. 9 It is a three-dimensional structural diagram of the linkage frame in the present invention.

[0019] Description of reference numerals: 1. Mounting frame; 101. Vertical plate; 102. Bearing; 103. Swing motor; 104. Driving arm; 105. Rotating shaft; 106. Swing frame; 107. Sector gear; 108. Water tank; 109. High-pressure pump; 110. Sprinkler; 111. Control panel; 2. Motion mechanism; 201. Swinging shaft; 202. Swinging gear; 203. Drying chamber; 204. Drying motor; 205. Swinging plate; 206. Detection chamber; 207. Motion slide plate; 208. Swinging seat; 209. Limiting frame; 210. Linkage frame; 211. Swing arm; 212. Engagement frame; 213. Mounting boss; 214. Locking structure; 215. Undercarriage to be tested; 216. Tripod; 217. Driving shaft; 218. Linkage shaft; 219. Mounting plate; 220. Driving motor; 221. T-type slide; 222. T-type slide seat; 223. Fatigue sensor; 3. Turntable mechanism; 301. Base; 302. Cylinder; 303. Friction table; 304. Landing area; 305. Detection 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

[0020] The following will be combined with the attached Figures 1 to 9 The technical solution of the present invention is described clearly and completely. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] The present invention provides a fatigue test device for a landing gear buffer by improvement, such as Figure 1-Figure 9As shown, it includes a mounting frame 1, a motion mechanism 2 and a turntable mechanism 3. A vertical plate 101 is fixedly arranged on the inner side of the mounting frame 1. The motion mechanism 2 includes a swing shaft 201 movably arranged between the vertical plate 101 and the mounting frame 1. A swing plate 205 simulating left and right swinging is arranged in the middle of the swing shaft 201. A detection cavity 206 is opened on the swing plate 205; a motion slide plate 207 simulating forward and backward motion is slidably arranged on the swing plate 205, and a linkage frame 210 is swingably arranged on the motion slide plate 207. The linkage frame 210 consists of a swing arm 211 and an engagement frame 212; a tripod 216 is movably installed in the engagement frame 212, and a mounting The boss 213 has a landing gear 215 to be tested detachably mounted on the bottom of the mounting boss 213, 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, a friction table 303 is movably arranged on the top of the base 301, and the friction table 303 includes a plurality of 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 meshing 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.

[0022] In this embodiment: the fatigue test device for the landing gear buffer is mainly divided into three parts: the mounting frame 1, the motion mechanism 2 and the turntable mechanism 3. When the device is working, the landing gear 215 to be tested is first installed on the locking structure 214. Then the swing motor 103 and the driving motor 220 are started. When the driving motor 220 drives the tripod 216 to rotate, the motion slide plate 207 will reciprocate along the T-shaped slide 221, and the linkage frame 210 will also reciprocate relative to the swing seat 208, and the front landing gear 215 to be tested will drag and squeeze the friction table 303 below. At this time, the fatigue degree and the critical pressure value of the landing gear 215 to be tested can be intuitively obtained through the data of the fatigue sensor 223 and the pressure sensor 306. When the sector tooth 107 drives 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 table 303 can be adjusted. When the swing plate 205 tilts to the left, the landing condition of the landing gear 215 to be tested tilted to the right can be simulated. When the swing plate 205 tilts to the right, the landing condition of the landing gear 215 to be tested tilted to the left can be simulated. When different weather conditions need to be simulated, the opening and closing conditions of the high-pressure pump 109 and the fan 312 can be controlled to simulate sunny days, rainy days and strong winds.

[0023] 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 arranged in the middle of the rotating shaft 105, and a sector tooth 107 is arranged 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.

[0024] 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 the helicopter with the fuselage swaying in an emergency.

[0025] See attached Figure 1 -Attached Figure 2 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 .

[0026] 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.

[0027] See attached Figure 1 -Attached Figure 3 A water tank 108 is installed on the top of the mounting frame 1, a high-pressure pump 109 is arranged on the top of the water tank 108, and nozzles 110 located on both sides of the friction table 303 are arranged at the output end of the high-pressure pump 109; arc plates 311 are arranged 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 arranged on the inner wall of the arc plate 311.

[0028] In this embodiment: In order to further improve the degree of freedom and simulate the take-off and landing conditions under different weather conditions, a nozzle 110 and a nozzle 313 structure are designed. When it is necessary to simulate sunny weather, the high-pressure pump 109 and the fan 312 are both turned off. When it is necessary to simulate windy weather, the high-pressure pump 109 is turned off and the fan 312 is turned on. When it is necessary to simulate rainy weather, the high-pressure pump 109 is turned on and the fan 312 is turned off. When it is necessary to simulate windy and rainy weather, the high-pressure pump 109 and the fan 312 are both turned on. In addition, different weather and the friction table 303 with different friction coefficients can simulate the fatigue of the landing gear under various conditions.

[0029] See attached Figure 6 -Attached Fig. 9A T-shaped slide groove 221 is provided on the swing plate 205, and a T-shaped slide seat 222 cooperating therewith is fixedly provided at the bottom of the moving slide plate 207; a swing seat 208 and a limit frame 209 are also fixedly provided on the moving slide plate 207, and the swing seat 208 is located on the inner side of the limit frame 209; the linkage frame 210 is movably installed on the swing seat 208 through the swing arm 211; a driving shaft 217 is fixedly provided at one of the diagonals of the tripod 216, and a linkage shaft 218 is fixedly provided in the middle of one group of side lengths 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.

[0030] In this embodiment: since the tripod 216 is a triangular structure and the linkage shaft 218 is slidably arranged in the limit frame 209, when the tripod 216 rotates, the moving slide plate 207 will reciprocate along the T-shaped slide groove 221, and the linkage frame 210 will also reciprocate relative to the swing seat 208. The landing gear 215 to be tested at the front end drags and squeezes the friction platform 303 below. The motion trajectory of the landing gear 215 to be tested is relatively complex and can be simplified to reciprocating sliding in the horizontal direction and reciprocating swinging relative to the swing seat 208. Since the motion trajectory of the landing gear 215 to be tested is an arc, the landing gear 215 to be tested has a variable squeezing force when squeezing the friction platform 303 at the bottom. And when the swing plate 205 is in a horizontal position, the landing gear 215 to be tested moves vertically downward to simulate a normal landing condition. When the swing plate 205 tilts to the left, the landing condition when the landing gear 215 to be tested tilts to the right can be simulated. 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.

[0031] See attached Figure 6 -Attached Fig. 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, and the output end of the driving motor 220 is fixedly connected to the driving shaft 217; a locking structure 214 cooperating with the landing gear 215 to be tested is provided at the bottom of the mounting boss 213.

[0032] In this embodiment, a driving motor 220 is designed to drive the tripod 216 to rotate. A locking structure 214 is designed to quickly disassemble and assemble the landing gear 215 to be tested.

[0033] See attached Figure 2 and attached Figure 4A plurality of cylinders 302 are installed at the bottom of the base 301, a mounting column 307 is provided at the bottom of the friction table 303, and a mounting cavity 309 cooperating therewith is also provided on the base 301; a plurality of locking blocks 308 are arranged at intervals on the outer wall of the mounting column 307, and a plurality of locking hoops 310 cooperating with the locking blocks 308 are arranged on the inner wall of the mounting cavity 309.

[0034] In this embodiment, in order to further improve the degree of freedom, so as to adjust the landing area 304 with different friction coefficients according to actual needs, a locking block 308 and a locking hoop 310 structure that cooperate with each other are designed. The landing area 304 is designed with four groups, so the locking block 308 and the locking hoop 310 are also designed with four groups. When the locking block 308 is locked with the adjacent locking hoop 310, the friction table 303 will rotate 90 degrees clockwise or counterclockwise. The height of the friction table 303 can be adjusted by the cylinder 302, so as to further adjust the distance between the landing gear 215 to be tested and the friction table 303, so that the structure can adjust the extrusion force during the test.

[0035] See attached Figure 1 and attached Figure 6 A drying chamber 203 located above the friction platform 303 is fixedly arranged on the outer side of the swing shaft 201 , and a drying motor 204 is arranged on the top of the drying chamber 203 .

[0036] 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.

[0037] See attached Figure 1 -Attached Figure 2 A bearing 102 that matches the rotating shaft 105 is installed on the vertical plate 101, and a control panel 111 is also provided on the mounting frame 1.

[0038] In this embodiment, a control panel 111 is designed to control the operation of the device.

[0039] The working principle of the present invention is as follows: when the device is working, the landing gear 215 to be tested is first installed on the locking structure 214. Then the swing motor 103 and the driving motor 220 are started. When the driving motor 220 drives the tripod 216 to rotate, the moving slide plate 207 will reciprocate along the T-shaped slide groove 221, and the linkage frame 210 will also reciprocate relative to the swing seat 208, and the landing gear 215 to be tested at the front end will drag and squeeze the friction table 303 below. At this time, the fatigue degree and the critical pressure value of the landing gear 215 to be tested can be intuitively obtained through the data of the fatigue sensor 223 and the pressure sensor 306. When the sector tooth 107 drives 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 table 303 can be adjusted. When the swing plate 205 tilts to the left, the landing condition of the landing gear 215 to be tested when it tilts to the right can be simulated. When the swing plate 205 tilts to the right, the landing condition of the landing gear 215 to be tested tilts to the left can be simulated. When different weather conditions need to be simulated, the opening and closing conditions of the high-pressure pump 109 and the fan 312 can be controlled to simulate sunny days, rainy days and strong winds.

[0040] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those 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 will not be limited to the embodiments shown herein, but will 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 arranged on the inner side of the mounting frame (1), the movement mechanism (2) comprises a swing shaft (201) movably arranged between the vertical plate (101) and the mounting frame (1), a swing plate (205) simulating left and right swinging is arranged in the middle of the swing shaft (201), and a detection cavity (206) is provided on the swing plate (205); A motion slide plate (207) simulating forward and backward motion is slidably disposed on the swing plate (205); a linkage frame (210) is swingably disposed 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 mounted in the engagement frame (212); a mounting boss (213) is disposed 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); and a fatigue sensor (223) is mounted on the bottom of the mounting boss (213); The turntable mechanism (3) comprises a base (301) located below the detection chamber (206); a friction table (303) is movably provided on the top of the base (301); the friction table (303) comprises a plurality of landing areas (304) having different friction coefficients; a detection chamber (305) is provided inside the landing area (304); a pressure sensor (306) is installed inside the detection chamber (305); when the tripod (216) rotates in the meshing 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 test 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 arranged in the middle of the rotating shaft (105), and sector teeth (107) are arranged 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 test 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 meshes with the inside of the swing frame (106).

4. A fatigue test 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 arranged on the top of the water tank (108), and nozzles (110) are arranged 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 arranged on both sides of the base (301), a fan (312) is installed on the outer wall of the arc plate (311), and a plurality of groups of nozzles (313) are arranged on the inner wall of the arc plate (311).

5. A fatigue test 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 a T-shaped slide seat (222) cooperating therewith is fixedly provided at the bottom of the moving slide plate (207); a swing seat (208) and a limit frame (209) are also fixedly provided on the moving slide plate (207), and the swing seat (208) is located inside the limit frame (209); 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 portions of the tripod (216), and a linkage shaft (218) is fixedly provided at the middle of one set of side lengths 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 test device for a landing gear buffer according to claim 5, characterized in that: The swing plate (205) is also fixedly provided with a mounting plate (219) located on the side of the motion slide plate (207); a drive motor (220) is mounted on the mounting plate (219); an output end of the drive motor (220) is fixedly connected to the drive shaft (217); and a locking structure (214) cooperating with the landing gear (215) to be tested is provided at the bottom of the mounting boss (213).

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

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

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

10. A test method for a fatigue test device for a landing gear buffer according to any one of claims 1 to 9, characterized in that: S1. The landing gear (215) to be tested is fixed to the mounting boss (213) by means of a locking structure (214), and then one set of landing areas (304) on the friction table (303) is selected; S2. When the swing plate (205) and the motion slide plate (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. Visually observe the fatigue degree and the critical pressure value of the undercarriage (215) to be tested through the data of the fatigue sensor (223) and the pressure sensor (306); S4. Rotate the friction table (303) to retest the landing area (304) with different friction coefficients, thereby simulating the influence of different friction coefficients on fatigue.

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