An aircraft caster with MoS high temperature resistant coating

Abstract

The invention discloses an aircraft caster with a MoS high temperature resistant coating, belonging to the field of aircraft casters. The aircraft caster with a MoS high temperature resistant coating comprises a landing gear and a moving wheel coated with a MoS layer, a vertical rod is slidably connected in the landing gear, a cross rod is fixedly connected at the bottom of the vertical rod, the moving wheel is rotatably connected to the cross rod, a brake disc is fixedly connected to the moving wheel, a cavity is provided between the vertical rod and the cross rod and is filled with hydraulic oil, an oil pipe is fixedly connected to the piston cylinder and is connected to the cavity between the vertical rod and the cross rod through the oil pipe, and a pressure valve is provided on the oil pipe. When the hydraulic oil between the landing gear and the vertical rod flows into the piston cylinder through the oil pipe, the piston rod in the piston cylinder will be pushed by the hydraulic rod and move in a direction close to the brake disc, and the brake pad can contact the brake disc, so that the brake pad can slide relative to the brake disc at this time, thereby assisting the aircraft to decelerate.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft casters, in particular to an aircraft caster with a MoS high temperature resistant coating. Background Art

[0002] There are many types of aircraft with a wide range of applications. According to their purpose, there are civil aircraft and military aircraft. According to the type of aircraft engine, there are propeller aircraft and jet aircraft. According to the number of engines, there are single-engine aircraft, twin-engine aircraft, three-engine aircraft, and four-engine aircraft. According to the flight speed, there are subsonic aircraft and supersonic aircraft. According to the range of the aircraft, there are short-range, medium-range, and long-range aircraft.

[0003] In the prior art, large aircraft mostly use engine reverse thrust to decelerate during landing, while small aircraft (such as agricultural machinery, etc.) generally use caster brakes to decelerate during landing. In the prior art, the pilot generally manually operates the caster brakes, which makes the operation cumbersome and may cause the pilot to be distracted and cause an accident. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft caster with a MoS high temperature resistant coating, which has the advantage of being able to automatically brake the caster during landing, thereby solving the problem of complex operation of existing devices.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an aircraft caster with a MoS high-temperature resistant coating, comprising a landing gear and a moving wheel coated with a MoS layer, wherein a vertical rod is slidably connected inside the landing gear, a cross rod is fixedly connected to the bottom of the vertical rod, the moving wheel is rotatably connected to the cross rod, a brake disc is fixedly connected to the moving wheel, a fixing frame is fixedly connected to the vertical rod and the cross rod, a gear ring is fixedly connected to the fixing frame, a sector plate is fixedly connected to the gear ring, a piston cylinder is fixedly connected to the sector plate, a piston rod is slidably connected inside the piston cylinder, a brake pad is fixedly connected to one end of the piston rod away from the piston cylinder, the brake pad is intermittently slidably connected to the brake disc, a cavity is opened between the vertical rod and the cross rod and is filled with hydraulic oil, an oil pipe is fixedly connected to the piston cylinder and is connected to the cavity between the vertical rod and the cross rod through the oil pipe, and a pressure valve is provided on the oil pipe.

[0006] Preferably, a sun gear is rotatably connected to the cross bar, and a mounting cylinder is coaxially fixedly connected to an end face of the sun gear close to the brake disc, the inner diameter of the mounting cylinder is slightly larger than the outer diameter of the cross bar, and a cylinder is slidably connected to the mounting cylinder via a keyway, and a swivel is rotatably connected to the cylinder, and the swivel is fixedly connected to the piston rod.

[0007] Preferably, a plug rod is slidably connected to the side wall of the cylinder, a spring is fixedly connected between the plug rod and the cylinder, a slot cooperating with the plug rod is opened on the brake disc, the number of the plug rods is specifically five, and the five plug rods are evenly distributed on the cylinder in a circle.

[0008] Preferably, a planet carrier is rotatably connected to the crossbar, a planet gear is rotatably connected to the planet carrier, and both the sun gear and the ring gear are meshed with the planet gear.

[0009] Preferably, a hollow ring is fixedly connected to the fixed frame, an annular impeller is fixedly connected to the planetary frame, and the annular impeller is rotatably connected in the hollow ring.

[0010] Preferably, a box is fixedly connected to the fixing frame, the box is filled with fluorinated liquid, a first pipe is fixedly connected to the box, one end of the first pipe away from the box is connected to the cavity in the hollow ring, a Tesla valve is provided in the middle of the first pipe, and the Tesla valve is fixedly connected to the fixing frame.

[0011] Preferably, a cavity is provided in the brake pad, a second pipe is fixedly connected to the hollow ring, and an end of the second pipe away from the hollow ring is communicated with the cavity in the brake pad.

[0012] Preferably, a third pipe is fixedly connected to the box body, and one end of the third pipe (46) away from the box body is communicated with the cavity in the brake pad.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. When the hydraulic oil between the landing gear and the vertical rod flows into the piston cylinder through the oil pipe, the piston rod in the piston cylinder will be pushed by the hydraulic rod to move toward the brake disc, and the brake pad will be able to contact the brake disc, so that the brake pad can slide relative to the brake disc at this time, thereby assisting the aircraft to decelerate.

[0015] 2. The present invention drives the planet carrier to rotate by performing a series of transmissions on the rotation of the moving wheel, so that the resistance encountered by the moving wheel during rotation is not only the friction between the brake disc and the brake pad, thereby improving the braking effect of the aircraft.

[0016] 3. The present invention provides a Tesla valve on the first pipeline, thereby increasing the resistance of the fluorinated liquid in the box body flowing into the hollow ring through the first pipeline, and the resistance of the fluorinated liquid flowing through the first pipeline can be adjusted by changing the number of diversions in the Tesla valve. The power of the fluorinated liquid flow comes from the rotation of the planetary carrier, and the rotation power of the planetary carrier comes from the rotation of the moving wheel. When the Tesla valve is provided on the first pipeline to increase the flow resistance of the fluorinated liquid, the resistance to the rotation of the annular impeller will also increase, which will eventually cause the resistance to the rotation of the moving wheel to increase again. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The overall structure of the present invention is shown in FIG. Figure 1 ;

[0018] Figure 2 The overall structure of the present invention is shown in FIG. Figure 2 ;

[0019] Figure 3 It is a structural schematic diagram of the brake disc of the present invention;

[0020] Figure 4 It is a structural schematic diagram of the planet carrier of the present invention;

[0021] Figure 5 It is a structural schematic diagram of the cylinder of the present invention;

[0022] Figure 6 It is a structural schematic diagram of the annular impeller of the present invention;

[0023] Figure 7 It is a structural schematic diagram of the Tesla valve of the present invention.

[0024] In the figure: 1. landing gear; 11. oil pipe; 12. pressure valve; 2. vertical rod; 21. horizontal rod; 22. planetary carrier; 23. planetary gear; 24. sun gear; 25. mounting cylinder; 26. cylinder; 27. swivel; 28. spring; 29. ​​plug rod; 3. moving wheel; 31. piston cylinder; 32. piston rod; 33. brake pad; 34. brake disc; 35. slot; 4. gear ring; 41. fan plate; 42. annular impeller; 43. hollow ring; 44. first pipeline; 45. second pipeline; 46. third pipeline; 47. Tesla valve; 48. fixing frame; 5. box body. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. 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.

[0026] Embodiment 1

[0027] Reference Figure 1-Figure 3 The present invention provides a technical solution: an aircraft caster with a MoS high temperature resistant coating, comprising a landing gear 1 and a moving wheel 3 coated with a MoS layer, wherein a vertical rod 2 is slidably connected inside the landing gear 1, a cross rod 21 is fixedly connected to the bottom of the vertical rod 2, the moving wheel 3 is rotatably connected to the cross rod 21, a brake disc 34 is fixedly connected to the moving wheel 3, a fixing frame 48 is fixedly connected to the vertical rod 2 and the cross rod 21, a gear ring 4 is fixedly connected to the fixing frame 48, and a sector plate is fixedly connected to the gear ring 4 41, a piston cylinder 31 is fixedly connected to the sector plate 41, a piston rod 32 is slidably connected in the piston cylinder 31, a brake pad 33 is fixedly connected to the end of the piston rod 32 away from the piston cylinder 31, the brake pad 33 is intermittently slidably connected to the brake disc 34, a cavity is opened between the vertical rod 2 and the horizontal rod 21 and the cavity is filled with hydraulic oil, an oil pipe 11 is fixedly connected to the piston cylinder 31 and is connected to the cavity between the vertical rod 2 and the horizontal rod 21 through the oil pipe 11, and a pressure valve 12 is provided on the oil pipe 11.

[0028] During the landing of the aircraft, since the aircraft contacts the ground through the moving wheels 3, and the moving wheels 3 are rotatably connected to the crossbar 21, and the crossbar 21 is fixedly connected to the vertical rod 2, the instantaneous impact force of the aircraft landing can cause the hydraulic oil between the landing gear 1 and the vertical rod 2 to be subjected to a very large pressure and then break through the pressure setting value of the pressure valve 12. At this time, the landing gear 1 and the vertical rod 2 will slide relative to each other. When the hydraulic oil between the landing gear 1 and the vertical rod 2 flows into the piston cylinder 31 through the oil pipe 11, the piston in the piston cylinder 31 The rod 32 will be pushed by the hydraulic rod and move towards the brake disc 34, and then the brake pad 33 fixedly connected to the piston rod 32 will be able to contact the brake disc 34. Since the piston cylinder 31 is fixedly connected to the gear ring 4 through the fan plate 41, and the gear ring 4 is fixedly connected to the vertical rod 2 and the cross bar 21 through the fixing frame 48, and the brake disc 34 is fixedly connected to the moving wheel 3, and the moving wheel 3 is rotatably connected to the cross bar 21, the brake pad 33 can slide relative to the brake disc 34 at this time, thereby assisting the aircraft to slow down.

[0029] Embodiment 2

[0030] Reference Figure 1-Figure 5On the basis of the first embodiment, further, a sun gear 24 is rotatably connected to the cross bar 21, and a mounting cylinder 25 is coaxially fixedly connected to one end surface of the sun gear 24 close to the brake disc 34. The inner diameter of the mounting cylinder 25 is slightly larger than the outer diameter of the cross bar 21. A cylinder 26 is slidably connected to the mounting cylinder 25 through a keyway, and a swivel 27 is rotatably connected to the cylinder 26, and the swivel 27 is fixedly connected to the piston rod 32.

[0031] When the piston rod 32 moves in the direction of the brake disc 34, the swivel 27 fixedly connected to the piston rod 32 synchronously approaches the brake disc 34. Since the cylinder 26 is connected to the swivel 27 for limited rotation, the swivel 27 can drive the cylinder 26 to synchronously approach the position of the brake disc 34 until the end surface of the cylinder 26 close to the brake disc 34 is in contact with the brake disc 34. When the cylinder 26 is in contact with the brake disc 34, the insertion rod 29 on the cylinder 26 can be inserted into the slot 35 on the brake disc 34. Due to the setting of the spring 28 between the insertion rod 29 and the cylinder 26, when the insertion rod 29 is in contact with the brake disc 34 but not inserted into the slot 35 on the brake disc 34, the spring 28 will be compressed. Since the brake disc 34 rotates with the moving wheel 3, the slot 35 on the rotating brake disc 34 can eventually move to a position suitable for the insertion of the insertion rod 29, and then the insertion rod 29 can be inserted into the slot 35 under the action of the spring 28.

[0032] A plug rod 29 is slidably connected to the side wall of the cylinder 26, and a spring 28 is fixedly connected between the plug rod 29 and the cylinder 26. A slot 35 that cooperates with the plug rod 29 is opened on the brake disc 34. The number of the plug rods 29 is specifically five, and the five plug rods 29 are evenly distributed on the cylinder 26 in a circle. The planet carrier 22 is rotatably connected to the cross bar 21, and the planet gear 23 is rotatably connected to the planet carrier 22. The sun gear 24 and the ring gear 4 are both engaged with the planet gear 23.

[0033] When the insertion rod 29 is inserted into the slot 35, the rotation of the brake disc 34 can drive the cylinder 26 to rotate through the insertion rod 29, and the cylinder 26 is slidably connected to the mounting cylinder 25 through the keyway, so that the cylinder 26 can slide relative to the mounting cylinder 25, but the rotating cylinder 26 can drive the mounting cylinder 25 to rotate synchronously, and then the sun gear 24 fixedly connected to the mounting cylinder 25 can rotate. When the sun gear 24 rotates, the planetary gear 23 meshing with the sun gear 24 is driven to rotate, and the planetary gear 23 is meshed with the gear ring 4, and then the planetary gear 23 can roll in a circle in the gear ring 4, and then the rolling planetary gear 23 can drive the planetary carrier 22 to rotate on the cross bar 21. The planetary carrier 22 is driven to rotate by performing the above-mentioned series of transmissions on the rotation of the moving wheel 3, so that the resistance encountered by the moving wheel 3 when rotating is not only the friction between the brake disc 34 and the brake pad 33, thereby improving the braking effect of the aircraft.

[0034] Embodiment 3

[0035] Reference Figure 1-Figure 7 On the basis of the second embodiment, further, a hollow ring 43 is fixedly connected to the fixing frame 48, an annular impeller 42 is fixedly connected to the planetary frame 22, and the annular impeller 42 is rotatably connected in the hollow ring 43. A box body 5 is fixedly connected to the fixing frame 48, and the box body 5 is filled with fluorinated liquid. A first pipe 44 is fixedly connected to the box body 5, and one end of the first pipe 44 away from the box body 5 is connected to the cavity in the hollow ring 43. A Tesla valve 47 is provided in the middle of the first pipe 44, and the Tesla valve 47 is fixedly connected to the fixing frame 48.

[0036] Since the Tesla valve 47 is provided on the first pipeline 44, the resistance of the fluorinated liquid in the box body 5 flowing into the hollow ring 43 through the first pipeline 44 is increased, and the resistance of the fluorinated liquid flowing through the first pipeline 44 can be adjusted by changing the number of diversions in the Tesla valve 47. The power of the fluorinated liquid flow comes from the rotation of the planetary carrier 22, and the rotation power of the planetary carrier 22 comes from the rotation of the moving wheel 3. When the Tesla valve 47 is provided on the first pipeline 44 to increase the flow resistance of the fluorinated liquid, the resistance to the rotation of the annular impeller 42 will also increase, which will eventually cause the resistance to the rotation of the moving wheel 3 to increase again.

[0037] A cavity is defined in the brake pad 33 , a second pipe 45 is fixedly connected to the hollow ring 43 , an end of the second pipe 45 away from the hollow ring 43 is communicated with the cavity in the brake pad 33 , a third pipe 46 is fixedly connected to the box body 5 , an end of the third pipe 46 away from the box body 5 is communicated with the cavity in the brake pad 33 .

[0038] When the planet carrier 22 rotates, the annular impeller 42 fixedly connected to the planet carrier 22 can rotate synchronously. Since the hollow ring 43 is fixedly connected to the fixed frame 48, the planet carrier 22 can rotate relative to the fixed frame 48, and the annular impeller 42 fixedly connected to the planet carrier 22 can rotate in the cavity inside the hollow ring 43, and the hollow ring 43 is connected to the housing 5 through the first pipe 44, and the negative pressure generated when the annular impeller 42 rotates can adsorb the fluorinated liquid in the housing 5 through the first pipe 44, and the hollow ring 43 is connected to the cavity inside the brake pad 33 through the second pipe 45, and the fluorinated liquid can be transmitted to the cavity of the brake pad 33, and the cavity inside the brake pad 33 is connected to the housing 5 through the third pipe 46, and the flow of the fluorinated liquid can form a cycle, so that when the fluorinated liquid passes through the cavity of the brake pad 33, it can take away part of the heat generated by the friction between the brake pad 33 and the brake disc 34, and thus the thermal attenuation of the brake can be alleviated.

[0039] Working principle: When the aircraft caster with MoS high temperature resistant coating is used, during the take-off process of the aircraft, as the aircraft moves and climbs along the runway, the aircraft only applies its own gravity to the landing gear 1, that is, when the aircraft takes off, due to the setting of the pressure valve 12, the landing gear 1 only bears the aircraft's own gravity, and the hydraulic oil between the landing gear 1 and the vertical rod 2 will not exceed the pressure setting limit of the pressure valve 12 and flow out, and thus no relative sliding occurs between the landing gear 1 and the vertical rod 2;

[0040] During the landing of the aircraft, since the aircraft contacts the ground through the moving wheels 3, and the moving wheels 3 are rotatably connected to the crossbar 21, and the crossbar 21 is fixedly connected to the vertical rod 2, the instantaneous impact force of the aircraft landing can cause the hydraulic oil between the landing gear 1 and the vertical rod 2 to be subjected to a very large pressure and then break through the pressure setting value of the pressure valve 12. At this time, the landing gear 1 and the vertical rod 2 will slide relative to each other. When the hydraulic oil between the landing gear 1 and the vertical rod 2 flows into the piston cylinder 31 through the oil pipe 11, the piston in the piston cylinder 31 The rod 32 will be pushed by the hydraulic rod and move toward the brake disc 34, so that the brake pad 33 fixedly connected to the piston rod 32 can contact the brake disc 34. Since the piston cylinder 31 is fixedly connected to the gear ring 4 through the fan plate 41, and the gear ring 4 is fixedly connected to the vertical rod 2 and the cross bar 21 through the fixing frame 48, and the brake disc 34 is fixedly connected to the moving wheel 3, and the moving wheel 3 is rotatably connected to the cross bar 21, the brake pad 33 can slide relative to the brake disc 34 at this time, thereby assisting the aircraft to decelerate;

[0041] When the piston rod 32 moves in the direction of the brake disc 34, the swivel 27 fixedly connected to the piston rod 32 synchronously approaches the brake disc 34. Since the cylinder 26 is connected to the swivel 27 in a limited rotational connection, the swivel 27 can drive the cylinder 26 to synchronously approach the position of the brake disc 34 until the end surface of the cylinder 26 close to the brake disc 34 fits with the brake disc 34. When the cylinder 26 fits with the brake disc 34, the insertion rod 29 on the cylinder 26 can be inserted into the slot 35 on the brake disc 34. Due to the arrangement of the spring 28 between the insertion rod 29 and the cylinder 26, when the insertion rod 29 contacts the brake disc 34 but is not inserted into the slot 35 on the brake disc 34, the spring 28 will be compressed. Since the brake disc 34 rotates with the moving wheel 3, the slot 35 on the rotating brake disc 34 can eventually move to a position suitable for the insertion of the insertion rod 29, and then the insertion rod 29 can be inserted into the slot 35 under the action of the spring 28.

[0042] When the insertion rod 29 is inserted into the slot 35, the rotation of the brake disc 34 can drive the cylinder 26 to rotate through the insertion rod 29, and the cylinder 26 is slidably connected to the mounting cylinder 25 through the keyway, so that the cylinder 26 can slide relative to the mounting cylinder 25, but the rotating cylinder 26 can drive the mounting cylinder 25 to rotate synchronously, so that the sun gear 24 fixedly connected to the mounting cylinder 25 can rotate. When the sun gear 24 rotates, the planetary gear 23 meshing with the sun gear 24 is driven to rotate, and the planetary gear 23 is meshed with the gear ring 4, so that the planetary gear 23 can roll in a circle in the gear ring 4, and then the rolling planetary gear 23 can drive the planetary carrier 22 to rotate on the cross bar 21. By performing the above series of transmissions on the rotation of the moving wheel 3, the planetary carrier 22 is driven to rotate, so that the resistance encountered by the moving wheel 3 when rotating is not only the friction between the brake disc 34 and the brake pad 33, thereby improving the braking effect of the aircraft;

[0043] When the planet carrier 22 rotates, the annular impeller 42 fixedly connected to the planet carrier 22 can rotate synchronously. Since the hollow ring 43 is fixedly connected to the fixing frame 48, the planet carrier 22 can rotate relative to the fixing frame 48, and the annular impeller 42 fixedly connected to the planet carrier 22 can rotate in the cavity inside the hollow ring 43. The hollow ring 43 is connected to the housing 5 through the first pipe 44. The negative pressure generated when the annular impeller 42 rotates can absorb the fluorinated liquid in the housing 5 through the first pipe 44, and the hollow ring 43 is connected to the brake pad 33 through the second pipe 45. The cavity of the brake pad 33 is connected, and the fluorinated liquid can be transferred to the cavity of the brake pad 33, and the cavity in the brake pad 33 is connected to the box 5 through the third pipe 46, so that the flow of the fluorinated liquid can form a cycle, so that when the fluorinated liquid passes through the cavity of the brake pad 33, a part of the heat generated by the friction between the brake pad 33 and the brake disc 34 can be taken away, so as to alleviate the thermal decay of the brake. At the same time, the fluorinated liquid is not directly sprayed between the brake disc 34 and the brake pad 33, so as to ensure that the friction coefficient between the brake disc 34 and the brake pad 33 will not be changed due to the splashing of the liquid;

[0044] Since the Tesla valve 47 is provided on the first pipeline 44, the resistance of the fluorinated liquid in the box body 5 flowing into the hollow ring 43 through the first pipeline 44 is increased, and the resistance of the fluorinated liquid flowing through the first pipeline 44 can be adjusted by changing the number of diversions in the Tesla valve 47. The power of the fluorinated liquid flow comes from the rotation of the planetary carrier 22, and the rotation power of the planetary carrier 22 comes from the rotation of the moving wheel 3. When the Tesla valve 47 is provided on the first pipeline 44 to increase the flow resistance of the fluorinated liquid, the resistance to the rotation of the annular impeller 42 will also increase, which will eventually cause the resistance to the rotation of the moving wheel 3 to increase again.

[0045] In the above description, the power for the flow of the fluorinated liquid comes from the rotation of the planetary carrier 22. Those skilled in the art can appropriately replace the annular impeller 42 (such as using the rotational force of the planetary carrier 22 to drive a screw pump or a gear pump to pump the fluorinated liquid) to ensure that the power for the flow of the fluorinated liquid comes from the rotation of the planetary carrier 22. As for the fluorinated liquid in the box body 5, it can also be appropriately replaced as long as it is a dangerous solution that can transfer heat and is not flammable, explosive, or the like.

[0046] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft caster with a MoS high temperature resistant coating, comprising a landing gear (1) and a moving wheel (3) coated with a MoS layer, characterized in that: A vertical rod (2) is slidably connected to the landing gear (1), a cross rod (21) is fixedly connected to the bottom of the vertical rod (2), the moving wheel (3) is rotatably connected to the cross rod (21), a brake disc (34) is fixedly connected to the moving wheel (3), a fixing frame (48) is fixedly connected to the vertical rod (2) and the cross rod (21), a gear ring (4) is fixedly connected to the fixing frame (48), a sector plate (41) is fixedly connected to the sector plate (41), a piston cylinder (31) is fixedly connected to the sector plate (41), and the movable wheel (3) is fixedly connected to the cross rod (21). A piston rod (32) is slidably connected inside the piston cylinder (31); a brake pad (33) is fixedly connected to one end of the piston rod (32) away from the piston cylinder (31); the brake pad (33) is intermittently slidably connected to a brake disc (34); a cavity is provided between the vertical rod (2) and the horizontal rod (21) and is filled with hydraulic oil; an oil pipe (11) is fixedly connected to the piston cylinder (31) and is in communication with the cavity between the vertical rod (2) and the horizontal rod (21) through the oil pipe (11); a pressure valve (12) is provided on the oil pipe (11); The cross bar (21) is rotatably connected to a sun gear (24); a mounting cylinder (25) is coaxially fixedly connected to an end surface of the sun gear (24) close to the brake disc (34); the inner diameter of the mounting cylinder (25) is slightly larger than the outer diameter of the cross bar (21); a cylinder (26) is slidably connected to the mounting cylinder (25) via a keyway; a swivel (27) is rotatably connected to the cylinder (26); and the swivel (27) is fixedly connected to the piston rod (32). A plug rod (29) is slidably connected to the side wall of the cylinder (26), a spring (28) is fixedly connected between the plug rod (29) and the cylinder (26), a slot (35) cooperating with the plug rod (29) is provided on the brake disc (34), the number of the plug rods (29) is specifically five, and the five plug rods (29) are evenly distributed on the cylinder (26) in a circumferential manner, The crossbar (21) is rotatably connected to a planet carrier (22), the planet carrier (22) is rotatably connected to a planet gear (23), and both the sun gear (24) and the gear ring (4) are meshed with the planet gear (23).

2. The aircraft caster with MoS high temperature resistant coating according to claim 1, characterized in that: A hollow ring (43) is fixedly connected to the fixed frame (48), an annular impeller (42) is fixedly connected to the planetary frame (22), and the annular impeller (42) is rotatably connected in the hollow ring (43).

3. The aircraft caster with MoS high temperature resistant coating according to claim 2, characterized in that: The fixing frame (48) is fixedly connected to a box body (5), the box body (5) is filled with fluorinated liquid, the box body (5) is fixedly connected to a first pipe (44), an end of the first pipe (44) away from the box body (5) is connected to the cavity in the hollow ring (43), a Tesla valve (47) is provided in the middle of the first pipe (44), and the Tesla valve (47) is fixedly connected to the fixing frame (48).

4. The aircraft caster with MoS high temperature resistant coating according to claim 3, characterized in that: The brake pad (33) has a cavity therein, the hollow ring (43) is fixedly connected to a second pipe (45), and an end of the second pipe (45) away from the hollow ring (43) is in communication with the cavity in the brake pad (33).

5. The aircraft caster with MoS high temperature resistant coating according to claim 4, characterized in that: A third pipe (46) is fixedly connected to the box body (5), and an end of the third pipe (46) away from the box body (5) is in communication with the cavity in the brake pad (33).

Images