A landing gear and damper for an eVTOL aircraft

Abstract

This application relates to the field of aircraft technology, specifically an eVTOL aircraft landing gear and damper. The landing gear includes a moving rod and a mounting bracket, and the damper is disposed between the moving rod and the mounting bracket. The damper includes: a main body assembly, including a housing, a receiving cavity disposed on the inner wall of the housing, a fixing ring disposed on the inner wall of the receiving cavity, and a transmission component disposed inside the fixing ring; an adjustment assembly disposed on the outer wall of the housing, including an adjustment tank, a movable block disposed on the inner wall of the adjustment tank, the movable block moving on the inner wall of the adjustment tank under the influence of the transmission component; the movement of the transmission component is triggered by the rising speed of the movable sleeve, which drives the output gear through the push gear, and adjusts the position of the first valve plate in a linkage manner to realize dynamic adjustment of the damping force. When the impact force of the aircraft landing is small, the movable sleeve can buffer with a long stroke; when the impact force is large, the stroke is shortened to avoid the bottom of the aircraft hitting the ground and improve the buffer adaptability.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an eVTOL aircraft landing gear and damper. Background Technology

[0002] There are many problems with the dampers used in the landing gear of current eVTOL aircraft. Traditional passive dampers have fixed damping characteristics and cannot be adjusted in real time according to the actual flight and landing conditions of the aircraft. This results in the dampers either failing to provide sufficient buffering force under different landing speeds and ground conditions, causing the aircraft to experience excessive impact force upon landing, which not only affects the passenger experience but may also damage the aircraft structure; or the damping force is too large, causing the landing gear to rebound slowly, affecting the aircraft's taxiing stability.

[0003] While some existing semi-active dampers can adjust the damping force to a certain extent, their response speed is limited. When faced with complex and ever-changing flight environments, such as sudden strong airflow or unstable landing sites, they cannot make rapid and accurate adjustments, making it difficult to meet the stringent safety and comfort requirements of eVTOL aircraft.

[0004] Chinese Patent Publication No. CN107054630A discloses an aircraft landing gear including a primary damper and a secondary damper, comprising: an axle; a strut extending along the axis Z of a primary strut, the strut having a first portion a and a second portion b supporting the axle; a primary damper designed to dampen axial movement of the first strut portion a relative to the second strut portion b; and a first damper a, different from the primary damper, designed to dampen angular oscillation about the axis Z of the primary strut. The first damper a is supported by the first strut portion a and includes: an inertial mass member M; and a connecting device a connecting the inertial mass member M to the first strut portion a, the device being designed to dampen rotational movement of the inertial mass member M about the axis Z. This structure improves damping against shimmy without requiring modifications to any landing gear components.

[0005] However, this technical solution still has some technical problems: the damper cannot adjust its travel distance according to the different impact forces when the aircraft lands. Summary of the Invention

[0006] In view of the problems existing in the prior art, this application is hereby filed.

[0007] To solve the above-mentioned technical problems, this application provides the following technical solution: a landing gear for an eVTOL aircraft, comprising a landing gear, a support column fixed to the end of the landing gear and a moving rod hinged to the end of the support column, an electric push cylinder also provided at the end of the landing gear and the end of the electric push cylinder connected to the outer wall of the moving rod, a hinge rod hinged to the end of the moving rod and a mounting frame provided at the other end of the hinge rod, and a wheel also provided on the outer wall of the mounting frame;

[0008] The landing gear is fixed inside the fuselage. An electric push cylinder at the end of the landing gear pulls a moving rod to move at the end of the fuselage, thereby completing the storage of the bottom mounting frame and wheels.

[0009] A damper, the damper being applied to the landing gear of the eVTOL aircraft described above, includes: a main body assembly including a housing, a receiving cavity disposed on the inner wall of the housing, a fixing ring disposed on the inner wall of the receiving cavity, and a transmission component disposed inside the fixing ring;

[0010] The transmission component is affected by the movable sleeve located on the inner wall of the accommodating cavity. When the movable sleeve moves on the inner wall of the accommodating cavity, it drives the transmission component to move.

[0011] An adjustment assembly located on the outer wall of the housing includes an adjustment tank and a movable block located on the inner wall of the adjustment tank. The movable block moves on the inner wall of the adjustment tank under the influence of a transmission component. When the movable block moves, it adjusts the position of the first valve plate inside the adjustment accommodating cavity to adjust the resistance encountered by the movable sleeve during its movement.

[0012] As a preferred embodiment of the damper described in this application, the transmission component includes a drive gear, which is installed inside the movable cavity opened in the inner wall of the fixed ring. The fixed ring is fixed to the inner wall of the accommodating cavity to separate the internal space. At the same time, an opening is provided through the end of the fixed ring for the medium to flow inside the accommodating cavity.

[0013] As a preferred embodiment of the damper described in this application, the movable cavity is provided with a first flow channel and a second flow channel at its end. The first flow channel and the second flow channel are connected to the movable cavity. When the movable sleeve moves upward inside the accommodating cavity, the pushing medium enters the movable cavity from the first flow channel and flows out from the second flow channel. At this time, the pushing gear located inside the movable cavity is driven by the medium to rotate.

[0014] As a preferred embodiment of the damper described in this application, a transmission rod is provided at the center of the drive gear shaft and the end of the transmission rod extends into the interior of the regulating tank. The end of the transmission rod is located on the inner wall of the movable block and an output gear is also provided on the outer wall of the transmission rod. A limit shaft is provided on the outer wall of the output gear and the limit shaft is installed on the inner wall of the regulating tank. A connecting cavity is also provided on the inner wall of the output gear and the end of the transmission rod extends into the inner wall of the connecting cavity.

[0015] As a preferred embodiment of the damper described in this application, the transmission rod end is provided with a turntable and the outer wall of the turntable is provided with a rotating rod, the outer wall of the rotating rod is provided with a protrusion, the outer wall of the protrusion is provided with a third elastic element and the other end of the third elastic element is fixed to the outer wall of the turntable and used to pull the rotating rod.

[0016] As a preferred embodiment of the damper described in this application, the movable block is provided with a rack on its inner wall and the rack meshes with the output gear. The output gear drives the movable block to move on the inner wall of the regulating tank. The end of the movable block is also provided with a fourth elastic element and the fourth elastic element moves in the placement cavity of the inner wall of the regulating tank. The end of the movable block is provided with a first leakage hole and a second leakage hole is provided at the end opposite to the fourth elastic element. The end face of the movable block is also connected to a support rod and the end of the support rod is connected to a second valve plate.

[0017] As a preferred embodiment of the damper described in this application, the outer wall of the regulating tank is provided with a first connecting channel and a second connecting channel, the inner wall of the second connecting channel is also provided with a third connecting channel, the end of the second valve plate is provided with a second air chamber and the end of the second air chamber is provided with a connecting pipe, and the other end of the connecting pipe is connected to the first air chamber located at the end of the first valve plate.

[0018] As a preferred embodiment of the damper described in this application, the inner wall of the movable sleeve is provided with a connecting rod and the end of the connecting rod is provided with a piston, the outer wall of the connecting rod is sleeved with a first elastic element, and the end of the piston is also provided with a second elastic element.

[0019] As a preferred embodiment of the damper described in this application, the outer wall of the housing is further provided with a collar and an electric pusher cylinder is provided on the outer wall of the collar. A push rod is provided at the shaft center of the electric pusher cylinder, and a connecting rod is provided at the other end of the push rod. A first hinge plate is hinged to the end of the connecting rod, and a second hinge plate is hinged to the other end of the first hinge plate.

[0020] The beneficial effects of this application are as follows: This application uses an electric push cylinder at the end of the landing gear to pull the moving stick, which can conveniently complete the storage and landing of the bottom mounting frame and the wheels. When the aircraft is in flight, the wheels can be quickly retracted into the fuselage to reduce flight drag and improve flight efficiency. When landing, the wheels can quickly touch the ground to ensure landing safety. The operation is simple and efficient. Furthermore, a damper is installed between the mounting frame and the moving stick. When the aircraft lands, the damper can effectively buffer the impact force during landing and reduce the vibration of the fuselage.

[0021] The upward speed of the damper's movable sleeve triggers the movement of the transmission components, which in turn drives the output gear to adjust the position of the first valve plate, thereby achieving dynamic adjustment of the damping force. When the impact force of the aircraft landing is small, the movable sleeve can provide long-stroke buffering; when the impact force is large, the movement stroke is shortened to prevent the bottom of the aircraft from hitting the ground and improve the buffering adaptability.

[0022] The first and second elastic elements located inside the movable sleeve provide basic shock absorption and buffering; the electric propulsion cylinder, together with the connecting rod, the first hinge plate and the second hinge plate, form a multi-angle adjustment structure to absorb and disperse impact forces and help maintain the balance and stability of the aircraft's structural attitude. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the overall structure of the landing gear and damper of an eVTOL aircraft according to this application;

[0025] Figure 2 This is a schematic diagram of the overall structure of the damper in this application;

[0026] Figure 3 This is a side sectional view of the main component in this application;

[0027] Figure 4 This is a side sectional view of the outer casing in this application;

[0028] Figure 5 for Figure 4 Enlarged schematic diagram of the structure at point A in the middle;

[0029] Figure 6 This is a schematic diagram of the adjustment component structure in this application;

[0030] Figure 7 This is a side sectional view of the regulating tank in this application;

[0031] Figure 8 This is a schematic diagram of the structure of the active block in this application;

[0032] Figure 9 This is a side sectional view of the output gear in this application.

[0033] Explanation of reference numerals in the attached drawings: 100, main component; 101, outer shell; 1011, accommodating cavity; 1012, retaining ring; 1013, opening; 1014, first flow channel; 1015, movable cavity; 1016, second flow channel; 1017, moving cavity; 1018, first valve plate; 1019, first air chamber; 102, movable sleeve; 1021, connecting rod; 1022, piston; 1023, first elastic element; 1024, second elastic element; 103, pushing gear; 1031, transmission rod; 1032, turntable; 1033, rotating rod; 1034, protrusion; 1035, third elastic element;

[0034] 200. Adjusting assembly; 201. Adjusting tank; 202. Fixed shell; 203. Placement cavity; 2031. Fourth elastic element; 204. Movable block; 2041. First leakage hole; 2042. Rack; 2043. Second leakage hole; 205. Support rod; 2051. Second valve plate; 206. First connecting channel; 2061. Second connecting channel; 2062. Third connecting channel; 207. Output gear; 2071. Connecting cavity; 2072. Limiting shaft; 208. Second air chamber; 2081. Connecting pipe;

[0035] 301. Collar; 302. Electric push cylinder; 3021. Push rod; 3022. Connecting rod; 303. First hinge plate; 304. Second hinge plate;

[0036] 401. Landing gear; 402. Support column; 403. Moving rod; 404. Electric push cylinder; 405. Articulated rod; 406. Mounting bracket; 407. Wheel. Detailed Implementation

[0037] To make the above-mentioned objectives, features and advantages of this application more apparent and understandable, the specific embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0038] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0039] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of this application. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that excludes other embodiments.

[0040] Example 1

[0041] This is the first embodiment of the present application, which provides an eVTOL aircraft landing gear.

[0042] Specifically, the landing gear 401 has a support column 402 fixed at one end and a moving rod 403 hinged to the end of the support column 402. The landing gear 401 is also equipped with an electric push cylinder 404, and the end of the electric push cylinder 404 is connected to the outer wall of the moving rod 403. The end of the moving rod 403 is hinged with a hinge rod 405, and the other end of the hinge rod 405 is equipped with a mounting bracket 406. The outer wall of the mounting bracket 406 is also equipped with a wheel 407.

[0043] The landing gear 401 is fixed inside the fuselage. The electric push cylinder 404 at the end of the landing gear 401 pulls the moving rod 403 to move at the end of the fuselage. The electric push cylinder 404 pulls the moving rod 403 to complete the storage of the bottom mounting bracket 406 and the wheels 407.

[0044] The landing gear 401 is installed inside the fuselage of the aircraft. One end of the motion stick 403 is hinged to the support column 402, and the upper surface of the other end is hinged to the electric push cylinder 404. When pulled by the electric push cylinder 404, the end of the motion stick 403 that is hinged to the electric push cylinder 404 is raised, and the mounting frame 406 and the wheels 407 below are retracted into the fuselage. When the aircraft lands, the mounting frame 406 and the wheels 407 are lowered by the electric push cylinder 404, so that the wheels 407 touch the ground to complete the landing. At the same time, the damper between the mounting frame 406 and the motion stick 403 provides cushioning.

[0045] Example 2

[0046] This is a second embodiment of the present application, which provides a damper.

[0047] Specifically, refer to Figures 1 to 5 The main component 100 includes a housing 101, a receiving cavity 1011 disposed on the inner wall of the housing 101, a fixing ring 1012 disposed on the inner wall of the receiving cavity 1011, and a transmission component disposed inside the fixing ring 1012.

[0048] The transmission component is affected by the movable sleeve 102 located on the inner wall of the accommodating cavity 1011. When the movable sleeve 102 moves on the inner wall of the accommodating cavity 1011, it drives the transmission component to move.

[0049] The adjustment assembly 200, located on the outer wall of the housing 101, includes an adjustment tank 201 and a movable block 204 located on the inner wall of the adjustment tank 201. The movable block 204 moves on the inner wall of the adjustment tank 201 under the influence of the transmission component. When the movable block 204 moves, it adjusts the position of the first valve plate 1018 inside the adjustment accommodating cavity 1011 to adjust the resistance encountered by the movable sleeve 102 when it moves.

[0050] The fixed ring 1012 is fixed inside the accommodating cavity 1011, and the interior of the accommodating cavity 1011 is separated by the fixed ring 1012. The transmission component is installed inside the fixed ring 1012. When the movable sleeve 102 moves upward inside the outer shell 101, the movable sleeve 102 drives the medium to move upward inside the accommodating cavity 1011. When the medium passes through the fixed ring 1012, it drives the transmission component inside the fixed ring 1012 to move.

[0051] The regulating tank 201 is fixed to the outside of the outer shell 101 by the fixed shell 202. The movable block 204 inside is affected by the transmission component and moves inside the regulating tank 201. When the movable block 204 moves inside the regulating tank 201, the first valve plate 1018 inside the accommodating cavity 1011 moves downward synchronously and approaches the fixed ring 1012. The space between the first valve plate 1018 and the fixed ring 1012 becomes smaller, and the medium passing through the fixed ring 1012 becomes less, which increases the resistance of the movable sleeve 102 when it moves inside the outer shell 101 and reduces the distance the movable sleeve 102 moves.

[0052] When the impact force of the aircraft landing is small, the movable sleeve 102 moves and rises slowly inside the outer shell 101, allowing it to travel a larger distance to buffer the impact. When the impact force of the landing is large, the movable sleeve 102 will rise rapidly inside the outer shell 101. In this case, it is necessary to control the upward travel of the movable sleeve 102 inside the outer shell 101 to avoid the bottom of the aircraft contacting the ground due to the large impact force and the excessive travel in order to buffer the impact.

[0053] Example 3

[0054] This is the third embodiment of the present application, which is implemented based on the previous embodiment.

[0055] Specifically, refer to Figures 2-5 The transmission component includes a drive gear 103, which is installed inside the movable cavity 1015 opened in the inner wall of the fixed ring 1012. The fixed ring 1012 is fixed to the inner wall of the accommodating cavity 1011 to separate the internal space. At the same time, an opening 1013 is opened through the end of the fixed ring 1012 for the medium to flow inside the accommodating cavity 1011.

[0056] The openings 1013 array has multiple holes penetrating the surface of the fixed ring 1012, connecting the receiving cavity 1011 to the moving cavity 1017 above the fixed ring 1012. When the movable sleeve 102 moves upward inside the outer shell 101, the movable sleeve 102 pushes the medium upward, and the medium enters the moving cavity 1017 from the receiving cavity 1011 through the openings 1013. Figure 3 , Figure 5 As shown, the first valve plate 1018 is located above the moving chamber 1017. Therefore, when the medium enters the interior of the moving chamber 1017, the first valve plate 1018 moves upward as the medium increases. At this time, the movable sleeve 102 can rise a greater distance inside the outer shell 101, and the overall system has a better buffering effect.

[0057] Preferred, refer to Figures 3-5 The movable cavity 1015 has a first flow channel 1014 and a second flow channel 1016 respectively at its end. The first flow channel 1014 and the second flow channel 1016 are connected to the movable cavity 1015. When the movable sleeve 102 moves upward inside the accommodating cavity 1011, the pushing medium enters the movable cavity 1015 from the first flow channel 1014 and flows out from the second flow channel 1016. At this time, the pushing gear 103 located inside the movable cavity 1015 is driven by the medium to rotate.

[0058] Among them, such as Figure 4 As shown, the first flow channel 1014 is inclined inside the fixed ring 1012, so that when the medium moves upward, it moves obliquely upward through the first flow channel 1014, which can drive the push gear 103 located inside the active cavity 1015 to rotate, and flow out from the second flow channel 1016 above, and enter the active cavity 1017, which cooperates with the opening 1013 to allow the medium to pass through.

[0059] When the movable sleeve 102 rises at a relatively slow speed, the medium normally passes through the opening 1013 and the movable cavity 1015 into the moving cavity 1017. When the movable sleeve 102 rises at a relatively fast speed, since the opening 1013 and the movable cavity 1015 are of a fixed size, the medium passes through at a faster speed, which drives the push gear 103 to rotate rapidly inside the movable cavity 1015.

[0060] Reference Figures 6 to 8 A transmission rod 1031 is provided at the shaft of the drive gear 103, and the end of the transmission rod 1031 extends into the interior of the regulating tank 201. The end of the transmission rod 1031 is located on the inner wall of the movable block 204, and an output gear 207 is also provided on the outer wall of the transmission rod 1031.

[0061] The transmission rod 1031 rotates synchronously with the push gear 103. At the same time, the top of the transmission rod 1031 is movably connected to the output gear 207 inside the regulating tank 201. When the transmission rod 1031 rotates rapidly with the push gear 103, it drives the output gear 207 to rotate inside the regulating tank 201. When the push gear 103 rotates at normal speed, the output gear 207 does not move.

[0062] Reference Figures 8-9 The outer wall of the output gear 207 is provided with a limiting shaft 2072 and the limiting shaft 2072 is installed on the inner wall of the regulating tank 201. The inner wall of the output gear 207 is also provided with a connecting cavity 2071 and the end of the transmission rod 1031 extends to the inner wall of the connecting cavity 2071.

[0063] The output gear 207 is fixed to the inner wall of the regulating tank 201 by the limiting shaft 2072, while the top end of the transmission rod 1031 extends into the connecting cavity 2071 opened on the surface of the output gear 207.

[0064] A turntable 1032 is provided at the end of the transmission rod 1031, and a rotating rod 1033 is provided on the outer wall of the turntable 1032. A protrusion 1034 is provided on the outer wall of the rotating rod 1033, and a third elastic element 1035 is provided on the outer wall of the protrusion 1034. The other end of the third elastic element 1035 is fixed to the outer wall of the turntable 1032 and is used to pull the rotating rod 1033.

[0065] Among them, such as Figure 9 As shown, the surface of the turntable 1032 is arrayed with rotating rods 1033. The rotating rods 1033 are pulled by the third elastic element 1035. In the initial state, they are pulled inward by the third elastic element 1035. When the drive gear 103 is pushed by the normal flow of the medium, the centrifugal force generated by the rotation of the rotating rods 1033 cannot make the rotating rods 1033 open outward. When the speed of the medium flow increases, the rotation speed of the rotating rods 1033 increases, and the centrifugal force generated increases, causing the rotating rods 1033 to open outward and stick to the inner wall of the connecting cavity 2071, driving the output gear 207 to rotate synchronously.

[0066] Reference Figures 6 to 8 The inner wall of the movable block 204 is provided with a rack 2042, which meshes with the output gear 207. The output gear 207 drives the movable block 204 to move on the inner wall of the regulating tank 201. The end of the movable block 204 is also provided with a fourth elastic element 2031, which moves in the placement cavity 203 on the inner wall of the regulating tank 201. The end of the movable block 204 is provided with a first leakage hole 2041, and the end opposite to the fourth elastic element 2031 is also provided with a second leakage hole 2043. The end face of the movable block 204 is also connected to a support rod 205, and the end of the support rod 205 is connected to a second valve plate 2051.

[0067] The movable block 204 is fitted on the outer wall of the output gear 207, and the rack 2042 on the inner wall meshes with the output gear 207. The output gear 207 drives the movable block 204 to move upward inside the regulating tank 201.

[0068] The bottom of the movable block 204 is provided with a fourth elastic element 2031. The fourth elastic element 2031 pushes the movable block 204 to maintain a certain height inside the regulating tank 201. At the same time, when the movable block 204 moves downward, the deformation of the fourth elastic element 2031 provides buffering and finally resets the movable block 204.

[0069] The interior of the placement cavity 203 is also filled with medium. When the movable block 204 moves inside, the medium flows through the first leakage hole 2041 and the second leakage hole 2043 on the surface of the movable block 204. At the same time, the second valve plate 2051 at the top moves up and down inside the regulating tank 201 along with the movable block 204 via the support rod 205.

[0070] Better, refer to Figure 6 The outer wall of the regulating tank 201 is provided with a first connecting channel 206 and a second connecting channel 2061. The inner wall of the second connecting channel 2061 is also provided with a third connecting channel 2062. The end of the second valve plate 2051 is provided with a second air chamber 208 and the end of the second air chamber 208 is provided with a connecting pipe 2081. The other end of the connecting pipe 2081 is connected to the first air chamber 1019 located at the end of the first valve plate 1018.

[0071] The first connecting channel 206 and the second connecting channel 2061 are both connected to the inner wall of the regulating tank 201. Figure 6 As can be seen, the upper port of the first connecting channel 206 is located above the movable block 204, and the lower port is located at the slotted position on the inner wall of the movable block 204. Similarly, the upper port and lower port of the second connecting channel 2061 are located at the middle of the movable block 204 and the lower end of the placement cavity 203, respectively. The first connecting channel 206 and the second connecting channel 2061 are used to accelerate the flow speed of the medium inside the movable block 204 when it moves up and down inside the regulating tank 201, that is, to accelerate the movement speed of the movable block 204.

[0072] In summary, during use, in the initial state, the movable sleeve 102 rises slowly inside the outer shell 101. When the movable sleeve 102 rises, the pushing medium enters the moving chamber 1017 above the fixed ring 1012 through the opening 1013 and the movable chamber 1015. As the medium increases, it pushes the first valve plate 1018 upward. At this time, the high-pressure gas in the first air chamber 1019 is compressed and enters the interior of the second air chamber 208 through the connecting pipe 2081, thereby pushing the second valve plate 2051 downward. Through the support rod 205, it drives the lower movable block 204 downward and compresses the fourth elastic element 2031. At this time, because the movable sleeve 102 rises slowly, when the pushing medium passes through the movable chamber 1015, the internal pushing gear 103 rotates slowly and cannot drive the output gear 207 to rotate. As the medium flows into the moving chamber 1017, the movable sleeve 102 can move a longer distance inside the outer shell 101.

[0073] When the movable sleeve 102 rises rapidly inside the outer shell 101, the flow rate of the medium increases, causing the drive gear 103 to rotate rapidly inside the fixed ring 1012. At this time, the outward expansion of the rotating rod 1033 drives the output gear 207 to rotate on the inner wall of the movable block 204. Through the cooperation with the rack 2042, the movable block 204 moves upward inside the regulating tank 201. When the movable block 204 moves upward, it drives the second valve plate 2051 to move upward and squeeze the second air chamber 208, making the volume of the first air chamber 1019 larger. The first valve plate 1018 moves downward above the moving chamber 1017 and squeezes the moving chamber 1017 to make its volume smaller, so that it cannot accommodate the medium passing through the receiving chamber 1011. As a result, the movable sleeve 102 moves a shorter stroke inside the outer shell 101.

[0074] Example 4

[0075] This is the fourth embodiment of the present application, which is implemented based on the previous embodiment.

[0076] Specifically, refer to Figures 1-4 The inner wall of the movable sleeve 102 is provided with a connecting rod 1021 and a piston 1022 is provided at the end of the connecting rod 1021. The outer wall of the connecting rod 1021 is provided with a first elastic element 1023, and the end of the piston 1022 is also provided with a second elastic element 1024.

[0077] The connecting rod 1021 is inside the movable sleeve 102, and the piston 1022 at the top is close to the inner wall of the movable sleeve 102. The first elastic element 1023 is sleeved on the outer wall of the connecting rod 1021 and is located below the piston 1022, while the second elastic element 1024 is located above the piston 1022. The first elastic element 1023 and the second elastic element 1024 realize the shock absorption and buffering of the connecting rod 1021.

[0078] Preferably, the outer wall of the outer casing 101 is also provided with a collar 301 and an electric push cylinder 302 is provided on the outer wall of the collar 301. A push rod 3021 is provided at the shaft center of the electric push cylinder 302, and a connecting rod 3022 is provided at the other end of the push rod 3021. A first hinge plate 303 is hinged to the end of the connecting rod 3022, and a second hinge plate 304 is hinged to the other end of the first hinge plate 303.

[0079] Among them, the electric thrust cylinder 302 is symmetrically arranged on both sides of the collar 301. The electric thrust cylinder 302 drives the push rod 3021 to move. The linkage mechanism is formed by the connecting rod 3022, the first hinge plate 303 and the second hinge plate 304. It can realize multi-angle attitude adjustment. In conjunction with the damper, it buffers the complex displacement when the aircraft vibrates, absorbs and disperses the impact force, and helps maintain the balance and stability of the aircraft's structural attitude.

[0080] It should be noted that the above embodiments are only used to illustrate the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of this application without departing from the spirit and scope of the technical solutions of this application, and all such modifications and substitutions should be covered within the scope of the claims of this application.

Claims

1. A landing gear for an eVTOL aircraft, comprising: A landing gear (401) is provided with a support column (402) fixed at one end and a moving rod (403) hinged at the end of the support column (402). An electric push cylinder (404) is also provided at the end of the landing gear (401) and the end of the electric push cylinder (404) is connected to the outer wall of the moving rod (403). A hinge rod (405) is hinged at the end of the moving rod (403) and a mounting bracket (406) is provided at the other end of the hinge rod (405). A wheel (407) is also provided on the outer wall of the mounting bracket (406). The landing gear (401) is fixed inside the fuselage. The electric push cylinder (404) at the end of the landing gear (401) pulls the moving rod (403) to move at the end of the fuselage. The electric push cylinder (404) pulls the moving rod (403) to complete the storage of the bottom mounting bracket (406) and the wheels (407). The feature is that it further includes a damper applied to the landing gear of the eVTOL aircraft, comprising: a main body assembly (100), including a housing (101), a receiving cavity (1011) disposed on the inner wall of the housing (101), a fixing ring (1012) disposed on the inner wall of the receiving cavity (1011), and a transmission component disposed inside the fixing ring (1012); The transmission component is affected by the movable sleeve (102) located on the inner wall of the accommodating cavity (1011). When the movable sleeve (102) moves on the inner wall of the accommodating cavity (1011), it drives the transmission component to move. An adjustment assembly (200) provided on the outer wall of the outer shell (101) includes an adjustment tank (201) and a movable block (204) provided on the inner wall of the adjustment tank (201). The movable block (204) moves on the inner wall of the adjustment tank (201) under the influence of the transmission component. When the movable block (204) moves, it adjusts the position of the first valve plate (1018) inside the adjustment accommodating cavity (1011) to adjust the resistance encountered by the movable sleeve (102) when it moves. The transmission component includes a drive gear (103), a transmission rod (1031) is provided at the shaft of the drive gear (103), and the end of the transmission rod (1031) extends into the interior of the regulating tank (201). The end of the transmission rod (1031) is located on the inner wall of the movable block (204), and an output gear (207) is also provided on the outer wall of the transmission rod (1031). A limit shaft (2072) is provided on the outer wall of the output gear (207), and the limit shaft (2072) is installed on the inner wall of the regulating tank (201). A connecting cavity (2071) is also provided on the inner wall of the output gear (207), and the end of the transmission rod (1031) extends into the inner wall of the connecting cavity (2071). The transmission rod (1031) is provided with a turntable (1032) at its end, and a rotating rod (1033) is provided on the outer wall of the turntable (1032). A protrusion (1034) is provided on the outer wall of the rotating rod (1033), and a third elastic element (1035) is provided on the outer wall of the protrusion (1034). The other end of the third elastic element (1035) is fixed to the outer wall of the turntable (1032) and is used to pull the rotating rod (1033). The inner wall of the movable block (204) is provided with a rack (2042) and the rack (2042) meshes with the output gear (207). The output gear (207) drives the movable block (204) to move on the inner wall of the regulating tank (201). The end of the movable block (204) is also provided with a fourth elastic element (2031) and the fourth elastic element (2031) moves in the placement cavity (203) on the inner wall of the regulating tank (201). The end of the movable block (204) is provided with a first leakage hole (2041) and a second leakage hole (2043) is provided at the end opposite to the fourth elastic element (2031). The end face of the movable block (204) is also connected to a support rod (205) and the end of the support rod (205) is connected to a second valve plate (2051).

2. The landing gear for an eVTOL aircraft as described in claim 1, characterized in that: The drive gear (103) is installed inside the movable cavity (1015) opened in the inner wall of the fixed ring (1012). The fixed ring (1012) is fixed to the inner wall of the accommodating cavity (1011) to separate the internal space. At the same time, an opening (1013) is opened through the end of the fixed ring (1012) for the medium to flow inside the accommodating cavity (1011).

3. The landing gear for an eVTOL aircraft as described in claim 2, characterized in that: The movable cavity (1015) is provided with a first flow channel (1014) and a second flow channel (1016) at its end. The first flow channel (1014) and the second flow channel (1016) are connected to the movable cavity (1015). When the movable sleeve (102) moves upward inside the accommodating cavity (1011), the pushing medium enters the movable cavity (1015) from the first flow channel (1014) and flows out from the second flow channel (1016). At this time, the pushing gear (103) located inside the movable cavity (1015) is driven by the medium to rotate.

4. The landing gear for an eVTOL aircraft as described in claim 3, characterized in that: The regulating tank (201) has a first connecting channel (206) and a second connecting channel (2061) on its outer wall. The second connecting channel (2061) also has a third connecting channel (2062) on its inner wall. The second valve plate (2051) has a second air chamber (208) at its end and a connecting pipe (2081) at its end. The other end of the connecting pipe (2081) is connected to the first air chamber (1019) located at the end of the first valve plate (1018).

5. The landing gear for an eVTOL aircraft as described in claim 4, characterized in that: The inner wall of the movable sleeve (102) is provided with a connecting rod (1021) and the end of the connecting rod (1021) is provided with a piston (1022). The outer wall of the connecting rod (1021) is sleeved with a first elastic element (1023), and the end of the piston (1022) is also provided with a second elastic element (1024).

6. The landing gear for an eVTOL aircraft as described in claim 5, characterized in that: The outer wall of the outer shell (101) is also provided with a collar (301) and an electric push cylinder (302) is provided on the outer wall of the collar (301). A push rod (3021) is provided at the axis of the electric push cylinder (302). A connecting rod (3022) is provided at the other end of the push rod (3021). A first hinge plate (303) is hinged to the end of the connecting rod (3022), and a second hinge plate (304) is hinged to the other end of the first hinge plate (303).

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