A landing gear structure for aircraft with a cushioning function

Abstract

This utility model discloses an aircraft landing gear structure with a buffer function, relating to the field of aircraft landing gear technology. The utility model includes an aircraft body, with brackets fixedly connected to each of the four outer corners of the aircraft body. A shield is fixedly connected to the bottom of each bracket. It also includes a support mechanism located at the bottom of the aircraft body. Specifically, by setting up the support mechanism, when the aircraft body lands, the landing gear contacts the ground through rubber pads at the bottom. These rubber pads provide a certain degree of buffering, and the resulting impact force is further buffered by the cooperation of spring two and damping rod two, absorbing the impact force and significantly reducing rebound, thus maintaining stability during landing. Furthermore, when the landing deviates, the inner rod contacts the ground, allowing the impact force to be absorbed by damping rod one and spring one, satisfying the buffering requirements for different deviations and achieving a more stable landing effect.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft landing gear technology, and in particular relates to an aircraft landing gear structure with a buffer function. Background Technology

[0002] The landing gear of an aircraft is a mechanical device that integrates load-bearing and cushioning. It is mainly used to support the weight of the aircraft during takeoff, landing and ground parking. It is a key interface connecting the aircraft and the ground and must meet the requirements of structural strength to support the aircraft.

[0003] Traditional UAV landing gear is usually fixed to the bottom of the aircraft with multiple screws. This method is not good at cushioning. When the aircraft lands, the landing gear will directly hit the ground, and the impact force will be directly transmitted to the aircraft. The vibration generated by the impact force can easily cause internal electronic components to fall off, resulting in damage to the aircraft and significantly reducing its service life. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft landing gear structure with a buffer function. By setting up a support mechanism, specifically, when the aircraft body lands, the landing gear will contact the ground through the rubber pad at the bottom. At this time, the rubber pad can play a certain role in buffering, and the impact force generated will be buffered by the cooperation of spring two and damping rod two, so that the impact force can be absorbed, significantly reducing rebound and maintaining stability during landing. When the landing deviates, the inner rod contacts the ground, so that the impact force is absorbed by damping rod one and spring one, satisfying the buffering of different deviations and achieving a more stable landing effect. This solves the problem that when the aircraft lands, the landing gear will directly hit the ground, and the impact force will be directly transmitted to the aircraft. The vibration generated by the impact force can easily cause internal electronic components to fall off, resulting in damage to the aircraft.

[0005] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution:

[0006] This utility model relates to an aircraft landing gear structure with a buffer function, comprising an aircraft body, with brackets fixedly connected to each of the four outer corners of the aircraft body, and a shield fixedly connected to the bottom of the brackets, and further comprising:

[0007] A support mechanism is located at the bottom of the aircraft body. The support mechanism includes two fixed seats fixedly connected to the bottom of the aircraft body. Several circular holes are opened inside the fixed seats. A connecting plate is provided below the fixed seats. A mounting plate is provided at the bottom of the connecting plate. A landing gear is fixedly connected to the bottom of the mounting plate. A rubber pad is fixedly connected to the bottom of the landing gear. Several damping rods and springs are fixedly connected to the top of the connecting plate. The tops of the damping rods and springs are fixedly connected to the inner wall of the circular holes on the fixed seats. An outer rod is fixedly connected to the bottom of the shield. An inner rod is slidably connected to the bottom of the outer rod. A damping rod and spring are fixedly connected to the top of the inner rod. The tops of the damping rod and spring are fixedly connected to the bottom of the shield.

[0008] The second damping rod and the second spring correspond to the circular holes on the fixed base, and the second spring is sleeved on the outside of the second damping rod.

[0009] Furthermore, the spring is set on the outside of the damping rod one, the bottom of the inner rod is hemispherical, and the top of the inner rod is a convex plate. The convex plate on the inner rod is used to limit the movement of the inner rod. The top of the spring two is fixedly connected to a rubber sleeve, and the top of the rubber sleeve is fixedly connected to the outside of the fixed seat. The rubber sleeve is used to cover several damping rods two and spring two. The rubber sleeve is used to protect several damping rods two and spring two and improve the aesthetics. At the same time, the setting of the rubber sleeve will not affect the movement of the connecting plate.

[0010] Furthermore, a plug is fixedly connected to the bottom of the connecting plate, and a fixing plate is fixedly connected to the bottom of the mounting plate. A threaded knob is threadedly connected inside the fixing plate. An inclined groove is opened on the side of the plug facing the fixing plate, and a locking block is provided inside the inclined groove. The fixing plate and the mounting plate are integrally formed, and the fixing plate is used to support the threaded knob.

[0011] The bottom of the inner wall of the inclined groove is inclined, and the top of the locking block contacts the bottom of the mounting plate.

[0012] Furthermore, the bottom of the connecting plate contacts the top of the mounting plate, the insert block is positioned and inserted into the mounting plate, the insert block penetrates the mounting plate and extends to the outside, a convex shaft is fixedly connected to the side of the threaded knob facing the locking block, a limit hole is opened on the side of the locking block facing the threaded knob, the convex shaft is rotatably connected inside the limit hole, and the bottom of the locking block contacts the inclined surface on the inclined groove; the cooperation between the convex shaft and the limit hole is used to restrict the threaded knob on the locking block, so that the locking block can be smoothly pushed or pulled when the threaded knob rotates.

[0013] Furthermore, two limiting rods are fixedly connected to the side of the locking block facing the fixed plate. The limiting rods slide through the fixed plate and extend to the outside. The limiting rods are used to support and limit the locking block. When the locking block moves, it will drive the limiting rods to slide on the fixed plate, so that the locking block moves in a straight line.

[0014] This utility model has the following beneficial effects:

[0015] 1. This utility model, through the setting of a support mechanism, specifically, when the main body of the aircraft lands, the landing gear will contact the ground through the rubber pad at the bottom. At this time, the rubber pad can play a certain role in buffering, and the impact force generated will be buffered by the cooperation of spring two and damping rod two, so that the impact force can be absorbed, significantly reducing rebound and maintaining stability during landing. Furthermore, when the landing deviates, the inner rod contacts the ground, so that the impact force is absorbed by damping rod one and spring one, satisfying the buffering of different deviations and achieving a more stable landing effect.

[0016] 2. This utility model uses an installation plate to connect the landing gear to the connecting plate. Then, turning the threaded knob clockwise causes the locking block to push the insert block downwards, thus quickly completing the fixation. By turning the threaded knob counterclockwise, the locking block is disengaged from the insert block, and the landing gear can be pulled downwards for quick disassembly. This facilitates subsequent landing gear replacement and maintenance. This method is simple and convenient to operate, and has higher disassembly and assembly efficiency.

[0017] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0020] Figure 2 This is a schematic diagram of the internal cross-sectional structure of the fixing base of this utility model;

[0021] Figure 3 This is a schematic diagram of the bottom structure of the mounting plate of this utility model;

[0022] Figure 4 This is a schematic diagram of the internal cross-sectional structure of the outer rod of this utility model;

[0023] Figure 5This is a schematic diagram of the overall structure of the insert block of this utility model.

[0024] The attached diagram lists the components represented by each number as follows:

[0025] 1. Aircraft body; 11. Bracket; 12. Shield; 121. Outer rod; 122. Inner rod; 123. Damping rod one; 124. Spring one; 2. Support mechanism; 21. Fixed seat; 22. Connecting plate; 221. Damping rod two; 222. Spring two; 223. Rubber sleeve; 23. Mounting plate; 231. Fixed plate; 232. Threaded knob; 233. Protruding shaft; 24. Landing gear; 241. Rubber pad; 25. Insert block; 251. Inclined groove; 252. Locking block; 253. Limiting hole; 254. Limiting rod. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0027] Please see Figures 1-5 As shown, this utility model is an aircraft landing gear structure with a buffer function, including an aircraft body 1, with brackets 11 fixedly connected to the four outer corners of the aircraft body 1, and shields 12 fixedly connected to the bottom of the brackets 11, and also including:

[0028] Support mechanism 2 is located at the bottom of the aircraft body 1. Support mechanism 2 includes two fixed seats 21 fixedly connected to the bottom of the aircraft body 1. Each fixed seat 21 has several circular holes. A connecting plate 22 is located below the fixed seat 21. A mounting plate 23 is located at the bottom of the connecting plate 22. A landing gear 24 is fixedly connected to the bottom of the mounting plate 23. A rubber pad 241 is fixedly connected to the bottom of the landing gear 24. Several damping rods 221 and springs 222 are fixedly connected to the top of the connecting plate 22. The tops of the damping rods 221 and springs 222 are fixedly connected to the inner walls of the circular holes on the fixed seats 21. An outer rod 121 is fixedly connected to the bottom of the shield 12. An inner rod 122 is slidably connected to the bottom of the outer rod 121. A damping rod 123 and spring 123 are fixedly connected to the top of the inner rod 122. 124, the tops of damping rod 123 and spring 124 are fixedly connected to the bottom of shield 12; when the main body 1 of the aircraft lands, the landing gear 24 will contact the ground through the rubber pad 241 at the bottom. At this time, the rubber pad 241 can play a certain role in buffering, and the impact force generated will be buffered by the cooperation of spring 222 and damping rod 221, so that the impact force can be absorbed, the rebound can be greatly reduced, and the stability during landing can be maintained. When the landing deviates, the inner rod 122 contacts the ground, so that the impact force is absorbed by damping rod 123 and spring 124, satisfying the buffering of different deviations and achieving a more stable landing effect; damping rod 221 and spring 222 correspond to the round holes on the fixed seat 21, and spring 222 is sleeved on the outside of damping rod 221.

[0029] Spring 124 is sleeved on the outside of damping rod 123. The bottom of inner rod 122 is hemispherical and the top of inner rod 122 is a convex plate. The convex plate on inner rod 122 is used to limit the movement of inner rod 122. A rubber sleeve 223 is fixedly connected to the top of spring 222. The top of rubber sleeve 223 is fixedly connected to the outside of fixed seat 21. Rubber sleeve 223 is used to cover several damping rods 221 and springs 222.

[0030] A plug 25 is fixedly connected to the bottom of the connecting plate 22, and a fixing plate 231 is fixedly connected to the bottom of the mounting plate 23. A threaded knob 232 is threadedly connected inside the fixing plate 231. A slanted groove 251 is opened on the side of the plug 25 facing the fixing plate 231, and a locking block 252 is set inside the slanted groove 251. The landing gear 24 is connected to the connecting plate 22 through the mounting plate 23. Then, the threaded knob 232 is rotated clockwise, so that the locking block 252 pushes the plug 25 downward to squeeze it, thereby quickly completing the fixing. By rotating the threaded knob 232 counterclockwise, the locking block 252 is disengaged from the plug 25, and the landing gear 24 can be pulled down for quick disassembly. This facilitates the replacement of the landing gear 24 and subsequent maintenance. This method is simple and convenient to operate and has higher disassembly and assembly efficiency. The bottom of the inner wall of the slanted groove 251 is set with a slope, and the top of the locking block 252 contacts the bottom of the mounting plate 23.

[0031] The bottom of the connecting plate 22 contacts the top of the mounting plate 23. The insert 25 is positioned and inserted into the mounting plate 23. The insert 25 passes through the mounting plate 23 and extends to the outside. The threaded knob 232 is fixedly connected to the side facing the locking block 252 with a convex shaft 233. The locking block 252 has a limit hole 253 on the side facing the threaded knob 232. The convex shaft 233 is rotatably connected inside the limit hole 253. The bottom of the locking block 252 contacts the inclined surface on the inclined groove 251.

[0032] Two limiting rods 254 are fixedly connected to the side of the locking block 252 facing the fixing plate 231. The limiting rods 254 slide through the fixing plate 231 and extend to the outside. The limiting rods 254 are used to support and limit the locking block 252.

[0033] One specific application of this embodiment is:

[0034] In use, the landing gear 24 is connected to the connecting plate 22 via the mounting plate 23. At this time, the insert block 25 will be inserted into the mounting plate 23, thus positioning and installing the mounting plate 23. Then, the threaded knob 232 is rotated clockwise, causing the cam shaft 233 to rotate within the limiting hole 253. This allows the threaded knob 232 to smoothly drive the locking block 252 to move. Subsequently, the threaded knob 232 pushes the locking block 252, causing it to enter the inclined groove 251, and the limiting rod 254 slides on the fixed plate 231, causing the locking block 252 to move in a straight line. The locking block 252 moves in a manner that, when it enters the inclined groove 251, it pushes and presses the insert block 25 downwards through the inclined surface at the bottom of the inner wall of the inclined groove 251, thereby making the mounting plate 23 and the connecting plate 22 fit tightly together and complete the fixation. The other landing gear 24 can be installed in the same way. When the landing gear 24 needs to be replaced, the threaded knob 232 is turned counterclockwise to make the locking block 252 leave the insert block 25, thereby releasing the fixation of the mounting plate 23. Then, the landing gear 24 can be pulled down for quick disassembly, which is convenient for subsequent replacement of the landing gear 24 and for subsequent maintenance.

[0035] After the landing gear 24 is installed, the aircraft body 1 can take off. When the aircraft body 1 lands, the landing gear 24 will contact the ground through the rubber pad 241 at the bottom. At this time, the rubber pad 241 can provide a certain degree of cushioning. As the impact force of landing is relatively large, the aircraft body 1 will move downward through the fixed seat 21, and the second spring 222 will be compressed. The cooperation between the second spring 222 and the second damping rod 221 will buffer the impact force, allowing the impact force to be absorbed by the second damping rod 221 and the second spring 222, and at the same time, it can significantly reduce the impact force. The aircraft body 1 rebounds multiple times, maintaining stability during landing. When the aircraft body 1 deviates during landing, the inner rod 122 will contact the ground and compress the damping rod 123 and spring 124. At this time, the cooperation of the damping rod 123 and spring 124 is used to buffer the impact force. The contact of the inner rod 122 with the ground can prevent the aircraft body 1 from deviating too much. In addition, the bottom of each of the four supports 11 is equipped with an inner rod 122, so it can meet the buffering of different deviations and achieve a more stable landing effect.

[0036] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0037] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the present utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the present utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A landing gear structure for an aircraft with a buffer function, comprising an aircraft body (1), wherein brackets (11) are fixedly connected to the four outer corners of the aircraft body (1), and a shield (12) is fixedly connected to the bottom of the brackets (11), characterized in that, Also includes: A support mechanism (2) is located at the bottom of the aircraft body (1). The support mechanism (2) includes two fixed seats (21) fixedly connected to the bottom of the aircraft body (1). The fixed seats (21) have several round holes inside. A connecting plate (22) is provided below the fixed seats (21). A mounting plate (23) is provided at the bottom of the connecting plate (22). A landing gear (24) is fixedly connected to the bottom of the mounting plate (23). A rubber pad (241) is fixedly connected to the bottom of the landing gear (24). The connecting plate (22) Several damping rods (221) and springs (222) are fixedly connected to the top. The tops of the damping rods (221) and springs (222) are fixedly connected to the inner wall of the round hole on the fixed seat (21). An outer rod (121) is fixedly connected to the bottom of the shield (12). An inner rod (122) is slidably connected to the bottom of the outer rod (121). A damping rod (123) and spring (124) are fixedly connected to the top of the inner rod (122). The tops of the damping rod (123) and spring (124) are fixedly connected to the bottom of the shield (12). The second damping rod (221) and the second spring (222) correspond to the circular holes on the fixed base (21), and the second spring (222) is sleeved on the outside of the second damping rod (221).

2. The aircraft landing gear structure with buffer function according to claim 1, characterized in that, The spring (124) is sleeved on the outside of the damping rod (123). The bottom of the inner rod (122) is hemispherical and the top of the inner rod (122) is a convex plate. The convex plate on the inner rod (122) is used to limit the movement of the inner rod (122).

3. The aircraft landing gear structure with buffer function according to claim 2, characterized in that, A rubber sleeve (223) is fixedly connected to the top of the second spring (222). The top of the rubber sleeve (223) is fixedly connected to the outside of the fixed base (21). The rubber sleeve (223) is used to cover several damping rods (221) and the second spring (222).

4. The aircraft landing gear structure with buffer function according to claim 3, characterized in that, The bottom of the connecting plate (22) is fixedly connected to a plug (25), the bottom of the mounting plate (23) is fixedly connected to a fixing plate (231), the fixing plate (231) is threadedly connected to a threaded knob (232), the plug (25) is provided with a slanted groove (251) on the side facing the fixing plate (231), and a locking block (252) is provided inside the slanted groove (251); The bottom of the inner wall of the inclined groove (251) is inclined, and the top of the locking block (252) is in contact with the bottom of the mounting plate (23).

5. The aircraft landing gear structure with buffer function according to claim 4, characterized in that, The bottom of the connecting plate (22) contacts the top of the mounting plate (23), the insert (25) is positioned and inserted into the mounting plate (23), and the insert (25) penetrates the mounting plate (23) and extends to the outside.

6. The aircraft landing gear structure with a buffer function according to claim 5, characterized in that, The threaded knob (232) is fixedly connected to a convex shaft (233) on the side facing the locking block (252). The locking block (252) has a limiting hole (253) on the side facing the threaded knob (232). The convex shaft (233) is rotatably connected inside the limiting hole (253). The bottom of the locking block (252) is in contact with the inclined surface on the inclined groove (251).

7. The aircraft landing gear structure with a buffer function according to claim 5, characterized in that, The locking block (252) has two limiting rods (254) fixedly connected to the side facing the fixing plate (231). The limiting rods (254) slide through the fixing plate (231) and extend to the outside. The limiting rods (254) are used to support and limit the locking block (252).

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