Landing cushion mechanism and flying device

Abstract

This application discloses a landing buffer mechanism and flight device, relating to the field of aircraft. The landing buffer mechanism includes at least one set of buffer components disposed below the wing. Each buffer component includes a housing, multiple buffer rods, a linkage unit, and an elastic element. Multiple buffer rods are slidably mounted on the housing, with at least a portion of the rods extending to the outer side of the housing. The linkage unit is disposed between two adjacent buffer rods, used to cause them to move towards or away from each other when they slide relative to each other. The elastic element is sleeved on the outer wall of the linkage unit and used to drive the buffer rods to reset. When the landing surface is flat, the multiple buffer rods slide synchronously, with the elastic element providing cushioning; when the landing surface is uneven, each buffer rod slides independently according to the terrain differences, generating relative movement through the linkage unit to adaptively match the terrain undulations. The damping force generated by the elastic element and the relative movement works together to provide cushioning, effectively suppressing changes in aircraft attitude and improving landing stability and safety.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a landing buffer mechanism and flight device. Background Technology

[0002] Fixed-wing aircraft, with their advantages of long endurance and high flight efficiency, have been widely used in various fields such as surveying, exploration, and agricultural plant protection. During takeoff and landing, the landing buffer mechanism is a key component that ensures the safety of the airframe structure and the stability of the equipment.

[0003] Currently, most fixed-wing aircraft landing gear or buffer mechanisms use rigid support rods combined with a single spring or telescopic sleeve structure. However, this traditional design has drawbacks in practical applications. When the aircraft lands on uneven or sloping ground, the various support points cannot independently and adaptively adjust to changes in the terrain, which can easily cause the aircraft to tilt or even roll over, seriously affecting landing stability and safety. Summary of the Invention

[0004] This application provides a landing buffer mechanism and a flight device, which solves the problems mentioned in the background art.

[0005] In a first aspect, embodiments of this application provide a landing buffer mechanism, comprising: at least one set of buffer components disposed below the wing; the buffer components comprising: a housing; a plurality of buffer rods slidably mounted on the housing, wherein at least a portion of each buffer rod extends to the outside of the housing for contacting the landing surface; a linkage unit disposed between two adjacent buffer rods for causing the two adjacent buffer rods to move toward or away from each other when the buffer rods slide relative to each other; and an elastic element disposed within the housing and sleeved on the outer wall of the linkage unit for driving the buffer rods to reset after buffering and / or after buffering is completed.

[0006] In conjunction with the first aspect, in one possible implementation, the linkage unit includes: a sliding rod, which is slidably disposed within the housing along the sliding direction of the buffer rod; wherein the elastic element is sleeved on the outer wall of the sliding rod, and its two ends respectively abut against the inner top wall of the housing and the sliding rod.

[0007] In conjunction with the first aspect, in one possible implementation, the landing buffer mechanism further includes a transmission assembly; the transmission assembly is tractively connected to the sliding rod and the buffer rod respectively, for converting the sliding of the buffer rod into the linear displacement of the sliding rod.

[0008] In conjunction with the first aspect, in one possible implementation, the transmission assembly includes: a linkage gear disposed at one end of the sliding rod; and a plurality of rack portions disposed on corresponding buffer rods and meshing with the linkage gear; wherein the opposing or reciprocating movements of the two buffer rods are converted into linear displacement of the sliding rod through the meshing of the linkage gear and the rack portions.

[0009] In conjunction with the first aspect, in one possible implementation, the landing buffer mechanism further includes a buffer unit; the buffer unit is drivenly connected to the sliding rod and is used to convert the linear motion of the sliding rod into rotational motion, and to provide buffering force through the shear resistance of the viscous damping medium to absorb impact energy.

[0010] In conjunction with the first aspect, in one possible implementation, the buffer unit includes: a buffer cylinder, fixedly disposed within the housing, the interior of which is filled with a viscous damping medium; a transmission rod, rotatably disposed within the buffer cylinder; and an actuating element, fixedly disposed on the transmission rod and immersed in the viscous damping medium; wherein, the linear displacement of the sliding rod drives the transmission rod to rotate via a transmission pair, thereby causing the actuating element to agitate the viscous damping medium to generate buffer damping.

[0011] In conjunction with the first aspect, in one possible implementation, the transmission pair includes: a buffer rack disposed on the sliding rod; and a buffer gear coaxially fixed to the transmission rod and meshing with the buffer rack.

[0012] In conjunction with the first aspect, in one possible implementation, the buffer rod is provided with an abutment foot at one end located on the outside of the housing; the abutment foot is a spherical structure or a roller structure; and / or also includes multiple arms; multiple sets of the buffer components are respectively disposed on the corresponding arms and correspond to the four directions of the flight device: front, back, left, and right.

[0013] In conjunction with the first aspect, in one possible implementation, the buffer rod is provided with a limiting structure to limit the sliding stroke of the buffer rod relative to the housing; the limiting structure includes: a positioning groove, which is disposed through the buffer rod; and a positioning rod, which is fixedly disposed in the housing and slidably engaged in the positioning groove.

[0014] Secondly, embodiments of this application provide a flight device, including the landing buffer mechanism of the first aspect or any possible implementation of the first aspect.

[0015] One or more technical solutions provided in the embodiments of this application have at least the following technical effects:

[0016] The landing buffer mechanism of this application embodiment includes at least one set of buffer components. This application solves the problem that traditional rigid support rods combined with a single spring or telescopic sleeve structure cannot independently and adaptively adjust to changes in terrain, leading to the aircraft easily tilting or even overturning on uneven or sloping landing surfaces. This is achieved by setting at least one set of buffer components under the wing and sliding multiple buffer rods onto the housing. The synergistic effect of the linkage unit and elastic elements solves this problem. When the landing surface is flat, multiple buffer rods slide synchronously, with the elastic elements providing the buffering effect. When the landing surface is uneven, each buffer rod can slide to different degrees according to local terrain differences, and the linkage unit causes adjacent buffer rods to move relative to each other, achieving opposite or forward movement, thus adaptively matching the terrain undulations. In this case, the elastic elements and the relative movement of the two buffer rods work together to provide buffering, effectively suppressing excessive changes in aircraft attitude and improving the stability and safety of the landing process. Simultaneously, during and after the buffering process, the elastic elements can drive the buffer rods to reset, ensuring the landing buffer mechanism has continuous and reliable reusability. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the landing buffer mechanism provided in the embodiments of this application;

[0019] Figure 2 for Figure 1 Enlarged view of point A in the image;

[0020] Figure 3 This is a schematic diagram of the structure of the buffer component provided in the embodiments of this application;

[0021] Figure 4 This is a schematic diagram of the structure of the buffer unit provided in the embodiments of this application;

[0022] Figure 5 This is a schematic diagram of the limiting structure provided in an embodiment of this application.

[0023] Icons: 1-Buffer assembly; 11-Shell; 12-Buffer rod; 13-Linkage unit; 131-Sliding rod; 14-Elastic element; 15-Transmission assembly; 151-Linkage gear; 152-Rack section; 16-Buffer unit; 161-Buffer cylinder; 162-Transmission rod; 163-Actuating element; 164-Transmission pair; 1641-Buffer rack; 1642-Buffer gear; 17-Abutting foot; 18-Limiting structure; 181-Positioning groove; 182-Positioning rod; 19-Limiting plate; 191-Limiting seat; 2-Wing; 3-Arm. Detailed Implementation

[0024] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0025] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0026] This application provides a landing buffer mechanism, such as... Figures 1 to 5As shown, the landing cushioning mechanism includes at least one set of cushioning components 1. At least one set of cushioning components 1 is disposed below the wing 2. The cushioning component 1 includes a housing 11, a plurality of cushioning rods 12, a linkage unit 13, and an elastic element 14. The plurality of cushioning rods 12 are slidably mounted on the housing 11, and at least a portion of each cushioning rod 12 extends to the outside of the housing 11 for contact with the landing surface. The linkage unit 13 is disposed between two adjacent cushioning rods 12 and is used to cause the two adjacent cushioning rods 12 to move towards or away from each other when the cushioning rods 12 slide relative to each other. The elastic element 14 is disposed within the housing 11 and sleeved on the outer wall of the linkage unit 13, and is used to drive the cushioning rods 12 to reset after cushioning and / or after the cushioning is completed.

[0027] It should be noted that this application solves the problem that traditional rigid support rods combined with a single spring or telescopic sleeve structure cannot independently and adaptively adjust according to the unevenness of the terrain, which leads to the aircraft tilting or even overturning on uneven or sloping landing surfaces. This is achieved by setting at least one set of buffer components 1 below the wing 2 and sliding multiple buffer rods 12 onto the shell 11. The synergistic effect of the linkage unit 13 and the elastic element 14 further addresses this issue. When the landing surface is flat, multiple buffer rods 12 slide synchronously, with the elastic element 14 providing the main buffering effect. When the landing surface is uneven, each buffer rod 12 can slide to different degrees according to local terrain differences. The linkage unit 13 causes adjacent buffer rods 12 to move relative to each other, achieving opposite or inverse movements, thus adaptively matching the terrain undulations. In this case, the relative movement of the elastic element 14 and the two buffer rods 12 work together to provide buffering, effectively suppressing excessive changes in the aircraft's attitude and improving the stability and safety of the landing process. Meanwhile, during and after the buffering process, the elastic element 14 can drive the buffer rod 12 to reset, ensuring that the landing buffer mechanism has a continuous and reliable reusability.

[0028] In one embodiment of this application, the limiting seat 191 is fixedly connected to the inside of the housing 11. The limiting seat 191 has a U-shaped structure, and its opening is oriented towards the sliding path of the buffer rod 12. The inner sidewall of the limiting seat 191 is provided with a guide groove along the sliding direction of the buffer rod 12. The buffer rod 12 is slidably engaged in the guide groove so as to guide and limit the sliding of the buffer rod 12 through the guide groove.

[0029] In this embodiment, the linkage unit 13 includes a sliding rod 131. The sliding rod 131 is slidably disposed within the housing 11 along the sliding direction of the buffer rod 12. An elastic element 14 is sleeved on the outer wall of the sliding rod 131, with its two ends abutting against the inner top wall of the housing 11 and the sliding rod 131, respectively.

[0030] In one embodiment of this application, a limiting disk 19 is coaxially fixed on the sliding rod 131, and an elastic element 14 is sleeved on the outer wall of the sliding rod 131. One end of the elastic element 14 abuts against the inner top wall of the housing 11, and the other end of the elastic element 14 abuts against the top of the limiting disk 19, thereby achieving axial positioning and stable support of the elastic element 14 on the sliding rod 131. This structure allows the linear displacement of the sliding rod 131 to uniformly compress the elastic element 14 through the limiting disk 19 when the buffer rod 12 moves relative to it, ensuring that the elastic force is stably transmitted along the axial direction of the sliding rod 131 and preventing the elastic element 14 from deflecting or becoming unstable during compression. At the same time, after the buffering is completed, the elastic element 14 pushes the sliding rod 131 to reset through the limiting disk 19, thereby driving the buffer rod 12 to return to its initial position. This effectively improves the reliability and consistency of the reset process of the buffer assembly 1, and the structure is compact, which is beneficial for optimizing the internal space layout of the housing 11.

[0031] In this embodiment, the landing buffer mechanism further includes a transmission assembly 15. The transmission assembly 15 is connected to the sliding rod 131 and the buffer rod 12 respectively, and is used to convert the sliding of the buffer rod 12 into the linear displacement of the sliding rod 131.

[0032] In this embodiment, the transmission assembly 15 includes a linkage gear 151 and multiple rack sections 152. The linkage gear 151 is disposed at one end of the sliding rod 131. The multiple rack sections 152 are respectively disposed on corresponding buffer rods 12 and mesh with the linkage gear 151. The relative or opposite movements of the two buffer rods 12 are converted into linear displacement of the sliding rod 131 through the meshing of the linkage gear 151 and the rack sections 152.

[0033] In this embodiment, the landing buffer mechanism further includes a buffer unit 16. The buffer unit 16 is connected to the sliding rod 131 and is used to convert the linear motion of the sliding rod 131 into rotational motion, and to provide buffering force through the shear resistance of the viscous damping medium to absorb impact energy.

[0034] In this embodiment, the buffer unit 16 includes a buffer cylinder 161, a transmission rod 162, and an actuating element 163. The buffer cylinder 161 is fixedly disposed within the housing 11 and is filled with a viscous damping medium. The transmission rod 162 is rotatably disposed within the buffer cylinder 161. The actuating element 163 is fixedly disposed on the transmission rod 162 and immersed in the viscous damping medium. The linear displacement of the sliding rod 131 drives the transmission rod 162 to rotate via the transmission pair 164, thereby causing the actuating element 163 to agitate the viscous damping medium to generate buffer damping.

[0035] In this embodiment, the transmission pair 164 includes a buffer rack 1641 and a buffer gear 1642. The buffer rack 1641 is mounted on the sliding rod 131. The buffer gear 1642 is coaxially fixed on the transmission rod 162 and meshes with the buffer rack 1641. When the sliding rod 131 undergoes linear displacement, the buffer rack 1641 drives the buffer gear 1642 to precisely engage and transmit the linear motion of the sliding rod 131, efficiently and reliably converting it into the rotational motion of the transmission rod 162. This drives the agitator 163 to stir the viscous damping medium, generating stable shear resistance. This transmission pair 164 has a compact structure, high transmission accuracy, and rapid response. It can smoothly transmit the impact energy at the moment of landing to the buffer unit 16 for viscous dissipation in the form of mechanical transmission. Compared with the traditional spring structure, it effectively avoids energy rebound and oscillation, improving the smoothness of the buffering process and the energy absorption efficiency.

[0036] This application, by setting up a buffer assembly 1, utilizes the meshing of the linkage gear 151 and the rack 152 to allow the buffer rods 12 on both sides to slide independently according to the unevenness of the ground, and achieves opposite or backward movement through the linkage unit 13, thereby adaptively matching terrain changes and effectively eliminating the fuselage tilting problem caused by unilateral ground contact. Simultaneously, the sliding rod 131 drives the buffer rack 1641 to move, driving the buffer gear 1642 to rotate, causing the transmission rod 162 to drive the agitator 163 to agitate the viscous damping medium inside the buffer cylinder 161. This process converts linear impact into rotational kinetic energy, utilizing the shear resistance of the viscous damping medium to form hydraulic buffer, efficiently absorbing and dissipating impact energy.

[0037] In this embodiment, the buffer rod 12 has an abutment foot 17 at one end located outside the housing 11. The abutment foot 17 has a spherical or roller structure. Specifically, the outer wall of the abutment foot 17 is provided with a rubber sleeve.

[0038] This application sets the contact foot 17 as a spherical or roller structure, which allows it to fit more closely to the ground when it comes into contact with the landing surface, increasing the contact adaptability and avoiding situations where the local pressure is too high or the support is unstable due to the small contact area. This further improves the grounding stability and reliability of the landing buffer mechanism under different terrain conditions.

[0039] And / or may also include multiple arms 3. Multiple sets of buffer components 1 are respectively disposed on the corresponding arms 3, corresponding to the four directions of front, back, left and right of the flight device.

[0040] Specifically, the buffer assembly 1 of this application is provided with four sets. By distributing the four sets of buffer assemblies 1 in the front, rear, left, and right directions of the flight device, it achieves all-round stable support for the aircraft during landing, effectively disperses multi-directional impact forces, and further improves the landing stability and anti-roll capability of the flight device under complex terrain conditions.

[0041] In this embodiment, a limiting structure 18 is provided on the buffer rod 12 to limit the sliding stroke of the buffer rod 12 relative to the housing 11. The limiting structure 18 includes a positioning groove 181 and a positioning rod 182. The positioning groove 181 is disposed through the buffer rod 12. The positioning rod 182 is fixedly disposed inside the housing 11 and is slidably engaged in the positioning groove 181.

[0042] In this embodiment, the sliding stroke of the buffer rod 12 is limited by the cooperation of the positioning groove 181 and the positioning rod 182, which effectively prevents the buffer rod 12 from slipping off the housing 11 and ensures the stability and reliability of the buffer assembly 1.

[0043] This application provides a flight device including the landing buffer mechanism described above.

[0044] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0045] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A landing buffer mechanism, characterized in that, include: At least one set of buffer components (1) is disposed below the wing (2); The buffer component (1) includes: Shell (11); Multiple buffer rods (12) are slidably mounted on the housing (11), and at least a portion of the rod of each buffer rod (12) extends to the outside of the housing (11) for contacting the landing surface; A linkage unit (13) is disposed between two adjacent buffer rods (12) for moving the two adjacent buffer rods (12) toward each other or away from each other when the buffer rods (12) slide relative to each other; the linkage unit (13) includes a sliding rod (131) which is slidably disposed in the housing (11) along the sliding direction of the buffer rods (12); It also includes a transmission assembly (15); The transmission assembly (15) includes: A linkage gear (151) is disposed at one end of the sliding rod (131); Multiple rack sections (152) are respectively disposed on the corresponding buffer rods (12) and mesh with the linkage gears (151); The opposing or reciprocating movements of the two buffer rods (12) are converted into linear displacement of the sliding rod (131) through the meshing of the linkage gear (151) and the rack (152). And / or may also include multiple arms (3); multiple sets of buffer components (1) are respectively disposed on the corresponding arms (3); An elastic element (14) is disposed inside the housing (11) and sleeved on the outer wall of the linkage unit (13) for driving the buffer rod (12) to reset after buffering and / or after buffering ends.

2. The landing buffer mechanism according to claim 1, characterized in that, The elastic element (14) is sleeved on the outer wall of the sliding rod (131), and its two ends abut against the inner top wall of the housing (11) and the sliding rod (131) respectively.

3. The landing buffer mechanism according to claim 2, characterized in that, The transmission assembly (15) is connected to the sliding rod (131) and the buffer rod (12) respectively, and is used to convert the sliding of the buffer rod (12) into the linear displacement of the sliding rod (131).

4. The landing buffer mechanism according to claim 1, characterized in that, It also includes a buffer unit (16); The buffer unit (16) is connected to the sliding rod (131) for converting the linear motion of the sliding rod (131) into rotational motion, and providing buffering force through the shear resistance of the viscous damping medium to absorb impact energy.

5. The landing buffer mechanism according to claim 4, characterized in that, The buffer unit (16) includes: A buffer cylinder (161) is fixedly installed inside the housing (11), and its interior is filled with a viscous damping medium; The transmission rod (162) is rotatably disposed inside the buffer cylinder (161); The actuating element (163) is fixedly mounted on the transmission rod (162) and immersed in a viscous damping medium; The linear displacement of the sliding rod (131) drives the transmission rod (162) to rotate through the transmission pair (164), which in turn drives the agitator (163) to stir the viscous damping medium to generate buffer damping.

6. The landing buffer mechanism according to claim 5, characterized in that, The transmission pair (164) includes: A buffer rack (1641) is provided on the sliding rod (131); The buffer gear (1642) is coaxially fixed on the transmission rod (162) and meshes with the buffer rack (1641).

7. The landing buffer mechanism according to claim 1, characterized in that, The buffer rod (12) is provided with an abutment foot (17) at one end located outside the housing (11). The abutment foot (17) has a spherical structure or a roller structure; And / or may also include multiple arms (3); Multiple sets of the buffer components (1) are respectively set on the corresponding arms (3) and correspond to the four directions of the flight device: front, back, left, and right.

8. The landing buffer mechanism according to claim 1, characterized in that, A limiting structure (18) is provided on the buffer rod (12) to limit the sliding stroke of the buffer rod (12) relative to the housing (11); The limiting structure (18) includes: A positioning groove (181) is provided through the buffer rod (12); The positioning rod (182) is fixedly installed inside the housing (11) and slidably engaged in the positioning groove (181).

9. A flight device, characterized in that, Includes the landing buffer mechanism as described in any one of claims 1-8.

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