Part damping device for aircraft

Abstract

The part damping device for the aircraft comprises an undercarriage, the undercarriage comprises two sets of foot stools, two sets of cross beams and two sets of connecting frames, the two sets of cross beams are arranged above the two sets of foot stools respectively, and the two sets of connecting frames are arranged above the two sets of foot stools respectively. The damping device comprises two sets of connecting frames and two sets of foot stools, damping assemblies used for buffering impact force generated during landing of the aircraft are arranged between the two sets of foot stools and the two sets of cross beams correspondingly, and the two sets of connecting frames are connected to the tops of the two sets of cross beams correspondingly. The shock absorption assembly is arranged on the cross beam, can bear the weight and impact force from an aircraft and is matched with the cross beam to form a stable frame, it is guaranteed that the whole shock absorption device is not prone to deformation or damage when being impacted, and the overall stability and reliability of the shock absorption device are guaranteed. And the impact force borne by the aircraft during landing is effectively reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a shock absorbing device for aircraft parts. Background Art

[0002] Aerial photography aircraft, also known as unmanned aerial photography system or aerial photography drone, is an aircraft specially used for aerial photography and video recording. It is usually equipped with high-definition cameras, gimbals, image transmission systems and other related equipment to capture images taken from an aerial perspective. The performance of the aerial photography aircraft landing gear shock absorber is crucial to ensure the stable take-off and landing of the aircraft, extend its service life and protect the aerial photography equipment from vibration damage.

[0003] During takeoff, hovering and landing, the landing gear of an aerial photography aircraft will frequently come into contact with the ground or supporting platform, generating strong impact and vibration. These vibrations will not only affect the stability and safety of the aircraft, but may also cause damage to aerial photography equipment such as cameras and sensors, thereby affecting the quality of aerial photography. Therefore, we need to propose a shock-absorbing device for aircraft components. Utility Model Content

[0004] The purpose of the utility model is to provide a shock absorbing device for aircraft parts, aiming to solve the problem in the prior art that during take-off, hovering and landing of aerial photography aircraft, the landing gear will frequently contact the ground or supporting platform, generating strong impact and vibration, which will not only affect the stability and safety of the aircraft, but also may cause damage to aerial photography equipment such as cameras, sensors, etc., thereby affecting the quality of aerial photography.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] A shock absorbing device for aircraft parts includes a landing gear, wherein the landing gear includes two groups of tripods, two groups of cross beams and two groups of connecting frames, the two groups of cross beams are respectively arranged above the two groups of tripods, and shock absorbing components for buffering the impact force generated when the aircraft lands are respectively arranged between the two groups of tripods and the two groups of cross beams, and the two groups of connecting frames are respectively connected to the tops of the two groups of cross beams.

[0007] Preferably, the shock-absorbing assembly includes two groups of fixed sleeves, the top ends of the two groups of fixed sleeves are fixedly connected to the bottom of the crossbeam, the interiors of the two groups of fixed sleeves are provided with cavities, the bottoms of the two groups of fixed sleeves are slidably plugged with movable rods, the outer walls of the movable rods are slidably connected to the inner walls of the cavities, and the bottom ends of the movable rods are fixedly connected to the top ends of the tripods.

[0008] Preferably, a buffer spring is further included, wherein the top end of the buffer spring is fixedly connected to the inner top of the cavity, and the bottom end of the buffer spring is fixedly connected to the top of the movable rod.

[0009] Preferably, it further comprises a damper, the top end of the damper is fixedly connected to the bottom of the crossbeam, the bottom end of the damper is fixedly connected to the top of the tripod, and the damper is located between the two sets of fixing sleeves.

[0010] Preferably, both ends of the two groups of the tripods are respectively provided with upturned ends, and the outer walls of the two groups of the tripods are both provided with wear-resistant layers.

[0011] Preferably, the tops of the two groups of beams are respectively provided with inclined surfaces, the connecting frame includes several groups of connecting rods, the bottom ends of the several groups of connecting rods are fixedly connected to the tops of the inclined surfaces, and reinforcing ribs are respectively fixedly connected between two adjacent groups of connecting rods.

[0012] Preferably, energy absorbing rods are fixedly connected between every two groups of reinforcing ribs, and the energy absorbing rods are arranged in an arc shape.

[0013] Compared with the prior art, the beneficial effects of the utility model are:

[0014] 1. The utility model sets a tripod, a crossbeam and a shock-absorbing assembly for coordinated use. The tripod, as the basic supporting structure of the shock-absorbing device, can withstand the weight and impact force from the aircraft, and cooperates with the crossbeam to form a stable frame, ensuring that the entire shock-absorbing device is not easily deformed or damaged when impacted, thereby ensuring the overall stability and reliability of the shock-absorbing device. The shock-absorbing assembly is the core part of the shock-absorbing device, which effectively reduces the impact force received by the aircraft during landing by absorbing and dispersing the impact force.

[0015] 2. By setting an upturned end, the design of the upturned end can make the tripod form a certain angle when it contacts the ground, so as to adapt to different terrains and slopes. This design increases the adaptability and stability of the aircraft under different terrain conditions. By setting the connection frame and the energy-absorbing rod for coordinated use, the main function of the energy-absorbing rod is to absorb the impact energy generated by the aircraft during the landing process. When the aircraft lands, the energy-absorbing rod can quickly deform and absorb the impact energy, thereby reducing damage to the aircraft components. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the structure of the utility model;

[0017] Figure 2 It is a structural schematic diagram of the tripod, crossbeam and shock absorbing assembly of the utility model;

[0018] Figure 3 It is a structural schematic diagram of the crossbeam and the connecting frame of the utility model.

[0019] In the figure: 1, landing gear; 2, tripod; 3, crossbeam; 4, connecting frame; 5, shock-absorbing assembly; 501, fixed sleeve; 502, cavity; 503, movable rod; 6, buffer spring; 7, damper; 8, upturned end; 9, wear-resistant layer; 10, inclined surface; 11, connecting rod; 12, reinforcing rib; 13, energy-absorbing rod. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0021] See also Figure 1-3 , the utility model provides a technical solution:

[0022] A shock absorbing device for aircraft parts comprises a landing gear 1, wherein the landing gear 1 comprises two groups of tripods 2, two groups of cross beams 3 and two groups of connecting frames 4, and is connected to the aircraft through the connecting frames 4. The two groups of cross beams 3 are respectively arranged above the two groups of tripods 2, and shock absorbing components 5 for buffering the impact force generated when the aircraft lands are respectively arranged between the two groups of tripods 2 and the two groups of cross beams 3. The two groups of connecting frames 4 are respectively connected to the tops of the two groups of cross beams 3. The utility model sets the tripod 2, the cross beam 3 and the shock absorbing component 5 for coordinated use. The tripod 2, as the basic supporting structure of the shock absorbing device, can withstand the weight and impact force from the aircraft, and cooperates with the cross beams to form a stable frame, ensuring that the entire shock absorbing device is not easily deformed or damaged when impacted, thereby ensuring the overall stability and reliability of the shock absorbing device. The shock absorbing component is the core part of the shock absorbing device, which effectively reduces the impact force received by the aircraft when landing by absorbing and dispersing the impact force.

[0023] The shock absorbing assembly 5 includes two groups of fixed sleeves 501, the top ends of the two groups of fixed sleeves 501 are fixedly connected to the bottom of the cross beam 3, the insides of the two groups of fixed sleeves 501 are provided with cavities 502, the bottoms of the two groups of fixed sleeves 501 are slidably plugged with movable rods 503, and the outer walls of the movable rods 503 are slidably connected to the inner walls of the cavities 502, and the bottom ends of the movable rods 503 are fixedly connected to the top ends of the tripods 2;

[0024] It also includes a buffer spring 6, the top end of the buffer spring 6 is fixedly connected to the inner top of the cavity 502, and the bottom end of the buffer spring 6 is fixedly connected to the top of the movable rod 503;

[0025] It is worth noting that when the impact force acts on the buffer spring 6, the buffer spring 6 will be deformed by the force, and the kinetic energy of the impact force will be converted into elastic energy for storage. This energy conversion makes the compression or extension of the buffer spring 6 by the impact force more uniform, and the kinetic energy is stored in the buffer spring 6. When the impact force ends, the elastic energy stored in the buffer spring 6 is released, and the buffer spring 6 returns to its original state, transferring the stored energy to the outside in the form of buffer force, thereby achieving a shock absorbing effect.

[0026] It also includes a damper 7, the top end of the damper 7 is fixedly connected to the bottom of the beam 3, the bottom end of the damper 7 is fixedly connected to the top of the tripod 2, and the damper 7 is located between the two sets of fixed sleeves 501;

[0027] By adopting the above case, the damper 7 is a component that can reduce the vibration amplitude of the aircraft, which is mainly achieved by absorbing vibration energy or hindering the propagation of vibration. When the damper 7 is used in combination with the buffer spring 6, it can play a shock-absorbing role. When the buffer spring 6 is vibrated by an external force, the damper 7 absorbs the vibration energy and converts part of the kinetic energy into heat energy or other forms of energy dissipation, thereby reducing the amplitude and frequency of the vibration;

[0028] Both ends of the two sets of tripods 2 are respectively provided with upturned ends 8, and the outer walls of the two sets of tripods 2 are provided with wear-resistant layers 9. By providing the upturned ends 8, the design of the upturned ends 8 can make the tripods 2 form a certain angle when contacting the ground, so as to adapt to different terrains and slopes. This design increases the adaptability and stability of the aircraft under different terrain conditions;

[0029] The tops of the two groups of beams 3 are respectively provided with inclined surfaces 10, and the connecting frame 4 includes a plurality of groups of connecting rods 11, the bottom ends of the plurality of groups of connecting rods 11 are fixedly connected to the tops of the inclined surfaces 10, and reinforcing ribs 12 are respectively fixedly connected between two adjacent groups of connecting rods 11, which play a role in increasing the overall structural strength of the device;

[0030] An energy-absorbing rod 13 is fixedly connected between every two groups of reinforcing ribs 12. The energy-absorbing rod 13 is arranged in an arc shape. By setting the connecting frame 4 and the energy-absorbing rod 13 for coordinated use, the main function of the energy-absorbing rod 13 is to absorb the impact energy generated by the aircraft during the landing process. When the aircraft lands, the energy-absorbing rod 13 can be deformed quickly and absorb the impact energy, thereby reducing damage to aircraft parts.

[0031] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A shock absorbing device for aircraft parts, comprising a landing gear (1), characterized in that: The landing gear (1) comprises two groups of foot frames (2), two groups of cross beams (3) and two groups of connecting frames (4); the two groups of cross beams (3) are respectively arranged above the two groups of foot frames (2); and shock absorbing components (5) for buffering the impact force generated when the aircraft lands are respectively arranged between the two groups of foot frames (2) and the two groups of cross beams (3); and the two groups of connecting frames (4) are respectively connected to the tops of the two groups of cross beams (3).

2. The aircraft component shock absorbing device according to claim 1, characterized in that: The shock absorbing assembly (5) comprises two groups of fixed sleeves (501), the top ends of the two groups of fixed sleeves (501) are fixedly connected to the bottom of the crossbeam (3), the interiors of the two groups of fixed sleeves (501) are provided with cavities (502), the bottoms of the two groups of fixed sleeves (501) are slidably plugged with movable rods (503), and the outer walls of the movable rods (503) are slidably connected to the inner walls of the cavities (502), and the bottom ends of the movable rods (503) are fixedly connected to the top ends of the tripods (2).

3. The aircraft component shock absorbing device according to claim 2, characterized in that: It also includes a buffer spring (6), the top end of the buffer spring (6) is fixedly connected to the inner top of the cavity (502), and the bottom end of the buffer spring (6) is fixedly connected to the top of the movable rod (503).

4. The aircraft component shock absorbing device according to claim 3, characterized in that: It also includes a damper (7), the top end of the damper (7) is fixedly connected to the bottom of the crossbeam (3), the bottom end of the damper (7) is fixedly connected to the top of the tripod (2), and the damper (7) is located between the two sets of fixed sleeves (501).

5. The aircraft component shock absorbing device according to claim 1, characterized in that: Both ends of the two groups of tripods (2) are respectively provided with upturned ends (8), and the outer walls of the two groups of tripods (2) are both provided with wear-resistant layers (9).

6. The aircraft component shock absorbing device according to claim 1, characterized in that: The tops of the two groups of cross beams (3) are respectively provided with inclined surfaces (10), the connecting frame (4) comprises a plurality of groups of connecting rods (11), the bottom ends of the plurality of groups of connecting rods (11) are fixedly connected to the tops of the inclined surfaces (10), and reinforcing ribs (12) are respectively fixedly connected between two adjacent groups of connecting rods (11).

7. The aircraft component shock absorbing device according to claim 6, characterized in that: An energy absorbing rod (13) is fixedly connected between each two groups of the reinforcing ribs (12), and the energy absorbing rod (13) is arranged in an arc shape.

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