Undercarriage of vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of undercarriages, and discloses an undercarriage of a vertical take-off and landing aircraft, which comprises a support assembly, the upper end of the support assembly is fixedly connected with a first connecting sleeve, the inner part of the first connecting sleeve is fixedly sleeved with a first connecting rod, the upper end of the first connecting sleeve is fixedly connected with a fixing assembly, and the fixing assembly is fixedly connected with a second connecting rod. A spring is fixedly connected to the interior of the fixing assembly, and a damper is fixedly connected to the upper end of the spring. The fixing assembly, the damper and the spring are additionally arranged at the connecting position of the first connecting rod and the supporting rod to form a buffering device, impact on the aircraft body can be reduced when the aircraft lands and makes contact with the ground, the aircraft body is protected against damage, impact energy is absorbed, and the service life of the aircraft is prolonged. The buffering device can effectively reduce vibration of the aircraft in the flying and landing process, so that the flying stability can be improved, airborne equipment is protected, and fatigue damage of an aircraft body structure is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of landing gears, and more specifically, to a landing gear for a vertical take-off and landing aircraft. Background Art

[0002] Electric vertical take-off and landing aircraft eVTOL, in layman's terms, is an electric aircraft that can take off and land vertically without a runway. In recent years, China has made significant achievements in the green industry. In terms of transportation, the new energy vehicle industry has developed rapidly. With the upgrading and transformation of electrification, the aviation industry has also ushered in new opportunities. eVTOL is expected to play an important role in future air travel scenarios. eVTOL is also a rare opportunity for the domestic aviation industry to overtake on the curve. Because it is a vertical take-off and landing, it will be subject to greater impact energy during the take-off and landing process, which is easy to cause damage to the internal parts of the fuselage. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the utility model provides a landing gear for a vertical take-off and landing aircraft, which has the advantage of absorbing impact and vibration of the aircraft.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a landing gear of a vertical take-off and landing aircraft, comprising a support assembly, the upper end of the support assembly is fixedly connected with a connecting kit 1, the interior of the connecting kit 1 is fixedly sleeved with a connecting rod 1, the upper end of the connecting kit 1 is fixedly connected with a fixing assembly, the interior of the fixing assembly is fixedly connected with a spring, the upper end of the spring is fixedly connected with a damper, the upper end of the damper is fixedly connected with a support rod, the surface of the support rod is fixedly sleeved with a connecting kit 2, and the side of the connecting kit 2 is fixedly connected with a connecting rod 2.

[0005] As a preferred technical solution of the utility model, the shape of the support component is an "X" shape, the bottom surface of the support component is flat, and the four corners of the support component are slightly tilted upwards.

[0006] As a preferred technical solution of the present utility model, the bottom surface of the connecting sleeve 1 is a plane, and the upper inclined side of the connecting sleeve 1 is a plane.

[0007] As a preferred technical solution of the utility model, both the front and rear ends of the connecting rod 1 are tilted, and both the front and rear ends of the connecting rod 1 are spherical.

[0008] As a preferred technical solution of the utility model, the lower end of the support rod is a rectangular block, and the area value of the rectangular block is equal to the area value inside the fixing component.

[0009] As a preferred technical solution of the present utility model, there are two support rods, and fixing components are fixed on the surfaces of the support rods at the front and rear positions. Fixing card slots are formed on the surfaces opposite to the fixing components to connect the second connecting rod.

[0010] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0011] 1. By adding a buffer device composed of a fixing component, a damper, and a spring at the connection between the first connecting rod and the support rod, the present utility model is beneficial to reducing the impact on the fuselage when the aircraft lands and touches the ground, protecting the fuselage from damage. In addition to absorbing the impact energy, the buffer device can also effectively reduce the vibration of the aircraft during flight and landing, which can improve flight stability, protect on-board equipment, and reduce the fatigue damage of the fuselage structure.

[0012] 2. By adding a support component at the bottom of the first connection kit, the present utility model is beneficial for the aircraft to adapt to more landing surfaces when landing. In daily use, there will always be some special situations where it is too late to find a flat ground for the aircraft to land. The support component can increase the landing support points of the aircraft, making it more difficult for the aircraft to roll over. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 is a schematic structural diagram of the present utility model;

[0014] Figure 2 is a schematic diagram of the bottom of the structure of the present utility model;

[0015] Figure 3 is a schematic sectional view of the structure of the present utility model;

[0016] Figure 4 is a schematic sectional view of the shock absorption device of the structure of the present utility model;

[0017] Figure 5 is the structure of the present utility model Figure 4 enlarged schematic view at A in.

[0018] In the figure: 1. Support component; 2. First connection kit; 3. First connecting rod; 4. Fixing component; 5. Support rod; 6. Second connection kit; 7. Second connecting rod; 8. Damper; 9. Spring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0020] As Figures 1 to 5 shown, the present utility model provides a landing gear for a vertical takeoff and landing aircraft, including a support assembly 1. A connecting kit one 2 is fixedly connected to the upper end of the support assembly 1. A connecting rod one 3 is fixedly sleeved inside the connecting kit one 2. A fixing assembly 4 is fixedly connected to the upper end of the connecting kit one 2. A spring 9 is fixedly connected inside the fixing assembly 4. A damper 8 is fixedly connected to the upper end of the spring 9. A support rod 5 is fixedly connected to the upper end of the damper 8. A connecting kit two 6 is fixedly sleeved on the surface of the support rod 5. A connecting rod two 7 is fixedly connected to the side of the connecting kit two 6.

[0021] By adding a buffer device composed of a fixing assembly 4, a damper 8 and a spring 9 at the connection between the connecting rod one 3 and the support rod 5, it is beneficial to reduce the impact on the fuselage when the aircraft lands and touches the ground, protect the fuselage from damage. In addition to absorbing the impact energy, the buffer device can also effectively reduce the vibration of the aircraft during flight and landing, which can improve flight stability, protect on-board equipment and reduce the fatigue damage of the fuselage structure.

[0022] Among them, the shape of the support assembly 1 is "X", the bottom surface of the support assembly 1 is flat, and the four corners of the support assembly 1 are slightly upturned.

[0023] The "X" shape provides more support landing points, and the upturned corners are beneficial to stability and it is not easy to tip over due to an uneven landing point.

[0024] Among them, the bottom surface of the connecting kit one 2 is a plane, and the upper inclined side of the connecting kit one 2 is a plane.

[0025] It is beneficial to the connection and assembly of the support assembly 1 and the fixing assembly 4 by the connecting kit one 2, and is beneficial to the welding confirmation operation surface.

[0026] Among them, both the front and rear ends of the connecting rod one 3 are upturned, and both the front and rear ends of the connecting rod one 3 are spherical.

[0027] It is beneficial to stabilize the fuselage in case of imbalance when the aircraft falls, and prevent the fuselage from directly hitting the ground and causing damage.

[0028] Among them, the lower end of the support rod 5 is a rectangular block, and the area value of the rectangular block is equal to the area value inside the fixing assembly 4.

[0029] Apply pressure to the damper 8 inside the fixing component 4 through the rectangular block at the lower end of the support rod 5 to ensure the force application area and the stability of the damper 8 and the spring 9.

[0030] Among them, there are two support rods 5. Fixing components 4 are fixed on the surfaces of the front and rear support rods 5. Fixing slots are provided on the surface opposite to the fixing component 4 to connect the second connecting rod 7.

[0031] Enhance the stability of the second connecting rod 7. The fixing slots provided on the surface opposite to the fixing component 4 to connect the second connecting rod 7 facilitate the fixing and control of the position of the second connecting rod 7.

[0032] The working principle and usage process of the present utility model:

[0033] When the aircraft is falling, since it is falling vertically, it is usually necessary to ensure the flatness of the landing surface. If a sudden gust of wind affects the balance of the aircraft during the fall and one side touches the ground first, because the corner edges of the support component 1 are upturned, the support component 1 is beneficial to make the aircraft return to the upright position when it is tilted. The front and rear ends of the first connecting rod 3 are beneficial for preventing foreign objects from hitting the fuselage easily when the aircraft lands, which can effectively protect the fuselage. When the support component 1 lands, the downward gravity during the fall will bounce upward, and at this time, it will impact the fuselage. At this time, the support rod 5 presses the damper 8 downward under the action of gravity, and the damper 8 presses the spring 9 downward, causing the spring 9 to undergo elastic deformation, thereby absorbing the impact energy and protecting the fuselage.

[0034] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0035] Although the embodiments of the present utility model have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present utility model. The scope of the present utility model is defined by the appended claims and their equivalents.

Claims

1. A landing gear for a vertical take-off and landing aircraft, comprising a support assembly (1), characterized in that: The upper end of the support component (1) is fixedly connected to a connecting kit 1 (2), the interior of the connecting kit 1 (2) is fixedly sleeved with a connecting rod 1 (3), the upper end of the connecting kit 1 (2) is fixedly connected to a fixing component (4), the interior of the fixing component (4) is fixedly connected to a spring (9), the upper end of the spring (9) is fixedly connected to a damper (8), the upper end of the damper (8) is fixedly connected to a support rod (5), the surface of the support rod (5) is fixedly sleeved with a connecting kit 2 (6), and the side of the connecting kit 2 (6) is fixedly connected to a connecting rod 2 (7).

2. The landing gear of a vertical take-off and landing aircraft according to claim 1, characterized in that: The support component (1) is in an "X" shape, the bottom surface of the support component (1) is flat, and the four corners of the support component (1) are slightly tilted upwards.

3. The landing gear of a vertical take-off and landing aircraft according to claim 1, characterized in that: The bottom surface of the connection kit one (2) is a plane, and the upper inclined side of the connection kit one (2) is a plane.

4. The landing gear of a vertical take-off and landing aircraft according to claim 1, characterized in that: The front and rear ends of the connecting rod 1 (3) are both raised, and the front and rear ends of the connecting rod 1 (3) are both spherical.

5. The landing gear of a vertical take-off and landing aircraft according to claim 1, characterized in that: The lower end of the support rod (5) is a rectangular block, and the area value of the rectangular block is equal to the area value inside the fixing component (4).

6. The landing gear of a vertical take-off and landing aircraft according to claim 1, characterized in that: There are two support rods (5), and the surfaces of the support rods (5) at the front and rear positions are both fixed with fixing components (4), and the opposite surface of the fixing components (4) is provided with a fixing slot connected to the second connecting rod (7).

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