Undercarriage buffer of unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle undercarriage buffer which comprises a buffer supporting column module, a damping module and an inflation valve. The buffering supporting column module comprises an outer cylinder end cover, an outer cylinder, a piston rod and a lower shaft sleeve, wherein the outer cylinder comprises an outer cylinder upper section and more than one outer cylinder lengthened section; one end of the outer cylinder lengthened section is fixed with the outer cylinder upper section through sealing threads, and the other end of the outer cylinder lengthened section is fixed with the outer cylinder end cover through sealing threads; the lower shaft sleeve and the upper section of the outer cylinder are tightly assembled together through a sealing ring I. The piston rod is slidably connected with the lower shaft sleeve through a plurality of sealing rings II. A damping module is fixed on an opening, located at the inner end of the outer cylinder, of the piston rod in a threaded mode; the inner cavity of the outer cylinder and the inner cavity of the piston rod are filled with hydraulic oil and nitrogen which are communicated with each other. The modular design is adopted, the aspects of manufacturing, maintaining, upgrading, adapting to different machine types and the like are flexible, the universality is high, the production cost is low, the production efficiency is high, maintaining and replacing are easy and convenient, and the cost is low.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) landing gear manufacturing technology, and relates to a UAV landing gear buffer. Background Technology

[0002] Landing gear is a specialized device used by aircraft for taxiing and parking. It needs to withstand the static and dynamic loads generated by the aircraft's contact with the ground, serving to support and protect the airframe. Landing gear relies on shock absorbers to absorb landing impact energy, and its performance has a decisive impact on the aircraft's takeoff and landing performance. Most aircraft use hydrant-pneumatic shock absorbers, which have the highest efficiency and best power absorption capacity among all types of shock absorbers. However, the existing structures of hydrant-pneumatic shock absorbers are mostly adapted to large aircraft and not suitable for small unmanned aerial vehicles (UAVs).

[0003] In recent years, drones have experienced explosive growth and are widely used in various fields. While there are many models available, existing drone landing gear buffer structures are often integrated designs, leading to numerous inconveniences in manufacturing, maintenance, upgrades, and adaptation to different aircraft models. When a component fails, the entire buffer needs to be disassembled and repaired, resulting in lengthy and costly repairs. Adjusting buffer parameters or upgrading functions for different aircraft models often requires redesigning the entire buffer structure, lacking flexibility and versatility. Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned problems in the prior art and provide a drone landing gear buffer. This buffer has a modular design, which is flexible and versatile in terms of manufacturing, maintenance, upgrading and adaptation to different models. It has low production cost, high production efficiency, and simple, convenient and low cost for maintenance and replacement.

[0005] To achieve the above objectives, the technical solution of the present invention is: a UAV landing gear buffer, comprising a buffer support module, a damping module, and an inflation valve; the buffer support module comprises an outer cylinder, an outer cylinder end cap, a piston rod, and a lower bushing; the outer cylinder comprises an upper section and one or more extended sections; when there are two or more extended sections, each extended section is sequentially and threadedly fixed together; one end of the extended section or the extended section fixed together is threadedly fixed to the upper section of the outer cylinder, and the other end is threadedly fixed to the end cap of the outer cylinder; the lower bushing is tightly assembled with the upper section of the outer cylinder through a sealing ring I, and the piston rod is slidably connected to the lower bushing through multiple sealing rings II; an inflation valve is threadedly fixed to the piston rod at the outer end of the outer cylinder, and a damping module is threadedly fixed to the piston rod at the inner end of the outer cylinder; the inner cavity of the outer cylinder and the inner cavity of the piston rod of the buffer support module are filled with interconnected hydraulic oil and nitrogen.

[0006] More preferably, the damping module includes a damping valve and a bolt; the damping valve is a plug with an external thread matching the internal thread of the piston rod end, and the plug has a central hole with an internal threaded hole and an external oil passage hole; the bolt is threaded into the threaded hole of the plug, and has an oil passage hole perpendicularly communicating with the central hole of the plug. The damping module is threadedly fixed to the piston rod, making it easy to disassemble, maintain, and replace, which is simple, convenient, and low-cost. Preferably, an electric regulating valve capable of adjusting the size of the oil passage hole is installed in the oil passage hole of the bolt. The electric regulating valve adopts an electric control method and can automatically adjust the size of the damping hole according to the landing status of the aircraft based on preset control logic.

[0007] More preferably, the inflation valve includes an end plug, an end cap, and a one-way valve, all having an external thread that matches the internal thread of the piston rod end. The end plug has a central oil hole, within which the one-way valve is installed. The end plug is threadedly and securely fixed to the piston rod, and the end cap is detachably fixed to the end plug. The inflation valve injects appropriate amounts of hydraulic oil and nitrogen into the inner cavity of the outer cylinder of the buffer support module and the inner cavity of the piston rod. The type of hydraulic oil and the gas pressure are both adjustable.

[0008] More preferably, a dustproof ring is also installed between the end of the lower bushing and the piston rod.

[0009] The beneficial effects of this invention compared to existing technologies are as follows: This invention features a modular structure, allowing each module to be manufactured, tested, and maintained independently. This improves production efficiency and product quality while reducing production costs. During landing gear maintenance, if a module malfunctions, the corresponding module can be quickly repaired or replaced, significantly shortening aircraft downtime for maintenance. When upgrading aircraft or adapting to different models, only adjustments or replacements to the corresponding structure are needed, improving the versatility and flexibility of the buffer and reducing R&D and maintenance costs. This invention can be widely applied to UAV landing gear, especially suitable for small and medium-sized UAV landing gear. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the internal structure of the present invention. Detailed Implementation

[0011] The present invention will now be further described with reference to the accompanying drawings and specific embodiments.

[0012] like Figure 1As shown, this embodiment includes a buffer support module, a damping module, and an inflation valve 6. The buffer support module includes an outer cylinder, an outer cylinder end cap 1, a piston rod 5, and a lower bushing 4. The outer cylinder includes an upper section 3 and one or more extended sections 2. When there are two or more extended sections 2, each extended section 2 is sequentially fixed together by a sealing gasket 7. One end of the extended section 2 or the extended sections 2 fixed together is fixed to the upper section 3 by a sealing gasket 7, and the other end is fixed to the outer cylinder end cap 1 by a sealing gasket 7. The lower bushing 4 is tightly assembled with the upper section 3 by a sealing ring I 10, and the piston rod 5 is slidably connected to the lower bushing 4 by multiple sealing rings II 11 (two in this embodiment). In this embodiment, a dustproof ring 12 is also installed between the end of the lower bushing 4 and the piston rod 5. The piston rod 5 is threadedly sealed with an inflation valve 6 at the outer end of the outer cylinder, and a damping module is threadedly fixed at the inner end of the outer cylinder. The inner cavity of the outer cylinder and the inner cavity of the piston rod of the buffer support module are filled with interconnected hydraulic oil and nitrogen.

[0013] In this embodiment, the damping module includes a damping valve 8 and a bolt 9. The damping valve 8 is a plug with an external thread that matches the internal thread at the end of the piston rod 5. The plug has a central hole 81 with an internal threaded hole and an external oil passage hole. The bolt 9 is threaded into the threaded hole of the plug and has an oil passage hole 91 that is perpendicularly connected to the central hole 81 of the plug. The damping module is threadedly fixed to the piston rod 5, making it easy to disassemble, maintain, and replace, which is simple, convenient, and low-cost. Preferably, an electric regulating valve capable of adjusting the size of the oil passage hole 91 is installed in the oil passage hole 91 of the bolt 9. The electric regulating valve adopts an electric control method and can automatically adjust the size of the damping hole according to the landing status of the aircraft based on preset control logic.

[0014] In this embodiment, the inflation valve 6 includes an end plug 61 with an external thread matching the internal thread of the piston rod 5, an end cap 62, and a one-way valve 63. The end plug 61 has a central oil hole, and the one-way valve 63 is installed in the central oil hole. The end plug 61 is threadedly and sealed to the piston rod 5, and the end cap 62 is detachably fixed to the end plug 61. The inflation valve 6 injects appropriate amounts of hydraulic oil and nitrogen into the inner cavity of the outer cylinder of the buffer support module and the inner cavity of the piston rod. The type of hydraulic oil and the gas pressure are adjustable.

[0015] During use, the outer cylinder of this invention is mounted on the landing gear outer cylinder, and the piston rod 5 is connected to the landing gear wheels. When the aircraft lands, the damper begins to work, the piston rod 5 is compressed inside the outer cylinder, and hydraulic oil and gas work together to buffer the impact force. For damping modules with electric regulating valves, the size of the damping orifice can be automatically adjusted according to parameters such as the impact velocity at the moment of landing and the aircraft landing weight, thereby controlling the compression and damping force of the damper.

[0016] During maintenance, if problems such as hydraulic oil leakage or piston rod wear occur in the buffer support module, the parts in the buffer support module can be disassembled individually for repair and replacement.

[0017] When it is necessary to adjust the landing gear's capacity absorption to adapt to different flight missions, different specifications of damping adjustment modules can be easily replaced.

[0018] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A landing gear buffer for an unmanned aerial vehicle (UAV), characterized in that: The system includes a buffer support module, a damping module, and an inflation valve. The buffer support module includes an outer cylinder, an outer cylinder end cap, a piston rod, and a lower bushing. The outer cylinder includes an upper section and one or more extended sections. When there are two or more extended sections, each extended section is sequentially and threadedly fixed together. One end of the extended section or the extended section fixed together is threadedly fixed to the upper section of the outer cylinder, and the other end is threadedly fixed to the end cap. The lower bushing is tightly fitted to the upper section of the outer cylinder via a sealing ring I, and the piston rod is slidably connected to the lower bushing via multiple sealing rings II. An inflation valve is threadedly fixed to the piston rod at the outer end of the outer cylinder, and a damping module is threadedly fixed to the piston rod at the inner end of the outer cylinder. The inner cavity of the outer cylinder and the inner cavity of the piston rod of the buffer support module are filled with interconnected hydraulic oil and nitrogen.

2. The UAV landing gear buffer according to claim 1, characterized in that: The damping module includes a damping valve and bolts; the damping valve is a plug with an external thread that matches the internal thread of the piston rod end, and the plug has an internal vertically connected oil passage hole in the center.

3. The UAV landing gear buffer according to claim 2, characterized in that: An electric regulating valve capable of adjusting the size of the oil passage hole is installed inside the bolt.

4. The UAV landing gear buffer according to claim 1, 2, or 3, characterized in that: The inflation valve includes an end plug, an end cap, and a one-way valve, all having an external thread that matches the internal thread of the piston rod end. The end plug has a central oil hole, and the one-way valve is installed inside the central oil hole. The end plug is threadedly and fixedly fixed to the piston rod, and the end cap is detachably fixed to the end plug.

5. The UAV landing gear buffer according to claim 4, characterized in that: A dustproof ring is also installed between the end of the lower bushing and the piston rod.

6. The UAV landing gear buffer according to claim 1, 2, or 3, characterized in that: A dustproof ring is also installed between the end of the lower bushing and the piston rod.

Images