CN114476034A - Buffering pillar, undercarriage and unmanned aerial vehicle - Google Patents

Abstract

The invention relates to a buffer strut, a landing gear and an unmanned aerial vehicle, wherein the buffer strut comprises an inner cylinder, an outer cylinder, a piston rod, a fixed damping unit and a floating damping unit, and the inner cylinder is arranged in the outer cylinder , the fixed damping unit and the floating damping unit are arranged in the inner cylinder, the piston rod is arranged in the outer cylinder, one end abuts the fixed damping unit, and the other end is in contact with the wheel fork assembly connect. The structure is suitable for the design of the buffer struts of small unmanned aerial vehicles, which can improve the buffer efficiency, reduce the landing rebound, and reduce the difficulty and cost of manufacturing.

Description

A buffer strut, landing gear and unmanned aerial vehicle

technical field

The invention relates to the field of unmanned aerial vehicles, in particular to a buffer strut, a landing gear and an unmanned aerial vehicle.

Background technique

In the UAV wheeled take-off and landing technology, the landing gear is an important part of the aircraft structure. It mainly supports the stop load of the UAV, and the dynamic load during roll-off and roll-down landing. Among them, the landing gear buffer struts mainly play a supporting role, and at the same time reduce aircraft vibration and landing overload.

At present, most UAV landing gear adopts oil and gas buffer structure, among which oil needle buffer structure and fixed oil air buffer structure are more common in landing gear buffer struts. However, the manufacturing process of oil needles is complex, requiring high assembly precision, and there is no good detection method after assembly, which is prone to eccentricity or even jamming, which greatly reduces the buffer performance; and the buffer structure of the fixed oil hole type is found in the working process The anti-travel damping matching is not good, the buffering efficiency is low, and the rebound is serious when the design is unreasonable.

SUMMARY OF THE INVENTION

The purpose of the present invention is to solve the shortcomings in the prior art, and the present invention aims to provide a buffer strut, a landing gear and an unmanned aerial vehicle for solving the above problems in the prior art.

The above technical purpose of the present invention will be achieved through the following technical solutions.

A buffer strut for unmanned aerial vehicles, the buffer strut includes an inner cylinder, an outer cylinder, a reciprocating motion unit, a fixed damping unit and a floating damping unit,

Wherein, the inner cylinder is arranged in the outer cylinder, the fixed damping unit and the floating damping unit are arranged in the inner cylinder, the reciprocating motion unit is arranged in the outer cylinder, and wherein the reciprocating motion One end of the unit is abutted against the fixed damping unit, and the other end of the reciprocating unit is connected to the wheel fork assembly.

According to the above aspect and any possible implementation, an implementation is further provided, wherein the fixed damping unit is a fixed damping block or a fixed damping plate; the floating damping unit is a floating damping block or a floating damping plate.

According to the above-mentioned aspect and any possible implementation manner, an implementation manner is further provided, wherein the outer cylinder and the inner cylinder are connected by interference through a pin provided at the inner top of the outer cylinder.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein a plurality of sealing grooves are formed on the upper part of the inner cylinder, and a plurality of sealing rings are arranged in the sealing grooves.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein a plurality of oil passage holes are provided on the inner cylinder.

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein a central damping hole is provided at a central position of the floating damping unit, and side damping holes are provided around the central damping hole.

In the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the floating damping unit is arranged at the lower part of the inner cylinder and is in interference fit with the inner cylinder, and the fixed damping unit is arranged at the lower part of the inner cylinder. between the floating damping unit and the reciprocating unit.

The present invention also provides a landing gear, the landing gear includes the buffer strut described in the present invention, and also includes an anti-twist arm assembly, a turning actuating device, a wheel fork assembly, and a wheel and tire assembly; wherein the anti-twist arm assembly The arm assembly, the turning actuating device and the wheel fork assembly are arranged on the buffer strut, the anti-twist arm assembly is connected with the turning actuating device and the wheel fork assembly, and the wheel fork assembly is connected with the wheel and the tire assembly .

According to the above aspect and any possible implementation manner, an implementation manner is further provided, wherein the upper end of the buffer strut is connected to the unmanned aerial vehicle, and the lower end of the buffer strut is connected to the wheel fork assembly.

The present invention also provides an unmanned aerial vehicle comprising the landing gear of the present invention.

Beneficial technical effects of the present invention

The buffer strut provided by the embodiment of the present invention is used for unmanned aerial vehicles. The buffer strut includes an inner cylinder, an outer cylinder, a reciprocating motion unit, a fixed damping unit and a floating damping unit, wherein the inner cylinder is arranged on the outer cylinder. Inside the cylinder, the fixed damping unit and the floating damping unit are arranged in the inner cylinder, the reciprocating motion unit is arranged in the outer cylinder, one end of which is abutted against the fixed damping unit, and the other end is connected to the wheel fork assembly , The structure is suitable for the use of small unmanned aerial vehicles, which can improve the buffering efficiency, reduce the landing rebound, and reduce the difficulty and cost of manufacturing.

Description of drawings

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein:

1 is a three-dimensional schematic view of a landing gear in an embodiment of the present invention;

2 is a schematic cross-sectional view of a buffer strut in an embodiment of the present invention;

FIG. 3 is a schematic diagram of the damping hole in the return stage of the buffer strut in the embodiment of the present invention;

FIG. 4 is a schematic diagram of the damping hole in the return stage of the buffer strut in the embodiment of the present invention;

5 is a schematic diagram of the installation of the fixed damping block and the floating damping block in the inner cylinder according to the embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a floating damping block in an embodiment of the present invention.

Detailed ways

In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will describe in detail with reference to the accompanying drawings and specific embodiments, but the embodiments of the present invention are not limited thereto.

As shown in FIG. 2, the buffer strut in the present invention is used for unmanned aerial vehicles, and the buffer strut includes an inner cylinder 6, an outer cylinder 5, a reciprocating motion unit, a fixed damping unit and a sliding damping unit,

The inner cylinder 6 is arranged in the outer cylinder 5, the fixed damping unit and the sliding damping unit are arranged in the inner cylinder 6, the reciprocating unit is realized by the piston rod 8, and the piston The rod 8 is arranged in the outer cylinder 5, one end of which is abutted against the fixed damping unit, and the other end is connected to the wheel assembly of the fork.

Preferably, in the embodiment of the present invention, the fixed damping unit is a fixed damping block 10 or a fixed damping plate; the sliding damping unit is a floating damping block 11 or a floating damping plate.

Preferably, in the embodiment of the present invention, the outer cylinder 5 and the inner cylinder 6 of the buffer strut are connected by the interference fit of the pin 7, the upper part of the inner cylinder 6 is separated with a sealing groove, and a sealing ring 12 is installed inside the sealing groove to seal Oil and gas effect, one end of the piston rod 8 is inserted between the outer cylinder 5 and the inner cylinder 6, and the other end is connected to the wheel fork assembly, the piston rod 8 plays the role of compression and shock absorption; the piston rod 8 is fixed to the outer cylinder through the lower sealing ring 9 In the cylinder 5, the lower sealing ring 9 is specifically arranged between the inner and outer cylinders, and plays the role of sealing and guiding the piston rod 8, wherein the outer side of the lower sealing ring 9 is equipped with a sealing ring 12 to realize the static sealing of the lower half of the landing gear; the lower sealing ring 9. The inner side is equipped with a sealing ring 12 to realize the dynamic sealing of the piston rod 8, and each sealing ring 12 is provided with two.

Preferably, as shown in FIG. 5 , in the embodiment of the present invention, the floating damping block 11 is arranged at the lower part of the inner cylinder 6 and has an interference fit with the inner cylinder 6 , and the fixed damping block 10 is arranged on the inner cylinder 6 . Between the floating damping block 11 and the piston rod 8 , a plurality of oil passage holes are provided on the side wall of the inner cylinder 6 , and the fixed damping block 10 is threadedly connected to the bottom of the inner cylinder 6 . Due to the limitation of the fixed damping block 10 , the floating damping block 11 can only move radially in a small range in the inner cylinder 6 . The floating damping block 11 and the fixed damping block 10 play a buffering role together.

Preferably, as shown in FIG. 6 , in the embodiment of the present invention, the floating damping block 11 is provided with a central damping hole at its central position, and side damping holes are provided around the central damping hole. and the diameter of the side damping holes are adjusted according to the weight of the drone; the central damping hole and the side damping holes play a damping role together with the fixed damping block 10 in the piston rod compression stage; in the piston rod 8 rebound stage, only the central damping The holes and the fixed damping block 10 work, but the side damping holes do not.

When the buffer strut is compressed, the hydraulic oil in the inner cavity of the piston rod 8 passes through the fixed damping block 10, and then squeezes into the air cavity in the outer cylinder 5 through the central damping hole and the side damping holes in the floating damping block 11. As shown in Figure 3;

During the rebound stage after the landing gear has landed, the high-pressure nitrogen in the outer cylinder 5 presses the hydraulic oil into the oil cavity at the lower part of the piston rod 8 through the central damping hole in the floating damping block 11. At this time, the side of the floating damping block 11 The damping hole is closed, which plays the role of reverse cut-off and solves the problem of large rebound force and too fast rebound, as shown in Figure 3 and Figure 4.

Preferably, as shown in FIG. 1 , the present invention also provides a landing gear, the landing gear includes the buffer strut of the present invention, an anti-twist arm assembly 2 , a turning actuating device 1 , a wheel fork assembly 3 and a wheel assembly 4 ; wherein The anti-twist arm assembly 2, the turning actuating device 1 and the wheel fork assembly 3 are arranged on the buffer strut, and the anti-twist arm assembly 2 is connected to the turning actuating device 1 and the wheel fork assembly 3, and the wheel The fork assembly 3 is connected to the wheel assembly 4, the upper end of the buffer strut is connected to the fuselage assembly of the UAV, and the other end is connected to the wheel fork assembly 3. This structure is suitable for the design of the buffer strut of the small UAV and can improve the buffering effect. At the same time, the landing rebound is reduced, and the manufacturing difficulty and cost are reduced.

The foregoing description shows and describes several preferred embodiments of the present invention, but as previously mentioned, it should be understood that the present invention is not limited to the form disclosed herein, and should not be construed as an exclusion of other embodiments, but may be used in various and other combinations, modifications, and environments, and can be modified within the scope of the present application contemplated by the above teachings or skill or knowledge in the relevant field. However, modifications and changes made by those skilled in the art do not depart from the spirit and scope of the present invention, and should all fall within the protection scope of the appended claims of the present invention.

Claims (10)

1. A buffer strut, characterized in that the buffer strut comprises an inner cylinder, an outer cylinder, a reciprocating motion unit, a fixed damping unit and a floating damping unit, Wherein, the inner cylinder is arranged in the outer cylinder, the fixed damping unit and the floating damping unit are arranged in the inner cylinder, the reciprocating motion unit is arranged in the outer cylinder, and wherein the reciprocating motion One end of the unit is abutted against the fixed damping unit, and the other end of the reciprocating unit is connected with the wheel assembly of the wheel fork. 2 . The buffer strut according to claim 1 , wherein the fixed damping unit is a fixed damping block or a fixed damping plate; and the floating damping unit is a floating damping block or a floating damping plate. 3 . 3 . The buffer strut according to claim 1 , wherein the outer cylinder and the inner cylinder are connected by interference through pins provided at the inner top of the outer cylinder. 4 . 4 . The buffer strut according to claim 1 , wherein a plurality of sealing grooves are formed in the upper part of the inner cylinder, and a plurality of sealing rings are arranged in the sealing grooves. 5 . 5 . The buffer strut according to claim 1 , wherein a plurality of oil passage holes are provided on the side wall of the inner cylinder. 6 . 6 . The buffer strut according to claim 1 , wherein a central damping hole is provided at a central position of the floating damping unit, and a plurality of side damping holes are provided around the central damping hole. 7 . 7 . The buffer strut according to claim 1 , wherein the floating damping unit is arranged at the lower part of the inner cylinder, and has an interference fit with the inner cylinder, and the fixed damping unit is arranged at the floating damping unit. 8 . between the unit and the reciprocating unit. 8. A landing gear, characterized in that the landing gear comprises the buffer strut according to any one of claims 1-7, and further comprises an anti-twist arm assembly, a turning actuating device, a wheel fork assembly, and wheels and tires assembly; wherein the anti-twist arm assembly, the turning actuating device and the wheel fork assembly are arranged on the buffer strut, the anti-twist arm assembly is connected to the turning actuating device and the wheel fork assembly, and the wheel fork assembly is connected The wheel and tire assembly. 9 . The landing gear according to claim 8 , wherein the upper end of the buffer strut is connected to the unmanned aerial vehicle, and the lower end of the buffer strut is connected to the wheel fork assembly. 10 . 10. An unmanned aerial vehicle, wherein the unmanned aerial vehicle comprises the landing gear of any one of claims 8-9.

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