CN212290320U

CN212290320U - Unmanned aerial vehicle undercarriage and unmanned aerial vehicle thereof

Info

Publication number: CN212290320U
Application number: CN202020117794.0U
Authority: CN
Inventors: 胡晓畑; 刘琛; 陈玮宇
Original assignee: Hangzhou Q Fly Uav Intelligent Technology Co ltd
Current assignee: Hangzhou Q Fly Uav Intelligent Technology Co ltd
Priority date: 2020-01-18
Filing date: 2020-01-18
Publication date: 2021-01-05
Anticipated expiration: 2030-01-18

Abstract

The utility model discloses an unmanned aerial vehicle undercarriage and an unmanned aerial vehicle thereof, which comprises a first supporting leg, a second supporting leg and an underframe; the first leg comprises a first upper supporting part and a first lower supporting part; the first upper supporting part and the first lower supporting part form a first obtuse angle and semi-surround the shell, and the upper end of the first upper supporting part is provided with a first upper connecting surface; the lower end of the first lower supporting part is provided with a first lower connecting surface. The second support leg comprises a second upper support part and a second lower support part; the second upper supporting part and the second lower supporting part form a second obtuse angle and semi-surround the shell, and the upper end of the second upper supporting part is provided with a second upper connecting surface; the lower end of the second lower supporting part is provided with a second lower connecting surface. The first obtuse opening is opposite to the second obtuse opening; one end of the underframe is connected with the first lower connecting surface; the other end of the underframe is connected with the second lower connecting surface. The landing gear is convenient to transport and light in weight, plays a role in reducing the landing inertia of the airplane step by step in the landing process of the airplane, and is safer in flexible landing.

Description

Unmanned aerial vehicle undercarriage and unmanned aerial vehicle thereof

Technical Field

The utility model relates to an unmanned aerial vehicle accessory, concretely relates to unmanned aerial vehicle undercarriage and unmanned aerial vehicle thereof.

Background

Unmanned aerial vehicle's undercarriage among the prior art adopts an organic whole to be the rigid support mostly, and integrative rigid support has following shortcoming:

(1) the whole volume is large in the transportation process, and the transportation is inconvenient;

(2) the rigid support enables the unmanned aerial vehicle to easily overturn when landing in an uneven field, and damages to the unmanned aerial vehicle are caused when the unmanned aerial vehicle is serious; moreover, due to the lack of buffering of the rigid support, damage to precision equipment on the unmanned aerial vehicle can be caused even if the rigid support is normally landed; especially for the plant protection unmanned aerial vehicle, the landing field is uneven;

(3) some rigid support directly adopt the metal frame of stainless steel, and metal support weight is heavy, increases the unmanned aerial vehicle degree of difficulty of taking off, reduces unmanned aerial vehicle bearing capacity.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an unmanned aerial vehicle undercarriage can solve one or more among the above-mentioned technical problem.

In order to achieve the above object, the present invention provides the following technical solutions:

unmanned aerial vehicle undercarriage, its characterized in that: comprises a first supporting leg, a second supporting leg and a bottom frame; the first leg comprises a first upper supporting part and a first lower supporting part; the first upper supporting part and the first lower supporting part form a first obtuse angle and semi-surround the shell, and the upper end of the first upper supporting part is provided with a first upper connecting surface; the lower end of the first lower supporting part is provided with a first lower connecting surface. The second support leg comprises a second upper support part and a second lower support part; the second upper supporting part and the second lower supporting part form a second obtuse angle and semi-surround the shell, and the upper end of the second upper supporting part is provided with a second upper connecting surface; the lower end of the second lower supporting part is provided with a second lower connecting surface. The first obtuse opening is opposite to the second obtuse opening; one end of the underframe is connected with the first lower connecting surface; the other end of the underframe is connected with the second lower connecting surface.

In the utility model, the first support leg and the second support leg are both arranged in an obtuse angle shape, wherein the first support leg is used as a front support leg, the first lower support part and the horizontal plane have an included angle of about 70 degrees, and the optimal angle between the first upper support part and the first lower support part is about 120 degrees; the second support leg is used as a rear support leg, an included angle of about 120 degrees is formed between the second lower support part and the vertical plane, and the optimal angle between the second upper support part and the second lower support part is about 110 degrees; the obtuse angle openings of the two support legs are opposite, and the first support leg and the second support leg which are at an obtuse angle are elastically deformed to buffer the inertia of the airplane in the landing process of the airplane; in addition, because the angles of the first support leg and the second support leg are different, the deformation generated in the buffering process is also different, so that the inertia is not reduced to the minimum at one time, and the flexible landing for gradually reducing the inertia of the landing of the airplane is realized by the aid of graded buffering.

The utility model discloses in, for reduce weight with landing leg (first landing leg and second landing leg) preparation for the casing that partly surrounds, when guaranteeing certain intensity, the effectual quality that has reduced.

Further: the first supporting leg and the second supporting leg are made of plastics, specifically carbon fiber reinforced nylon composite plastics, and the underframe is made of carbon fibers.

According to different requirements of the landing gear, different parts of the landing gear are made of different materials, and the support legs are mainly used for reducing impact, so that elastic plastic is adopted, and the plastic is light and easy to process and manufacture; a chassis is required to be high in strength and light in weight, and thus carbon fiber is used. The whole weight of undercarriage is greatly reduced, and the bearing capacity of the unmanned aerial vehicle is indirectly improved.

Further: the first obtuse angle is greater than the second obtuse angle; the vertex of the first obtuse angle is opposite to the second upper supporting part; the vertex of the second obtuse angle is opposite to the first lower support part.

The first obtuse angle and the second obtuse angle enable the deformation of the first supporting leg and the deformation of the second supporting leg to be different, grading buffering is achieved, and impact of landing is reduced step by step.

Further: a plurality of parallel transverse ribs are arranged in the shell from top to bottom, and the transverse ribs are internally tangent to the shell; a plurality of parallel vertical ribs are arranged between the transverse ribs; the transverse ribs and the vertical ribs divide the interior of the shell into a multi-lattice structure. The strength is increased, the stress strength is improved, and the service life is prolonged.

Further: the transverse ribs in the first supporting leg are pentagonal and gradually reduce from top to bottom along the first supporting leg.

Further: the transverse ribs in the second upper supporting part are pentagonal, and the transverse ribs in the second lower supporting part are triangular.

The cross ribs of the pentagon are mainly used as supports in the first supporting leg and the second supporting leg, so that transition from the pentagon to the trilateral is natural when the diameter of the first supporting leg or the second supporting leg is changed, and stress concentration cannot occur to destroy the overall strength.

Further: further comprising a connector comprising a first inlet for connecting the first leg or the second leg; a second inlet for connecting to a chassis; and a through hole; the first inlet is formed in the upper surface of the connecting piece; a second inlet is formed in the side face of the connecting piece; the through hole is a countersunk through hole which faces upwards from the lower surface of the connecting piece.

The connecting piece plays the intensity of protection connection position, avoids the junction too thin and damaged by the striking.

Including any of the above-mentioned unmanned aerial vehicle of unmanned aerial vehicle undercarriage, its characterized in that: the landing gear is installed below the engine body.

The unmanned aerial vehicle adopting the undercarriage is light in weight, heavy in load and convenient to transport.

The technical effects of the utility model are that:

(1) the landing gear is divided into three independent parts, and can be split into three parts in the transportation process, so that the transportation space can be more reasonably utilized compared with an integral structure;

(2) in the utility model, except that the first support leg and the second support leg are respectively made of elastic materials and the bottom frame is made of elastic materials, the shapes of the first support leg and the second support leg can realize elastic landing, and simultaneously, certain strength is kept, so that the use is safer;

(3) the first supporting leg and the second supporting leg are made of plastic materials, and the underframe is made of carbon fiber; the weight of undercarriage has been reduced on the whole, indirect improvement unmanned aerial vehicle's bearing capacity, be particularly useful for plant protection unmanned aerial vehicle and use.

Drawings

The accompanying drawings, which form a part of the present application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.

In the drawings:

fig. 1 is a schematic diagram of the overall structure of the present invention;

FIG. 2 is a schematic top view of FIG. 1;

FIG. 3 is a schematic left side view of FIG. 1;

FIG. 4 is a schematic partial exploded view of FIG. 1;

FIG. 5 is a schematic structural view of the first leg;

FIG. 6 is a cross-sectional schematic view of the first leg;

FIG. 7 is a schematic structural view of a second leg;

FIG. 8 is a cross-sectional view of the second upper support section of FIG. 5;

FIG. 9 is a cross-sectional view of the second lower support in FIG. 5;

FIG. 10 is a schematic view of the structure of the connector;

fig. 11 is a schematic structural view of the present invention mounted on an aircraft.

Detailed Description

The invention will be described in detail with reference to the drawings and specific embodiments, wherein the exemplary embodiments and the description are only intended to explain the invention, but not to limit the invention in a proper manner.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

As shown in fig. 1-10, the landing gear of the unmanned aerial vehicle comprises a first supporting leg 1, a second supporting leg 2 and an underframe 3; the first leg comprises a first upper support part 11 and a first lower support part 12; the first upper supporting part and the first lower supporting part form a first obtuse angle semi-enclosed shell, and the upper end of the first upper supporting part is provided with a first upper connecting surface 111; the first lower support portion has a first lower connection surface 121 at a lower end thereof.

The second leg 2 comprises a second upper support part 21 and a second lower support part 22; the second upper supporting part and the second lower supporting part form a second obtuse angle semi-enclosed shell, and the upper end of the second upper supporting part is provided with a second upper connecting surface 211; the lower end of the second lower supporting part is provided with a second lower connecting surface 221.

A plurality of parallel transverse ribs 5 are arranged in the shell from top to bottom, and the transverse ribs are internally tangent to the shell; a plurality of parallel vertical ribs 6 are arranged between the transverse ribs; the transverse ribs and the vertical ribs divide the interior of the shell into a multi-lattice structure.

As shown in fig. 5-6; the transverse ribs in the first supporting leg are pentagonal and gradually reduce from top to bottom along the first supporting leg.

As shown in fig. 8, the transverse ribs in the second upper support part are pentagonal, and as shown in fig. 9, the transverse ribs in the second lower support part are triangular.

The first obtuse opening is opposite to the second obtuse opening, wherein the first obtuse angle is larger than the second obtuse angle; the vertex of the first obtuse angle is opposite to the second upper supporting part; the vertex of the second obtuse angle is opposite to the first lower support part.

As shown in fig. 10, further comprising a connecting member, said connecting member 4 comprising a first inlet 41 for connecting a first leg or a second leg; a second inlet 42 for connecting to the chassis; and a through hole 43; the first inlet 41 is opened on the upper surface of the connecting piece 4; a second inlet 42 is arranged on the side surface of the connecting piece 4; the through hole 43 is a countersunk through hole that faces upward from the lower surface of the connecting member 4.

The first supporting leg and the second supporting leg are made of plastics, and the underframe is made of carbon fibers.

In the utility model, the first support leg and the second support leg are semi-enclosed shells, thus effectively reducing the mass; transverse and longitudinal ribs are arranged in the shell to improve the strength; and through the first landing leg and the second landing leg of different angles, let unmanned aerial vehicle in the hierarchical buffering of inertia of landing in-process, effectually avoided hard landing, guarantee the security that the aircraft landed.

As shown in fig. 11, the unmanned aerial vehicle including the landing gear of the unmanned aerial vehicle includes a body and a landing gear, wherein the landing gear is installed below the body.

Adopt the unmanned aerial vehicle of above-mentioned undercarriage, the inertia of buffering aircraft landing that not only can be fine also can reduce the whole weight of aircraft simultaneously, improves the load, is particularly suitable for plant protection unmanned aerial vehicle to use.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. Unmanned aerial vehicle undercarriage, its characterized in that: comprises a first supporting leg, a second supporting leg and a bottom frame;

the first leg comprises a first upper supporting part and a first lower supporting part; the first upper supporting part and the first lower supporting part form a first obtuse angle and semi-surround the shell, and the upper end of the first upper supporting part is provided with a first upper connecting surface; the lower end of the first lower supporting part is provided with a first lower connecting surface;

the second support leg comprises a second upper support part and a second lower support part; the second upper supporting part and the second lower supporting part form a second obtuse angle and semi-surround the shell, and the upper end of the second upper supporting part is provided with a second upper connecting surface; the lower end of the second lower supporting part is provided with a second lower connecting surface;

the first obtuse opening is opposite to the second obtuse opening; one end of the underframe is connected with the first lower connecting surface; the other end of the underframe is connected with the second lower connecting surface;

a plurality of parallel transverse ribs are arranged in the shell from top to bottom, and the transverse ribs are internally tangent to the shell; a plurality of parallel vertical ribs are arranged between the transverse ribs; the transverse ribs and the vertical ribs divide the interior of the shell into a multi-lattice structure.

2. An unmanned landing gear according to claim 1, wherein: the first supporting leg and the second supporting leg are made of plastics, and the underframe is made of carbon fibers.

3. An unmanned landing gear according to claim 1, wherein: the first obtuse angle is greater than the second obtuse angle; the vertex of the first obtuse angle is opposite to the second upper supporting part; the vertex of the second obtuse angle is opposite to the first lower support part.

4. An unmanned landing gear according to claim 1, wherein: the transverse ribs in the first supporting leg are pentagonal and gradually reduce from top to bottom along the first supporting leg.

5. An unmanned landing gear according to claim 1, wherein: the transverse ribs in the second upper supporting part are pentagonal, and the transverse ribs in the second lower supporting part are triangular.

6. An unmanned landing gear according to claim 1, wherein: further comprising a connector comprising a first inlet for connecting the first leg or the second leg; a second inlet for connecting to a chassis; and a through hole; the first inlet is formed in the upper surface of the connecting piece; a second inlet is formed in the side face of the connecting piece; the through hole is a countersunk through hole which faces upwards from the lower surface of the connecting piece.

7. A drone including a drone landing gear according to any one of claims 1 to 6, characterised in that: the landing gear is installed below the engine body.