CN209988101U

CN209988101U - Multi-rotor unmanned aerial vehicle

Info

Publication number: CN209988101U
Application number: CN201920249574.0U
Authority: CN
Inventors: 陈豹
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-02-27
Filing date: 2019-02-27
Publication date: 2020-01-24
Anticipated expiration: 2029-02-27

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to many rotor unmanned aerial vehicle. Including fuselage, horn and rotor, the one end of horn connect in the fuselage, the rotor sets up the other end of horn, the cross-sectional shape of horn is the rectangle. According to the utility model discloses many rotor unmanned aerial vehicle adopts the horn of cross sectional shape for the rectangle, and it is compared in the horn of cross sectional shape for circular shape conventional structure, has less amount of deflection under the same materials, and consequently moment resistance ability is stronger, consequently, improves the cross sectional shape of horn into the rectangle by circular, is favorable to reducing the materials of horn structure to reduce many rotor unmanned aerial vehicle's empty aircraft weight, and then promotes many rotor unmanned aerial vehicle's load and duration.

Description

Multi-rotor unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to many rotor unmanned aerial vehicle.

Background

With the development of the unmanned aerial vehicle technology, the unmanned aerial vehicle has more and more important functions in the aspects of aerial photography, detection, stability maintenance, investigation, rescue, plant protection and the like. In recent years, multi-rotor unmanned aerial vehicles gradually become mainstream development in the field of unmanned aerial vehicles, and multi-rotor unmanned aerial vehicles of various styles and functions appear in the market.

In the design of an aircraft, weight factors are one of the factors considered primarily, in the design concept of the relevant industry of the aircraft, the requirement on the weight of an air machine of the aircraft is very high, and the weight of the air machine of unmanned planes (including multi-rotor unmanned planes) in the current market is generally higher, so that the effective load is smaller, and the problem of shorter cruising time and distance is further caused.

SUMMERY OF THE UTILITY MODEL

The purpose of the utility model is to solve at least one of the problems existing in the prior art, this purpose is realized through following technical scheme:

according to the utility model discloses many rotor unmanned aerial vehicle, including fuselage, horn and rotor, the one end of horn connect in the fuselage, the rotor sets up the other end of horn, its characterized in that, the cross sectional shape of horn is the rectangle.

In some embodiments, the fuselage comprises: the number of the longitudinal beams is two, and the two longitudinal beams are arranged at intervals and in parallel; the two cross beams are arranged at intervals and in parallel, and the two cross beams and the two longitudinal beams are combined into a first rectangular frame body; the two longitudinal rib plates are arranged in parallel at intervals, and the longitudinal rib plates are connected between the two cross beams; the horizontal rib plate, horizontal rib plate is two and interval parallel arrangement, horizontal rib plate connects two between the longeron, two horizontal rib plate and two form the second rectangle framework after the vertical rib plate is alternately, the second rectangle framework is rotor unmanned aerial vehicle's main bearing structure.

In some embodiments, the multi-rotor drone further includes a battery for powering the multi-rotor drone, the battery being secured in the second rectangular frame.

In some embodiments, the multi-rotor drone further comprises a top cover secured to the first rectangular frame.

In some embodiments, the multi-rotor unmanned aerial vehicle further comprises a connecting seat, the connecting seat is fixed to the bottom of the second rectangular frame body, and an interface used for being connected with external task equipment is arranged on the connecting seat.

In some embodiments, the longitudinal rib and the transverse rib are respectively provided with a plurality of lightening holes.

In some embodiments, the multi-rotor unmanned aerial vehicle further includes two landing gears, each landing gear includes a horizontal connecting portion and support legs located at two ends of the horizontal connecting portion, and the horizontal connecting portion is the cross beam in the first rectangular frame.

In some embodiments, a foot is provided at the bottom of the leg, and a resilient cushion is provided at the bottom of the foot.

In some embodiments, the longitudinal beams, the cross beams, the longitudinal ribs, the latitudinal ribs, the horn, and the landing gear are all made of carbon fiber composite material.

The utility model has the advantages that:

according to the utility model discloses many rotor unmanned aerial vehicle adopts the horn of cross sectional shape for the rectangle, and it is compared in the horn of cross sectional shape for circular shape conventional structure, has less amount of deflection under the same materials, and consequently moment resistance ability is stronger, consequently, improves the cross sectional shape of horn into the rectangle by circular, is favorable to reducing the materials of horn structure to reduce many rotor unmanned aerial vehicle's empty aircraft weight, and then promotes many rotor unmanned aerial vehicle's load and duration.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:

fig. 1 is a schematic structural view of a multi-rotor unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural view of the multi-rotor drone shown in fig. 1, with the top cover omitted;

fig. 3 is a schematic structural view of the multi-rotor drone shown in fig. 2 when the battery is omitted.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.

Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.

For convenience of description, spatially relative terms, such as "inner", "outer", "lower", "below", "upper", "above", and the like, may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures. Such spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the example term "below … …" can include both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

As shown in fig. 1-3, according to the utility model discloses many rotor unmanned aerial vehicle of embodiment, including fuselage 10, horn 20 and rotor 30, the one end of horn 20 is connected in fuselage 10, and rotor 30 sets up the other end at horn 20, and the cross-sectional shape of horn 20 is the rectangle.

According to the utility model discloses many rotor unmanned aerial vehicle adopts the horn 20 of cross sectional shape for the rectangle, and it is compared in the horn of cross sectional shape for circular shape conventional structure, has less amount of deflection under the same materials, and consequently moment resistance ability is stronger, consequently, with the cross sectional shape of horn 20 by circular improvement for the rectangle, be favorable to reducing the materials of horn structure, thereby reduce many rotor unmanned aerial vehicle's empty aircraft weight, and then promote many rotor unmanned aerial vehicle's load and duration.

Specifically, in the deflection calculation, the calculation formula of the deformation (deflection) of the free end of the support arm of the multi-rotor unmanned aerial vehicle during flying is as follows:

in the formula: y represents the deformation of the free end, P represents the concentrated load of the free end of the support arm, l represents the length of the support arm, E represents the elastic modulus, and I represents the section moment of inertia, wherein the calculation formula of the section moment of inertia I is as follows:

in the formula: b represents the total width of the cross section, b₁Indicates the width of the hollow part of the cross section, and H indicates the cross sectionTotal height H₁The cross-sectional void height is indicated. The calculation formula of I is substituted into the calculation formula of deflection, the deflection is related to H, and the larger the H is, the smaller the deflection is, namely the farther the upper surface and the lower surface are from the stress center, the smaller the deflection is. Based on the results, the cantilever 20 with the rectangular cross section has smaller flexibility than the cantilever with the circular cross section, so that the same bending moment resistance is achieved, the material consumption is less, and the empty weight of the multi-rotor unmanned aerial vehicle is reduced.

In some embodiments, the fuselage 10 includes longitudinal beams 11, transverse beams 12, longitudinal ribs 13, and latitudinal ribs 14, where the longitudinal beams 11 are two, the two longitudinal beams 11 are spaced and arranged in parallel, the transverse beams 12 are two, the two transverse beams 12 are spaced and arranged in parallel, the two transverse beams 12 and the two longitudinal beams 11 are combined into a first rectangular frame, the horn 20 is connected to the first rectangular frame, the longitudinal ribs 13 are two and arranged in parallel, the longitudinal ribs 13 are connected between the two transverse beams 12, the latitudinal ribs 14 are two and arranged in parallel, the latitudinal ribs 14 are connected between the two longitudinal beams 11, the two latitudinal ribs 14 and the two longitudinal ribs 13 intersect to form a second rectangular frame, and the second rectangular frame is a main bearing structure of the unmanned rotorcraft, which can bear power equipment (e.g., batteries) and external task equipment (e.g., cameras, detection instruments, etc.). The basic structure of the airframe 10 is formed by the two longitudinal beams 11, the two cross beams 12, the two longitudinal rib plates 13 and the two transverse rib plates 14, and the airframe 10 is made to be compact as far as possible under the condition that the requirements of the strength and the rigidity of the airframe 10 are met, so that the weight of the airframe is reduced, the effective load of the multi-rotor unmanned aerial vehicle is improved, and the endurance time and the endurance distance of the multi-rotor unmanned aerial vehicle are improved.

In some embodiments, the multi-rotor drone further comprises a battery 40 for powering the multi-rotor drone, the battery 40 being fixed in the second rectangular frame. Further, many rotor unmanned aerial vehicle can also include top cap 50, and top cap 50 is fixed on first rectangle framework to cover battery 40 under its surface, can play the effect of protection battery 40 and other inner structure (such as circuit board, controller, cable etc.).

In some embodiments, multi-rotor unmanned aerial vehicle further includes connecting seat 60, and connecting seat 60 is fixed in the bottom of second rectangle framework, is equipped with the interface that is used for being connected with external task equipment on connecting seat 60, and when different external task equipment were connected on connecting seat 60, this multi-rotor unmanned aerial vehicle can be applied to different use occasions correspondingly, for example, when external task equipment was the camera, multi-rotor unmanned aerial vehicle can be used to reconnoiter, take photo by plane etc..

In some embodiments, the longitudinal rib plate 13 and the latitudinal rib plate 14 are respectively provided with a plurality of lightening holes, so that the empty weight of the multi-rotor unmanned aerial vehicle can be further reduced.

In some embodiments, the multi-rotor drone further comprises two landing gears 70, the landing gears 70 comprise a horizontal connecting portion and two legs 71 at two ends of the horizontal connecting portion, and in order to make the structure of the multi-rotor drone simpler, the horizontal connecting portion may be a beam 12 in the first rectangular frame.

Further, be equipped with the stabilizer blade 72 in the bottom of landing leg 71, can set up elastic buffer pad (not shown in the figure) by the bottom of stabilizer blade 72 to the impact that receives when can slowing down the landing of many rotor unmanned aerial vehicle and touch down.

In some embodiments, the longitudinal beams 11, the cross beams 12, the longitudinal rib plates 13, the transverse rib plates 14, the horn 20 and the landing gear 70 are all made of carbon fiber composite materials, and the carbon fiber composite materials have the advantages of light weight, high strength, good force bearing performance and the like, so that the weight reduction requirement of the multi-rotor unmanned aerial vehicle can be further met.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A multi-rotor unmanned aerial vehicle comprises a fuselage, a horn and rotors, wherein one end of the horn is connected to the fuselage, and the rotors are arranged at the other end of the horn;

the fuselage includes:

the number of the longitudinal beams is two, and the two longitudinal beams are arranged at intervals and in parallel;

the two cross beams are arranged at intervals and in parallel, and the two cross beams and the two longitudinal beams are combined into a first rectangular frame body;

the two longitudinal rib plates are arranged in parallel at intervals, and the longitudinal rib plates are connected between the two cross beams;

the horizontal rib plate, horizontal rib plate is two and interval parallel arrangement, horizontal rib plate connects two between the longeron, two horizontal rib plate and two form the second rectangle framework after the vertical rib plate is alternately, the second rectangle framework is rotor unmanned aerial vehicle's main bearing structure.

2. The multi-rotor drone of claim 1, further comprising a battery for powering the multi-rotor drone, the battery being secured in the second rectangular frame.

3. The multi-rotor drone of claim 2, further comprising a top cap secured to the first rectangular frame.

4. The multi-rotor unmanned aerial vehicle of any one of claims 1-3, further comprising a connection base secured to a bottom of the second rectangular frame, the connection base having an interface thereon for connection with external task equipment.

5. A multi-rotor drone according to any one of claims 1 to 3, wherein the longitudinal ribs and the latitudinal ribs are each provided with a plurality of lightening holes.

6. A multi-rotor unmanned aerial vehicle as claimed in any one of claims 1 to 3, further comprising two landing gears, the landing gears including a horizontal connecting portion and legs at both ends of the horizontal connecting portion, the horizontal connecting portion being the cross-beam in the first rectangular frame.

7. A multi-rotor unmanned aerial vehicle as recited in claim 6, wherein a foot is provided at a bottom of the leg, and wherein a resilient cushion is provided at a bottom of the foot.

8. The multi-rotor drone of claim 6, wherein the longitudinal beams, the cross beams, the longitudinal ribs, the latitudinal ribs, the horn, and the landing gear are all made of carbon fiber composite material.