CN206407101U - Folding multi-rotor unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a kind of folding multi-rotor unmanned aerial vehicle, specifically, the unmanned plane includes：Fuselage；Multiple horns, one end of each horn is connected by rotating mechanism with the side of fuselage, and the other end of each horn is provided with motor and the folding oar with motor connection, and horn is rotated by rotating mechanism relative to fuselage；Wherein, horn is divided into preceding horn and rear horn, in a folded configuration, preceding horn on to inboard rotary folding, and close at the blade on the side surface upper part of fuselage, preceding horn fold after close at before between horn and fuselage；Horn is from lower to inboard rotary folding afterwards, and closes at after the blade on the side lower of fuselage, rear horn is folded and close on the outside of rear horn, away from fuselage.Horn of the present utility model order, and the horn anglec of rotation is small in no particular order during folding or unfolding, is more convenient operation；Space availability ratio is high after folding；Avoid the interference to head；Design for folding oar and motor provides more possibility.

Description

Folding multi-rotor unmanned aerial vehicle

Technical field

The utility model is related to unmanned plane field, relates more specifically to a kind of folding multi-rotor unmanned aerial vehicle.

Background technology

In recent years, unmanned plane with the features such as its simple structure, convenient manipulation and higher security performance by more next More attention.But it is larger to there is size in the multi-rotor unmanned aerial vehicle of prior art, vanning, transport or it is inconvenient to carry the problem of. Of the prior art, the horn of unmanned plane is integrally formed mostly with fuselage, also have be partly by horn be divided into first paragraph horn and Second segment horn two parts, first paragraph horn is integrally formed with fuselage, and second segment horn is removably connected with first paragraph horn, Integrally removably it is connected with fuselage in addition with horn, the problem of these solve transport, memory space to a certain extent, But need for when in use it is manually installed, it is relatively complicated.Therefore, some horns be designed as it is foldable, without people Work is installed, but the folding of its folded form largely for horn before and after carrying out in the same plane in folding movement, and folding process Folded to need a point order, and the anglec of rotation of horn is larger, space availability ratio is not high, and the state after motor and blade have been folded is relative In fuselage upward or down, the design to blade and motor in limited folding space has been limited, and to cloud after folding Platform structure has been interfered.

Therefore, this area still lacks a kind of horn and folded in no particular order sequentially there is provided more preferable operating experience, and is folding Or the anglec of rotation is smaller during unfolding, space availability ratio is high after folding, it is to avoid the interference to cradle head structure, is the design of head More possibility are provided, while also providing more possible unmanned planes for the design of blade and motor.

Utility model content

The purpose of this utility model is to provide a kind of folding multi-rotor unmanned aerial vehicle.Many rotors of the present utility model without Man-machine horn order, and the horn anglec of rotation is small in no particular order during folding or unfolding, is more convenient operation；It is empty after folding Between utilization rate it is high；Avoid the interference to head；Design for folding oar and motor provides more possibility.

The utility model provides a kind of folding multi-rotor unmanned aerial vehicle, and the unmanned plane includes：Fuselage；Multiple machines Arm, one end of each horn is connected by rotating mechanism with the side of the fuselage, the other end of each horn Motor and the folding oar with the motor connection are provided with, the horn is carried out by the rotating mechanism relative to the fuselage Rotation；Wherein, the horn is divided into preceding horn and rear horn, in a folded configuration, and the preceding horn is on into the fuselage Side rotary folding, and close at the blade on the side surface upper part of the fuselage, the preceding horn fold after close at the preceding horn and Between the fuselage；The rear horn closes at the side lower of the fuselage, institute from lower to the inboard rotary folding State and closed at after the blade on rear horn is folded on the outside of the rear horn, away from the fuselage.

In another preference, the horn is provided with certain radian, and the section of the horn is non-constant section, described non- Uiform section refers to along along the horn length direction, and the sectional area of the horn is change by one end to the other end so that nothing It is man-machine after folding, horn takes full advantage of remaining after the straight horn of conventional uiform section is folded in the distribution straggly of fuselage both sides Intermediate space.

In another preference, the rotating mechanism includes fuselage end, horn end and rotating shaft, by the rotating shaft, by institute Fuselage end is stated to connect with the horn end, wherein, the fuselage end is connected with the fuselage, the horn end with it is described Horn is connected, under the rotation of the rotating shaft, and the horn rotates relative to the fuselage.

In another preference, the fuselage end and the horn end are equipped with the shaft hole for inserting the rotating shaft, A part for the rotating shaft is located in the shaft hole at the fuselage end, and a part is in the shaft hole at the horn end.

In another preference, the fuselage end for the rotating mechanism being connected with the preceding horn is in the upper of the horn end Side.

In another preference, the horn end for the rotating mechanism being connected with the rear horn is in the upper of the fuselage end Side.

In another preference, the rotating mechanism has certain radian, and it is shaped as " S " type.

In another preference, the rotating mechanism is described spacing and lock provided with spacing and lock device Device can be following any form：Buckle, tongue and groove and impeller tooth.

In another preference, the rotating mechanism being connected with the preceding horn is located at the side front upper place of the fuselage； The rotating mechanism being connected with the rear horn is located at the side back lower place of the fuselage.

In another preference, head is provided with the bottom of the fuselage.In another preference, the unmanned plane is in exhibition Open or state of flight under, it is described fold oar be located at the horn top.

In another preference, the rotating shaft is perpendicular to the end face at the fuselage end and/or the end face at the horn end.

In another preference, the end face at the fuselage end and the end face at the horn end are nose circle face.

In another preference, the end face at the fuselage end and the end face at the horn end fit.

In another preference, the rotating shaft and the central axis at the fuselage end coincide.

In another preference, the rotating shaft and the central axis at the horn end coincide.

In another preference, the locking mechanism and the structure that locks is snap parts.

In another preference, the rotating shaft is fixedly connected with the fuselage end, is flexibly connected with the horn end, i.e. institute Stating horn can rotate around the rotating shaft relative to the fuselage.

In another preference, the rotating shaft is fixedly connected with the horn end, is flexibly connected with the fuselage end, i.e. institute Stating horn and the rotating shaft can rotate relative to the fuselage.

In another preference, the rotating shaft is to be flexibly connected with the horn end and the fuselage end, between three It can rotate against.

Major advantage of the present utility model includes：

(a) horn during folding or unfolding in no particular order order；

(b) horn anglec of rotation during folding or unfolding is small；

(c) convenient operation, optimizes operating experience；

(d) space availability ratio is high after folding；

(e) interference to cradle head structure is avoided；

(f) design to fold oar and motor provides more possibility；

(g) unmanned plane size is reduced.

Therefore, misplaced above and below front and rear horn of the present utility model, preceding horn overturns toward inboard on and folded, rear horn Folded from lower overturn toward inboard, front and rear horn folding movement is non-interference, realize space folding order in no particular order；It is front and rear Horn is located at fuselage both sides after having rolled over, the state after preceding horn has been rolled over is that motor and blade are located at the preceding horn and the fuselage Between, the state after rear horn has been rolled over is that motor and blade are located at external fuselage towards fuselage outer side, motor and folding oar, is had more Big locational space also avoids head of the motor with blade and in front of fuselage from interferenceing there is provided more designabilities.

It should be understood that in the range of the utility model, above-mentioned each technical characteristic of the present utility model and below (as implemented Example) in specifically describe each technical characteristic between can be combined with each other, so as to constitute new or preferred technical scheme.It is limited to Length, no longer tires out state herein one by one.

Brief description of the drawings

, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art Or the accompanying drawing used required in description of the prior art does and simply introduced, it should be apparent that, drawings in the following description are only It is some embodiments of the present utility model, for those of ordinary skill in the art, is not paying the premise of creative work Under, other accompanying drawings can also be obtained according to these accompanying drawings.

Fig. 1 is state diagram when multi-rotor unmanned aerial vehicle horn in one example of the utility model is unfolded.

State diagram when Fig. 2 is the downward interior folding of horn after the multi-rotor unmanned aerial vehicle in one example of the utility model.

Fig. 3 is the preceding upward interior folding of horn after horn is folded after the multi-rotor unmanned aerial vehicle in one example of the utility model When state diagram.

Fig. 4 is the state diagram after one group of horn of multi-rotor unmanned aerial vehicle in one example of the utility model is folded.

Fig. 5 be the multi-rotor unmanned aerial vehicle in one example of the utility model horn all fold after state diagram.

In each accompanying drawing, each sign is as follows：

1- fuselages；

2- folds oar；

3- motors；

4- rotating mechanisms；

5- horns.

Embodiment

The present inventor is by in-depth study extensively, by largely screening, and rotation more than a kind of folding is developed first Wing unmanned plane.Compared with prior art, the preceding horn of the unmanned plane is on into the fuselage for unmanned plane of the present utility model Side rotary folding, and close at the blade on the side surface upper part of the fuselage, the preceding horn fold after close at the preceding horn and Between the fuselage；The rear horn closes at the side lower of the fuselage, institute from lower to the inboard rotary folding State and closed at after blade on rear horn is folded on the outside of the rear horn, away from the fuselage, therefore, the folding of the horn regardless of Sequencing, and top, bottom and the lateral space of folding rear body can install miscellaneous part, improve space availability ratio, The anglec of rotation of the horn during folding or unfolding is also reduced, simultaneously as oar and motor are folded positioned at the side of fuselage, Space is not limited, the design to fold oar and motor provides more possibilities, horn is designed as with certain radian, folding The distance that staggers above and below poststack, horn is greatly reduced, and possibility is provided for the smaller aircraft of design, if in addition, fuselage bottom installs cloud Platform, in horn folding process, the folding oar on rear horn closes at the outside of rear horn, it is to avoid interfered with head, herein On the basis of complete the utility model.

With reference to specific embodiment, the utility model is expanded on further.It should be understood that these embodiments are merely to illustrate this Utility model rather than limitation scope of the present utility model.In addition, accompanying drawing is schematic diagram, therefore the utility model device and set Standby is not limited by the size or ratio of the schematic diagram.

It should be noted that in the claim and specification of this patent, such as " on ", " under ", " upward ", " court Under ", " left front ", " right front ", " left back ", " right back ", " top surface ", " bottom surface ", " top ", the position of " bottom " etc. close It is term, it is only more easily to state the relative of each part for unmanned plane during flying state direction visual angle to be Position relationship, and not necessarily represent each part and there is this actual position relationship；Such as first and second or the like relation Term is used merely to make a distinction an entity or operation with another entity or operation, and not necessarily requires or imply There is any this actual relation or order between these entities or operation.Moreover, term " comprising ", "comprising" or its Any other variant is intended to including for nonexcludability so that process, method, article including a series of key elements or Equipment not only includes those key elements, but also other key elements including being not expressly set out, or also include be this process, Method, article or the intrinsic key element of equipment.In the absence of more restrictions, by wanting that sentence " including one " is limited Element, it is not excluded that also there is other identical element in the process including the key element, method, article or equipment.

As Figure 1-5, folding multi-rotor unmanned aerial vehicle of the present utility model include fuselage 1, fold oar 2, motor 3, Rotating mechanism 4 and horn 5, the horn 5 are foldable form.The quantity of the horn 5 is four, and the horn 5 is divided into again Horn after two preceding horns and two, one end of the horn 5 is connected on the fuselage 1 by the rotating mechanism, described The other end of horn 5 is connected with motor 3, and motor 3 is connected with folding oar 2 again.Wherein, two preceding horns by respectively with its phase The rotating mechanism of connection is located at the side front upper place of the fuselage 1；Horn with the rear horn by being connected respectively after two Rotating mechanism be located at the fuselage 1 the side back lower place.In addition, the horn 5 has certain radian, and the horn 5 Section is non-constant section so that after folding, horn 5 takes full advantage of conventional etc. in the distribution straggly of the both sides of fuselage 1 unmanned plane Remaining intermediate space after the straight horn in section is folded.

The rotating mechanism 4 includes fuselage end, horn end and rotating shaft, by the rotating shaft, by the fuselage end with it is described Horn end is connected, wherein, the fuselage end is to be located at the part on the fuselage 1 close to the horn 5, the horn End is to be located at the part on the horn 5 close to the fuselage 1, and under the rotation of the rotating shaft, the horn 5 is relative to institute Fuselage 1 is stated to rotate.Top of the fuselage end for the rotating mechanism being connected with the preceding horn at the horn end；And with it is described after Top of the horn end for the rotating mechanism that horn is connected at the fuselage end.The rotating mechanism 4 has certain radian, its shape For " S " type.

Specifically, the horn 5 of the folding unmanned plane is in deployed condition, as shown in Figure 1.The preceding horn is in exhibition During open state, the left front and right front of unmanned plane are stretched to respectively, and described folding oar 2 is located at the top of the rear horn, In deployed condition；The rear horn stretches to the left back and right back of unmanned plane, and described folding in deployed condition, respectively Folded oar 2 is similarly positioned in the top of the rear horn, in deployed condition.

The horn 5 of the folding unmanned plane is in folded state, as shown in Figure 2-5.In a folded configuration, before described Horn, to the inner side rotary folding of fuselage 1, and closes at the blade on the side surface upper part of the fuselage 1, the preceding horn on Closed at after folding between the preceding horn and the fuselage 1；The rear horn from lower to the inner side rotary folding of fuselage 1, and Close at and closed at after the blade on the side lower of the fuselage 1, the rear horn is folded on the outside of the rear horn, away from the machine Body 1.After folding, stagger above and below front and rear horn, the folding oar and motor on preceding horn inwardly, folding oar and motor on rear horn Outwardly.This folding mode not only anglec of rotation very little, is electricity while motor 3 and folding oar 2 exposed to the outside of fuselage 1 The design of machine 3 and folding oar 2 is provided under bigger performance space, such a mode, and horn 5 is equal when whether folding or unfold There is provided more preferable operating experience for order in no particular order；Horn 5 has after certain radian, such a folding mode when designing, horn 5 The distance that staggers up and down is greatly reduced, and possibility is provided for the smaller unmanned plane of design.

The fuselage end of the rotating mechanism 4 and the end face at horn end are nose circle face, during unmanned plane use, two The nose circle face is bonded to each other, in addition, the rotating shaft is perpendicular to two nose circle faces, and the rotating shaft and the fuselage end Central axis and the central axis at the horn end coincide.The fuselage end and the horn end are equipped with described for inserting The shaft hole of rotating shaft, the half of the rotating shaft is located in the shaft hole at the fuselage end, and half is located at the rotating shaft at the horn end Kong Zhong.The rotating shaft is fixedly connected with the fuselage end, is flexibly connected with the horn end, i.e., described horn can be around the rotating shaft Relative to fuselage rotation.One end that the rotating shaft is connected with the horn end provided with projection, the horn end be provided with The locking projections portion that the projection matches, it is described raised locked when the horn is fully rotated into extended configuration.

All documents referred in the utility model are all incorporated as reference in this application, just as each document quilt It is individually recited as with reference to such.In addition, it is to be understood that after above-mentioned instruction content of the present utility model has been read, this area skill Art personnel can make various changes or modifications to the utility model, and these equivalent form of values equally fall within the application appended claims Book limited range.

Claims (10)

1. a kind of folding multi-rotor unmanned aerial vehicle, it is characterised in that the unmanned plane includes：

Fuselage；

Multiple horns, one end of each horn is connected by rotating mechanism with the side of the fuselage, each machine The other end of arm is provided with motor and the folding oar with the motor connection, and the horn is by the rotating mechanism relative to institute Fuselage is stated to be rotated；

Wherein, the horn is divided into preceding horn and rear horn, in a folded configuration, and the preceding horn is on to the inboard Rotary folding, and close at the blade on the side surface upper part of the fuselage, the preceding horn fold after close at the preceding horn and institute State between fuselage；The rear horn closes at the side lower of the fuselage from lower to the inboard rotary folding, described The blade on horn is closed at after folding on the outside of the rear horn afterwards, away from the fuselage.

2. folding multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that the horn is provided with certain radian, And the section of the horn is non-constant section, the non-constant section refers to along along the horn length direction, section of the horn Area is change by one end to the other end.

3. folding multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that the rotating mechanism includes fuselage End, horn end and rotating shaft, by the rotating shaft, the fuselage end is connected with the horn end, wherein, the fuselage end Be connected with the fuselage, the horn end is connected with the horn, under the rotation of the rotating shaft, the horn relative to The fuselage rotation.

4. folding multi-rotor unmanned aerial vehicle as claimed in claim 3, it is characterised in that the fuselage end and the horn end The shaft hole for inserting the rotating shaft is equipped with, a part for the rotating shaft is located in the shaft hole at the fuselage end, one Divide in the shaft hole at the horn end.

5. folding multi-rotor unmanned aerial vehicle as claimed in claim 3, it is characterised in that the rotation being connected with the preceding horn Top of the fuselage end of rotation mechanism at the horn end.

6. folding multi-rotor unmanned aerial vehicle as claimed in claim 3, it is characterised in that the rotation being connected with the rear horn Top of the horn end of rotation mechanism at the fuselage end.

7. folding multi-rotor unmanned aerial vehicle as claimed in claim 3, it is characterised in that the rotating mechanism has certain arc Degree, it is shaped as " S " type.

8. folding multi-rotor unmanned aerial vehicle as claimed in claim 3, it is characterised in that the rotating mechanism provided with spacing and Lock device, it is described spacing and to lock device can be following any form：Buckle, tongue and groove and impeller tooth.

9. folding multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that the rotation being connected with the preceding horn Rotation mechanism is located at the side front upper place of the fuselage；The rotating mechanism being connected with the rear horn is located at the side of the fuselage The back lower place.

10. folding multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that be provided with the bottom of the fuselage Head.