CN211139671U

CN211139671U - Six rotor unmanned aerial vehicle

Info

Publication number: CN211139671U
Application number: CN201922165405.1U
Authority: CN
Inventors: 曹庆旭; 庞振岳; 赵学松; 孔令超; 佟亮; 裴允嘉; 李楠
Original assignee: Shenyang Xuanfei Aviation Technology Co ltd
Current assignee: Shenyang Xuanfei Aviation Technology Co ltd
Priority date: 2019-12-06
Filing date: 2019-12-06
Publication date: 2020-07-31
Anticipated expiration: 2029-12-06

Abstract

The utility model provides a six rotor unmanned aerial vehicle, its cantilever system include from four first cantilevers that the head and the tail both sides of fuselage outwards stretched out to and from two second cantilevers that the middle part both sides of fuselage outwards stretched out, the screw of the end-to-end support of first cantilever arranges up, the screw of the end-to-end support of second cantilever arranges down. The utility model provides a six rotor unmanned aerial vehicle, the interval between four oblique outside first cantilevers that stretch out is the biggest, can not produce the problem of interference between the screw on it, therefore the screw on four first cantilevers all can arrange up. Two second cantilevers are located the middle part of fuselage, and is relatively less with the interval between two first cantilevers of homonymy, and screw on two second cantilevers is arranged downwards and can be reduced and interfere, is favorable to reducing the length of cantilever, and unmanned aerial vehicle can obtain littleer structure size on the whole, therefore can greatly reduced unmanned aerial vehicle's volume, the unmanned aerial vehicle's of being convenient for warehousing and transportation.

Description

Six rotor unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field especially relates to an unmanned aerial vehicle of many rotors, in particular to unmanned aerial vehicle with six rotors.

Background

The unmanned aerial vehicle at present is multiaxis unmanned aerial vehicle mostly, like four-axis, six, the complete machine weight of taking off is very little, but the cantilever expansion is very big, brings certain difficulty for unmanned aerial vehicle's transportation, carry and save etc.. For example, CN 204587305U discloses eight rotor electric unmanned aerial vehicle of multi-functional folded cascade, mainly solves the problem that current rotor electric unmanned aerial vehicle usage is single, the structure is complicated, complete machine transportation difficulty. The angle such as eight rotors of above-mentioned prior art's unmanned aerial vehicle is around the organism setting, leads to the application load of carrying on the organism to set up under the organism only, and because each direction all receives blockking of rotor, the load of carrying can only develop the operation downwards, can not launch the weapon or observe to oblique top, just as introduce among this prior art, this unmanned aerial vehicle can only be suitable for the below to unmanned aerial vehicle and spray the operation such as.

In order to solve the technical problem, CN 207550499U provides an electric unmanned aerial vehicle, which comprises a vehicle body, two landing gears, eight cantilevers connected to the vehicle body, and eight motors supported by the cantilevers, wherein a longitudinal load channel is arranged below the vehicle body, and a first group of four cantilevers and a second group of four cantilevers are symmetrically arranged on two sides of the longitudinal load channel respectively. This prior art's electric unmanned aerial vehicle sets up a longitudinal load passageway that does not shelter from through in the fuselage below, can conveniently set up loads such as photoelectricity hanging storehouse and weapon launch canister, and take place to interfere with cantilever and screw when avoiding surveing and the weapon transmission, influence use and combat efficiency, improved unmanned aerial vehicle's range of application. In addition, this prior art has reduced the volume after folding through setting for the overall layout structure of optimization, the low-cost transportation of the unmanned aerial vehicle of being convenient for.

The above prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. Especially when the folding volume of unmanned aerial vehicle so that quick assembly disassembly, transportation need further reduce further, current unmanned aerial vehicle's beta structure still has further improved space.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to provide a six rotor unmanned aerial vehicle to reduce or avoid the aforementioned problem.

In order to solve the technical problem, the utility model provides a six rotor unmanned aerial vehicle, including fuselage, undercarriage and the cantilever system who supports the motor, every motor all has the screw, the cantilever system includes the follow four first cantilevers that outwards stretch out to the head and the tail both sides slant of fuselage, and follow two second cantilevers that outwards stretch out in the middle part both sides of fuselage, wherein, the end-to-end support's of first cantilever screw is located the top of first cantilever is arranged upwards, the end-to-end support's of second cantilever screw is located the below of second cantilever is arranged down.

Preferably, a first folding mechanism is arranged at the joint of the first cantilever and the body, and two first cantilevers located on the same side of the body can be folded oppositely to each other through the first folding mechanism.

Preferably, a second folding mechanism is arranged at the joint of the second cantilever and the machine body; the middle part of the cantilever is provided with a third folding mechanism, and the second cantilever is divided into a rear arm part and a front arm part by the third folding mechanism; the front arm part can be folded by drawing the rear arm part, the rear arm part can be folded by drawing the side wall of the machine body reliably, and the front arm part is clamped between the rear arm part and the side wall of the machine body.

Preferably, a longitudinal load channel is arranged below the machine body, and included angles between central axes of the four first cantilevers and central axes of the longitudinal load channel are all 45 degrees.

Preferably, the central axis of the second cantilever is perpendicular to the longitudinal load channel.

Preferably, the vertical installation position of the second cantilever on the body is lower than the vertical installation position of the first cantilever on the body.

The utility model provides a six rotor unmanned aerial vehicle, the interval between four oblique outside first cantilevers that stretch out is the biggest, can not produce the problem of interference between the screw on it, therefore the screw on four first cantilevers all can arrange up. Two second cantilevers are located the middle part of fuselage, and is relatively less with the interval between two first cantilevers of homonymy, and screw on two second cantilevers is arranged downwards and can be reduced and interfere, is favorable to reducing the length of cantilever, and unmanned aerial vehicle can obtain littleer structure size on the whole, therefore can greatly reduced unmanned aerial vehicle's volume, the unmanned aerial vehicle's of being convenient for warehousing and transportation.

Drawings

The drawings are only intended to illustrate and explain the present invention and do not limit the scope of the invention. Wherein the content of the first and second substances,

fig. 1 shows a schematic perspective view of a six-rotor drone according to an embodiment of the present invention;

fig. 2 and 3 show schematic views of the six-rotor drone of fig. 1 in a folded state, from different perspectives.

Detailed Description

In order to clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

Just as the background art said, this application is directed against the not enough of the electric unmanned aerial vehicle that discloses in prior art CN 207550499U, has proposed a six rotor unmanned aerial vehicle who improves structure, can obtain littleer structure size, and unmanned aerial vehicle's folding volume is littleer moreover to quick assembly disassembly and transportation are convenient for.

That is, to achieve the above object, the present application provides a six-rotor unmanned aerial vehicle, as shown in fig. 1-3, wherein fig. 1 shows a schematic three-dimensional structure diagram of the six-rotor unmanned aerial vehicle according to an embodiment of the present invention; fig. 2 and 3 show schematic views of the six-rotor drone of fig. 1 in a folded state, from different perspectives.

Referring to fig. 1-3, the six rotor drone of the present application comprises a fuselage 1, two undercarriages 2 and a cantilever system 3 supporting motors 4, each motor 4 carrying a propeller 5. The fuselage 1 is generally elongate and is provided with a longitudinal load channel 6 thereunder, the fuselage 1 being arranged parallel to the longitudinal load channel 6 as shown in dotted lines in figure 1. Set up a vertical load passageway 6 that does not shelter from through the below at six rotor unmanned aerial vehicle's fuselage 1, be favorable to setting up loads such as photoelectricity hangar and weapon launching tube, take place to interfere with cantilever system 3 and screw 5 etc. when avoiding surveing and the weapon transmission, influence and use and combat efficiency, improved unmanned aerial vehicle's range of application. In addition, due to the arrangement of the longitudinal load channel 6, the cantilever system 3 and the motor 4 thereon are distributed on two sides of the longitudinal load channel 6, namely two sides of the fuselage 1, so that a larger range of load hanging points can be obtained in the longitudinal direction of the fuselage, and the load layout is easy to expand.

The difference between this application and prior art is, six rotor unmanned aerial vehicle's cantilever system 3 of this application includes four first cantilevers 31 that outwards stretch out from the head and the tail both sides slant of fuselage 1 to and follow two second cantilevers 32 that outwards stretch out of the middle part both sides of fuselage 1, wherein, the end-to-end support's of first cantilever 31 screw 5 is located the top of first cantilever 31 and arranges upwards, and the end-to-end support's of second cantilever 32 screw 5 is located the below of second cantilever 32 and arranges downwards. In one embodiment, the central axes of the four first cantilevers 31 are all angled at 45 degrees to the central axis of the longitudinal load channel 6. The central axis of the second boom 32 is perpendicular to the longitudinal load channel 6.

The unmanned aerial vehicle's of prior art cantilever quantity is the same with rotor quantity, and the waste of structure weight is very big. The interference problem between the adjacent rotor owing to need avoid in prior art, or the quantity that can only reduce the rotor leads to the lift not enough, or can only increase the length of unmanned aerial vehicle's cantilever for obtain sufficient interval between the end of adjacent cantilever, the volume that finally leads to unmanned aerial vehicle becomes very big, and inconvenient carrying transportation, folding volume also hardly reduces.

The six-rotor unmanned aerial vehicle has the advantages that the distance between the four first cantilevers 31 extending outwards in the inclined mode is the largest, the problem of interference cannot occur between the propellers 5 on the four first cantilevers 31, and therefore the propellers 5 on the four first cantilevers 31 can be arranged upwards. Two second cantilevers 32 are located the middle part of fuselage 1, interval between two first cantilevers 31 with the homonymy is less relatively, screw 5 on it interferes with the screw on the adjacent first cantilever 31 easily, therefore screw 5 on two second cantilevers 32 is arranged downwards and is reduced the interference, be favorable to reducing the length of cantilever, unmanned aerial vehicle can obtain littleer structure size on the whole, therefore can greatly reduced unmanned aerial vehicle's volume, be convenient for unmanned aerial vehicle's warehousing and transportation.

Further, propeller 5 on first cantilever 31 and the second cantilever 32 sets up in reverse, further is favorable to unmanned aerial vehicle's folding. As shown in fig. 2 and 3, where the first suspension arm 31 is connected to the main body 1, a first folding mechanism 11 is provided, and the two first suspension arms 31 located on the same side of the main body 1 can be folded by the first folding mechanism 11 opposite to each other. In order to avoid the mutual interference of the folded structures, it can be seen in the drawing that when the two first cantilevers 31 on the same side are folded toward each other, there is a slight upward angle to avoid the tail end of the folded first cantilever 31 from propping the root of the other first cantilever 31, which is more beneficial to the folded first cantilever 31 to get close to the side wall of the fuselage 1 as much as possible, and is beneficial to obtaining smaller folded volume. Figures 2 and 3 omit the undercarriage beneath the fuselage 1 for clarity of illustration, not shown.

Further, a second folding mechanism 12 is arranged at the joint of the second cantilever 32 and the machine body 1; the middle of the cantilever 32 is provided with the third folding mechanism 13, and the second cantilever 32 is divided into a rear arm portion 131 and a front arm portion 132 by the third folding mechanism 13; wherein the section near the body 1 is a rear arm part 131, and the section far from the body 1 is a front arm part 132, as shown in the figure. The front arm portion 132 can be folded close to the rear arm portion 131 by the third folding mechanism 13, and the rear arm portion 131 can be folded close to the side wall of the body 1 by the second folding mechanism 12, and the front arm portion 132 is sandwiched between the rear arm portion 131 and the side wall of the body 1. In the illustrated embodiment, the second boom 32 is folded generally toward the tail of the drone. Of course, depending on the actual situation, the second boom 32 may also be set to fold as a whole towards the head of the drone.

In the above embodiment, the second suspension arm 32 is folded in two stages, and the front arm part 132 is folded toward the rear arm part 131, and then the rear arm part 131 carries the front arm part 132 toward the body. Because the propeller 5 at the end of the second cantilever 32 is arranged downwards, after the second cantilever 32 is folded twice, the propeller 5 at the end of the second cantilever can perfectly avoid the first cantilever 31, and the problem that the folded structures interfere with each other is avoided. In addition, in a preferred embodiment, the vertical installation position of the second suspension arm 32 on the body 1 is lower than the vertical installation position of the first suspension arm 31 on the body 1, so that the second suspension arm 32 as a whole can be arranged below the first suspension arm 31 to be folded, and the second suspension arm 32 can be close to the side wall of the body 1 as much as possible after being folded twice without interference, which is beneficial to reducing the folding volume.

In the six rotor unmanned aerial vehicle of this application, six cantilevers of cantilever system divide into two sets ofly to fold, and the great first cantilever in interval is folding relatively each other, and the second cantilever at fuselage middle part adopts two segmentation foldings, can form the beta structure of the range upon range of formula that fig. 2 and fig. 3 show, has avoided the defect that current cantilever fold-down suspended structure height is big, be difficult to the transportation, has reduced unmanned aerial vehicle's volume, the warehousing and transportation of being convenient for.

In addition, it should be understood by those skilled in the art that the first folding mechanism 11, the second folding mechanism 12, and the third folding mechanism 13 may be any of the existing folding structures suitable for the connection and folding of the bars, such as a folder of a foldable bicycle, etc., which can be used in the concept of the present application.

It is to be understood by those skilled in the art that while the present invention has been described in terms of several embodiments, it is not intended that each embodiment cover a separate embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including all technical equivalents which are encompassed by the claims.

The above description is only exemplary of the present invention, and is not intended to limit the scope of the present invention. Any equivalent changes, modifications and combinations that may be made by those skilled in the art without departing from the spirit and principles of the invention should be considered within the scope of the invention.

Claims

1. The utility model provides a six rotor unmanned aerial vehicle, includes cantilever system (3) of fuselage (1), undercarriage (2) and support motor (4), and every motor (4) all has screw (5), its characterized in that: cantilever system (3) are including follow four first cantilevers (31) that the head and the tail both sides slant of fuselage (1) are outwards stretched out, and follow two second cantilevers (32) that the middle part both sides of fuselage (1) are outwards stretched out, wherein, the end-supported propeller (5) of first cantilever (31) are located the top of first cantilever (31) and upwards arrange, the end-supported propeller (5) of second cantilever (32) are located the below of second cantilever (32) and arrange down.

2. A hexa-rotor drone according to claim 1, characterized in that the junction of the first boom (31) with the fuselage (1) is provided with a first folding mechanism (11), by means of which the two first booms (31) located on the same side of the fuselage (1) can be folded opposite each other.

3. A hexa-rotor drone according to claim 2, characterised in that the second boom (32) is provided with a second folding mechanism (12) at the connection with the fuselage (1); a third folding mechanism (13) is arranged in the middle of the cantilever (32), and the second cantilever (32) is divided into a rear arm part (131) and a front arm part (132) by the third folding mechanism (13); forearm portion (132) accessible third folding mechanism (13) draw close rear arm portion (131) are folding, rear arm portion (131) accessible second folding mechanism (12) draw close the lateral wall of fuselage (1) is folding, and will forearm portion (132) centre gripping is in rear arm portion (131) with between the lateral wall of fuselage (1).

4. A hexa-rotor unmanned aerial vehicle according to claim 3, wherein a longitudinal load channel (6) is arranged below the fuselage (1), and the included angles between the central axes of the four first cantilevers (31) and the central axis of the longitudinal load channel (6) are all 45 degrees.

5. A six-rotor drone according to claim 4, characterised in that the central axis of the second boom (32) is perpendicular to the longitudinal load channel (6).

6. A hexa-rotor drone according to claim 5, characterized in that the vertical mounting position of the second boom (32) on the fuselage (1) is lower than the vertical mounting position of the first boom (31) on the fuselage (1).