CN211139670U - Six rotor unmanned aerial vehicle of full beta structure - Google Patents

Abstract

The utility model provides a six rotor unmanned aerial vehicle of full beta structure, folding cantilever system including fuselage, folding undercarriage and support motor. The first cantilevers of the foldable cantilever system can be folded against each other and the second cantilevers of the foldable cantilever system can be folded in two. The first and second folding brackets of the foldable landing gear may be foldable relative to each other. In the six rotor unmanned aerial vehicle of full beta structure of this application, six cantilevers of cantilever system can be relative and two segmentation folds, and two folding supports of undercarriage also can be folded relatively each other simultaneously for six rotor unmanned aerial vehicle of this application 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 of full beta structure

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 cantilever and undercarriage all can folding six rotor unmanned aerial vehicle of full beta structure.

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 unmanned aerial vehicle sets up around the organism, leads to the application load of carrying on the organism to set up under the organism only, and because all directions all receive blockking of rotor, the load of carrying can only develop the operation downwards, can not launch the weapon or observe to oblique top, can only be suitable for in its description the operation such as spray below to unmanned aerial vehicle.

In order to solve the technical problem, CN 207550499U provides an electric unmanned aerial vehicle, which comprises a vehicle body, two landing gears, and eight motors connected to the eight motors supported by cantilevers on the vehicle body, 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 of full beta structure to reduce or avoid the aforementioned problem.

In order to solve the technical problem, the utility model provides a six-rotor unmanned aerial vehicle with a fully-folded structure, which comprises a vehicle body, a foldable undercarriage and a foldable cantilever system supporting motors, wherein each motor is provided with a propeller, and the cantilever system comprises four first cantilevers obliquely extending outwards from two sides of the head and the tail of the vehicle body and two second cantilevers extending outwards from two sides of the middle of the vehicle body; the two first cantilevers located on the same side of the fuselage can be folded towards each other; said second boom being divided into a rear arm portion and a front arm portion by a third folding mechanism; the front arm part can be folded close to the rear arm part, the rear arm part can be folded close to the side wall of the machine body, and the front arm part is clamped between the rear arm part and the side wall of the machine body; the foldable undercarriage comprises a first folding support and a second folding support, wherein the first folding support is positioned on one side of the undercarriage body, the second folding support corresponds to the first folding support and is positioned on the other side of the undercarriage body, and two pull rods are connected between the first folding support and the second folding support; the first folding bracket can be folded towards the second folding bracket to be parallel to the pull rod; the second folding bracket may be folded toward the first folding bracket to a state parallel to the draw bar.

Preferably, the end supported propeller of the first boom is located above and arranged facing upwards of the first boom, and the end supported propeller of the second boom is located below and arranged facing downwards of the second boom.

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

Preferably, a second folding mechanism is arranged at the joint of the second cantilever and the machine body; a third folding mechanism is arranged in the middle of the cantilever; the rear arm portion may be folded by the second folding mechanism and the front arm portion may be folded by the third folding mechanism.

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.

Preferably, a fourth folding mechanism is arranged below the position where the first folding bracket is connected with the pull rod, and the first folding bracket can be folded through the fourth folding mechanism; and a fifth folding structure is arranged below the position where the second folding support is connected with the pull rod, and the second folding support can be folded through the fifth folding structure.

Preferably, the vertical distance between the fourth folding mechanism and the pull rod is smaller than the vertical distance between the fifth folding mechanism and the pull rod.

Preferably, the first folding bracket is adjacent to the pull rod after being folded; after the second folding support is folded, the second folding support is close to the first folding support, and the first folding support is clamped between the second folding support and the pull rod.

In the six rotor unmanned aerial vehicle of full beta structure of this application, six cantilevers of cantilever system can be folded with one section and two sections modes respectively, and two folding supports of undercarriage also can be folded relatively each other simultaneously for six rotor unmanned aerial vehicle of this application 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 fully-folded six-rotor drone according to an embodiment of the present invention;

fig. 2 and 3 show schematic folded views of the fully folded configuration hexarotor drone of fig. 1 from different perspectives;

FIG. 4 shows a schematic view of a foldable landing gear according to an embodiment of the present application;

figures 5 and 6 show a schematic view of the foldable landing gear of figure 4 in a folded state, from a different perspective.

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 full beta structure six rotor unmanned aerial vehicle of improved structure, can obtain littleer structure size, and unmanned aerial vehicle's folding volume is littleer moreover to quick assembly disassembly and transportation.

That is, in order to achieve the above object, the present application provides a six-rotor drone with a fully-folded structure, as shown in fig. 1-3, wherein fig. 1 shows a schematic three-dimensional structure diagram of a six-rotor drone with a fully-folded structure according to a specific embodiment of the present invention; fig. 2 and 3 show schematic folded views of the fully folded configuration hexarotor drone of fig. 1 from different perspectives.

Referring to fig. 1-3, the fully folded configuration hexa-rotor drone of the present application comprises a fuselage 1, two foldable undercarriages 2 and a foldable 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 longitudinal load passageway 6 that does not shelter from through the below at six rotor unmanned aerial vehicle's of full beta structure fuselage 1, be favorable to setting up loads such as photoelectricity hanging storehouse 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 operational 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.

What is different from one of the prior art in this application is, the cantilever system 3 of the six rotor unmanned aerial vehicle of full folded structure of this application is collapsible, and it includes four first cantilevers 31 that outwards stretch out from the head and the tail both sides slant of fuselage 1 to and from the middle part both sides of fuselage 1 two second cantilevers 32 that outwards stretch out, wherein, the end-supported propeller 5 of first cantilever 31 is located the top of first cantilever 31 and arranges upwards, and end-supported propeller 5 of second cantilever 32 is located the below of second cantilever 32 and arranges downwards.

The utility model provides a six rotor unmanned aerial vehicle of full beta structure, the interval between four oblique first cantilevers 31 that outwards stretch out is the biggest, can not produce the problem of interference between the screw 5 on it, therefore the screw 5 on four first cantilevers 31 all can be arranged towards last. 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.

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 full beta structure of this application, six cantilevers of cantilever system divide into two sets of foldings, 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 downward folding suspended structure height of current cantilever big, the defect that is 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.

Further, the six rotor unmanned aerial vehicle of full beta structure of this application still has folding undercarriage.

As shown in fig. 4, as mentioned above, the foldable landing gear of the present application is used for being installed at two sides below the fuselage 1 of the unmanned aerial vehicle, that is, two sides of the fuselage 1 are respectively and symmetrically provided with one landing gear 2, and a pull rod 27 for reinforcing the structure is added between two landing gears 2 compared with the prior art. FIG. 4 shows a schematic view of a foldable landing gear according to an embodiment of the present application.

For convenience of explanation of the structure and folding principle of the foldable landing gear of the present application, in the following description, a landing gear on one side of the fuselage 1 is defined as a first folding bracket 20, a landing gear on the other side of the fuselage 1 corresponding to the first folding bracket 20 is defined as a second folding bracket 30, and the first folding bracket 20 and the second folding bracket 30 have substantially the same structure, and two tie rods 27 are connected therebetween. That is, by definition, the foldable landing gear of the present application comprises a first folding bracket 20 located on one side of the fuselage 1, and a second folding bracket 30 located on the other side of the fuselage 1, corresponding to the first folding bracket 20, with two tie rods 27 connected between the first folding bracket 20 and the second folding bracket 30. The above structure is in fact substantially the same as the unmanned aircraft landing gear mentioned in the background, with the difference that the first folding leg 20 and the second folding leg 30 of the foldable landing gear of the present application both have a foldable structure, and that the first folding leg 20 and the second folding leg 30 can be folded in a specific way, which can significantly reduce the bulk of the landing gear.

The collapsible landing gear of the present application is described in further detail below with reference to figures 4-6, which are improvements over the prior art, and as to structures not described in the present application, those skilled in the art can understand with reference to the figures and the prior art. In which figures 5 and 6 show, in different views, a schematic view of the collapsible landing gear shown in figure 4 in a collapsed state.

As shown in the drawings, in one embodiment of the present application, the first folding bracket 20 is provided with a fourth folding mechanism 212 below the position where the pull rod 27 is connected, and the first folding bracket 20 can be folded toward the second folding bracket 30 to be substantially parallel to the pull rod 27 by the fourth folding mechanism 212; the second folding bracket 30 is provided with a fifth folding mechanism 213 below the position where it is connected to the draw bar 27, and the second folding bracket 30 can be folded toward the first folding bracket 20 to be substantially parallel to the draw bar 27 by the fifth folding mechanism 213. The state after the first folding brackets 20 and the second folding brackets 30 are folded is shown in fig. 5 and 6. The fourth folding mechanism 212 and the fifth folding mechanism 213 may adopt any existing folding structure suitable for connecting and folding the rods, such as a folder of a foldable bicycle, etc., which can be used in the concept of the present application.

In the particular embodiment shown in fig. 5 and 6, the first folding bracket 20 is folded next to the tie rod 27; the second folding bracket 30 is folded next to the first folding bracket 20 and the first folding bracket 20 is sandwiched between the second folding bracket 30 and the draw bar 27. That is, in the illustrated embodiment, the first folding leg 20 is folded first, and then the second folding leg 30 is folded. To ensure that the folding does not interfere, the vertical distance between the fourth folding mechanism 212 and the pull rod 27 is preferably smaller than the vertical distance between the fifth folding mechanism 213 and the pull rod 27.

Further, as shown in the drawings, the first folding bracket 20 and the second folding bracket 30 of the present application each include two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bar 21, and the upper ends of the two vertical bars 21 are fixedly connected to the body. Specifically, the first folding bracket 20 includes two vertical bars 21 connected to the body and a cross bar 22 disposed at the end of the vertical bars 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical rods 21 of the first folding bracket 20 are each provided with a fourth folding mechanism 212 below the position of connection with the pull rod 27. The second folding bracket 30 also comprises two vertical rods 21 connected with the machine body and a cross rod 22 arranged at the tail ends of the vertical rods 21; the two vertical rods 21 are respectively connected with a pull rod 27; the two vertical rods 21 of the second folding bracket 30 are each provided with a fifth folding mechanism 213 below the position where they are connected to the tie rod 27.

Also to avoid folding interference, it is preferable that the fourth folding means 212 on the two vertical bars 21 of the first folding bracket 20 are located in the same plane as the corresponding tie rods 27. The fifth folding mechanism 212 on the two vertical bars 21 of the second folding support 30 is located in the same plane as the corresponding pull rod 27.

To sum up, this application is through setting up beta structure on the first folding support of the both sides at unmanned aerial vehicle's fuselage and the second folding support for first folding support and second folding support can fold relatively each other, and the first folding support after folding and the second folding support can be generally parallel relatively the pull rod between the two, have reduced the volume of undercarriage greatly. The utility model provides a folding undercarriage owing to need not to dismantle from unmanned aerial vehicle, can directly fold and reduce the volume, also very conveniently resumes into the user state from fold condition moreover, has improved unmanned aerial vehicle's warehousing and transportation efficiency greatly.

In addition, among the six rotor unmanned aerial vehicle of full beta structure of this application, six cantilevers of cantilever system can be folded with one section and two sections modes respectively, and two folding supports of undercarriage also can be folded relatively each other simultaneously for the six rotor unmanned aerial vehicle of this application 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.

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 (8)

1. The utility model provides a six rotor unmanned aerial vehicle of full beta structure, includes fuselage (1), folding undercarriage (2) and folding cantilever system (3) of supporting motor (4), and every motor (4) all have screw (5), its characterized in that: the foldable cantilever system (3) comprises four first cantilevers (31) obliquely extending outwards from the head and the tail of the machine body (1) and two second cantilevers (32) extending outwards from the two sides of the middle of the machine body (1); two first cantilevers (31) located on the same side of the fuselage (1) can be folded against each other; said second cantilever (32) being divided into a rear arm portion (131) and a front arm portion (132) by a third folding mechanism (13); the front arm part (132) can be folded by closing the rear arm part (131), the rear arm part (131) can be folded by closing the side wall of the machine body (1), and the front arm part (132) is clamped between the rear arm part (131) and the side wall of the machine body (1); the foldable undercarriage (2) comprises a first folding support (20) located on one side of the undercarriage (1) and a second folding support (30) corresponding to the first folding support (20) and located on the other side of the undercarriage (1), and two pull rods (27) are connected between the first folding support (20) and the second folding support (30); the first folding bracket (20) can be folded towards the second folding bracket (30) to be parallel to the pull rod (27); the second folding bracket (30) can be folded towards the first folding bracket (20) to be parallel to the pull rod (27).

2. A fully folded configuration hexa-rotor drone according to claim 1, characterized in that the end-supported propeller (5) of the first boom (31) is located above and arranged upwards of the first boom (31), and the end-supported propeller (5) of the second boom (32) is located below and arranged downwards of the second boom (32).

3. The six-rotor unmanned aerial vehicle with the fully-folded structure according to claim 1, wherein a first folding mechanism (11) is arranged at the joint of the first cantilever (31) and the fuselage (1), and two first cantilevers (31) on the same side of the fuselage (1) can be folded through the first folding mechanism (11).

4. The six-rotor unmanned aerial vehicle with a fully-folded structure according to claim 1, wherein a second folding mechanism (12) is arranged at the joint of the second cantilever (32) and the fuselage (1); a third folding mechanism (13) is arranged in the middle of the cantilever (32); the rear arm portion (131) is foldable by the second folding mechanism (12), and the front arm portion (132) is foldable by the third folding mechanism (13).

5. A fully folded configuration hexa-rotor drone according to claim 1, 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).

6. A fully-folded configuration hexa-rotor drone according to claim 1, characterized in that the first folding cradle (20) is provided, below the position of connection with the tie-rod (27), with a fourth folding mechanism (212), by means of which fourth folding mechanism (212) the first folding cradle (20) can be folded; the second folding support (30) is provided with a fifth folding mechanism (213) below a position connected with the pull rod (27), and the second folding support (30) can be folded through the fifth folding mechanism (213).

7. A fully folded configuration hexa-rotor drone according to claim 6, characterized in that the vertical distance of the fourth folding mechanism (212) from the tie rod (27) is less than the vertical distance of the fifth folding mechanism (213) from the tie rod (27).

8. A fully folded configuration hexa-rotor drone according to claim 1, characterized in that the first folding bracket (20) is folded next to the tie-rod (27); the second folding support (30) is adjacent to the first folding support (20) after being folded, and the first folding support (20) is clamped between the second folding support (30) and the pull rod (27).

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