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

A fully foldable six-rotor unmanned aerial vehicle

technical field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle, in particular to a fully foldable six-rotor unmanned aerial vehicle whose cantilever and landing gear can be folded.

Background technique

Most of the current UAVs are multi-axis UAVs, such as four-axis, six-axis, etc. The take-off weight of the whole machine is very small, but the cantilever is very large, which brings certain difficulties to the transportation, carrying and storage of the UAV. . For example, CN 204587305 U discloses a multifunctional foldable eight-rotor electric unmanned aerial vehicle, which mainly solves the problems of the existing rotary-wing electric unmanned aerial vehicle with single purpose, complex structure and difficult transportation of the whole machine. The eight rotors of the above-mentioned prior art UAV are arranged around the body at equal angles, resulting in the application load carried on the body can only be set directly below the body, and because all directions are blocked by the rotor, the load can only be carried downward. To carry out operations, it is impossible to launch weapons or observe obliquely upwards, and it is only suitable for operations such as spraying below the drone as described in its manual.

In order to solve the above technical problems, CN 207550499 U proposes an electric unmanned aerial vehicle, comprising a fuselage, two landing gears and eight motors supported by eight cantilevers connected to the fuselage, wherein the lower part of the fuselage is arranged There is a longitudinal load channel, and two sides of the longitudinal load channel are respectively symmetrically arranged with a first group of four cantilevers and a second group of four cantilevers. By setting an unobstructed longitudinal load channel under the fuselage, the electric UAV of the prior art can conveniently set loads such as photoelectric pods and weapon launchers, and avoid interference with cantilevers and propellers during observation and weapon launch. , affecting the use and combat effectiveness, and improving the application scope of UAVs. In addition, the prior art reduces the volume after folding by setting an optimized overall layout structure, which facilitates the low-cost transportation of the UAV.

The above-mentioned prior art effectively overcomes the defects of the prior art, but there is still room for improvement. Especially when the folded volume of the UAV needs to be further reduced for quick disassembly and transportation, the existing UAV's folding structure still has room for further improvement.

Utility model content

The technical problem to be solved by the present invention is to provide a fully foldable six-rotor UAV to reduce or avoid the aforementioned problems.

In order to solve the above technical problems, the present utility model proposes a fully foldable six-rotor UAV, including a fuselage, a foldable landing gear and a foldable cantilever system supporting a motor, each motor is provided with a propeller, so the The cantilever system includes four first cantilevers extending obliquely outward from both sides of the head and tail of the fuselage, and two second cantilevers extending outward from both sides of the middle of the fuselage; The two first cantilevers on the same side of the fuselage can be folded relative to each other; the second cantilever is divided into a rear arm part and a front arm part by a third folding mechanism; the front arm part can be folded close to the rear arm part , the rear arm portion can be folded against the side wall of the fuselage, and the front arm portion is clamped between the rear arm portion and the side wall of the fuselage; the foldable landing gear includes A first folding bracket located on one side of the fuselage, and a second folding bracket located on the other side of the fuselage corresponding to the first folding bracket, and two folding brackets are connected between the first folding bracket and the second folding bracket A pull rod; the first folding bracket can be folded toward the second folding bracket to a state parallel to the pull rod; the second folding bracket can be folded toward the first folding bracket to a state parallel to the pull rod.

Preferably, the propeller supported by the end of the first cantilever is located above the first cantilever and arranged upward, and the propeller supported by the end of the second cantilever is located below the second cantilever and arranged downward.

Preferably, a first folding mechanism is provided at the connection between the first cantilever and the fuselage, and the two first cantilevers on the same side of the fuselage can be folded by the first folding mechanism.

Preferably, a second folding mechanism is provided at the connection between the second cantilever and the fuselage; a third folding mechanism is provided in the middle of the cantilever; the rear arm portion can be folded by the second folding mechanism, so The forearm portion is foldable by the third folding mechanism.

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

Preferably, the first folding bracket is provided with a fourth folding mechanism below the position connected with the draw rod, and the first folding bracket can be folded by the fourth folding structure; the second folding bracket is connected to A fifth folding structure is provided below the position where the pull rod is connected, and the second folding bracket can be folded by 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; the second folding bracket is adjacent to the first folding bracket after being folded, and clamps the first folding bracket between the second folding bracket and the second folding bracket. between the rods.

In the fully foldable six-rotor UAV of the present application, the six cantilevers of the cantilever system can be folded in one section and two sections respectively, and the two folding brackets of the landing gear can also be folded relative to each other, so that the six-rotor of the present application can be folded. The overall size of the UAV can be smaller, so the volume of the UAV can be greatly reduced, which is convenient for the storage and transportation of the UAV.

Description of drawings

The following drawings are only intended to illustrate and explain the present invention schematically, and do not limit the scope of the present invention. in,

FIG. 1 shows a schematic three-dimensional structure diagram of a fully foldable six-rotor UAV according to a specific embodiment of the present invention;

Figures 2 and 3 show schematic diagrams of the folded state of the fully-folded six-rotor UAV shown in Figure 1 from different perspectives;

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

5 and 6 show schematic diagrams of the folded state of the foldable landing gear shown in FIG. 4 from different viewing angles.

Detailed ways

In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts use the same reference numerals.

As described in the background art, the present application aims at the shortcomings of the electric unmanned aerial vehicle disclosed in the prior art CN 207550499 U, and proposes a fully foldable six-rotor unmanned aerial vehicle with an improved structure, which can obtain a smaller structure size, and The folded volume of the drone is smaller for quick disassembly and transportation.

That is, in order to achieve the above purpose, the present application provides a fully folded six-rotor UAV, as shown in Figures 1-3, wherein Figure 1 shows a fully folded drone according to a specific embodiment of the present invention Schematic diagram of the three-dimensional structure of the six-rotor UAV of the structure; Figures 2 and 3 show the schematic diagram of the folded state of the fully-folded structure of the six-rotor UAV shown in Figure 1 from different perspectives.

Referring to FIGS. 1-3 , the fully foldable six-rotor UAV of the present application includes a fuselage 1, two foldable landing gears 2, and a foldable cantilever system 3 supporting motors 4, each of which is provided with a propeller 5. The fuselage 1 is generally elongated, and a longitudinal load channel 6 is arranged below it. As shown by the dotted line in FIG. 1 , the fuselage 1 is arranged parallel to the longitudinal load channel 6 . By setting an unobstructed longitudinal load channel 6 below the fuselage 1 of the fully folded six-rotor UAV, it is beneficial to set loads such as photoelectric pods and weapon launchers, and avoid the cantilever system 3 during observation and weapon launch. Interfering with the propeller 5, etc., affects the use and combat effectiveness, and improves the application scope of the UAV. In addition, due to the provision of the longitudinal load channel 6, the cantilever system 3 and the motor 4 on it are distributed on both sides of the longitudinal load channel 6, that is, both sides of the fuselage 1, so that a larger range can be obtained in the longitudinal direction of the fuselage The load mount point is easy to expand the load layout.

A difference between the present application and the prior art is that the cantilever system 3 of the fully foldable six-rotor UAV of the present application is foldable, and includes a slanting arm system 3 extending obliquely outward from the head and tail sides of the fuselage 1 . Four first cantilevers 31, and two second cantilevers 32 extending outward from both sides of the middle of the fuselage 1, wherein the propeller 5 supported by the end of the first cantilever 31 is located above the first cantilever 31 and faces upwards Arrangement, the propeller 5 supported by the end of the second cantilever 32 is located below the second cantilever 32 and is arranged downward.

In the fully folded six-rotor UAV of the present application, the distance between the four obliquely outwardly extending first cantilevers 31 is the largest, and there is no problem of interference between the propellers 5 on the four first cantilevers. The propellers 5 on 31 can all be arranged upward. The two second cantilevers 32 are located in the middle of the fuselage 1, and the distance between them and the two first cantilevers 31 on the same side is relatively small, and the propellers 5 on them are likely to interfere with the propellers on the adjacent first cantilevers 31, Therefore, the downward arrangement of the propellers 5 on the two second cantilevers 32 can reduce interference, which is conducive to reducing the length of the cantilevers, and the UAV can obtain a smaller structural size as a whole, so the volume of the UAV can be greatly reduced, which is convenient for no use. Human-machine storage and transportation.

Further, the propellers 5 on the first cantilever 31 and the second cantilever 32 are arranged in opposite directions, which further facilitates the folding of the drone. As shown in FIGS. 2 and 3 , a first folding mechanism 11 is provided at the connection between the first cantilever 31 and the fuselage 1 , and the two first cantilevers 31 located on the same side of the fuselage 1 can be connected to each other through the first folding mechanism 11 Fold relative to each other. In order to prevent the folded structures from interfering with each other, it can be seen from the figure that when the two first cantilevers 31 on the same side are folded toward each other, there is a slight upward angle to prevent the ends of the folded first cantilevers 31 from hitting the other. The root of the first cantilever 31 is more beneficial for the folded first cantilever 31 to be as close to the side wall of the fuselage 1 as possible, which is beneficial to obtain a smaller folded volume.

Further, a second folding mechanism 12 is provided at the connection between the second cantilever 32 and the fuselage 1 ; a third folding mechanism 13 is provided in the middle of the cantilever 32 , and the second cantilever 32 is divided by the third folding mechanism 13 into a rear arm portion 131 and Forearm part 132; wherein, the section close to the fuselage 1 is the rear arm section 131, and the section away from the fuselage 1 is the forearm section 132, as shown in the figure. The front arm part 132 can be folded close to the rear arm part 131 by the third folding mechanism 13 , and the rear arm part 131 can be folded close to the side wall of the fuselage 1 by the second folding mechanism 12 , and the forearm part 132 can be clamped between the rear arm part 131 and the rear arm part 131 . between the side walls of the fuselage 1. In the illustrated embodiment, the second cantilever 32 is folded toward the tail of the drone as a whole. Of course, according to the actual situation, the second cantilever 32 can also be set to be folded toward the nose of the drone as a whole.

In the above embodiment, the second cantilever 32 adopts a two-stage folding method. The forearm portion 132 is folded toward the rear arm portion 131 first, and then the rear arm portion 131 is folded toward the fuselage with the forearm portion 132 . Since the propeller 5 at the end of the second cantilever 32 is disposed downward, after the second cantilever 32 is folded twice, the propeller 5 at the end of the second cantilever 32 can perfectly avoid the first cantilever 31, avoiding the problem of mutual interference of the folded structures. In addition, in a preferred embodiment, the vertical installation position of the second cantilever 32 on the fuselage 1 is lower than the vertical installation position of the first cantilever 31 on the fuselage 1, so that the second cantilever 32 can be set as a whole Folded below the first cantilever 31, without interference, the second cantilever 32 can be as close as possible to the side wall of the fuselage 1 after being folded for the second time, which is beneficial to reduce the folded volume.

In the fully foldable six-rotor UAV of the present application, the six cantilevers of the cantilever system are divided into two groups to be folded, the first cantilevers with larger intervals are folded relative to each other, and the second cantilever in the middle of the fuselage adopts two-stage folding, which can The stacked folding structure shown in Figures 2 and 3 is formed, which avoids the defects of high height and difficult transportation of the existing cantilever folded-down hanging structure, reduces the volume of the UAV, and facilitates storage and transportation.

In addition, those skilled in the art should understand that the first folding mechanism 11, the second folding mechanism 12 and the third folding mechanism 13 can adopt any existing folding structure suitable for the connection and folding of rods, such as the folding of a foldable bicycle device, etc. can be used for the concept of the present application.

Further, the fully foldable six-rotor UAV of the present application also has a foldable landing gear.

As shown in FIG. 4 , as mentioned above, the foldable landing gear of the present application is used to be installed on both sides below the fuselage 1 of the UAV, that is, two sides of the fuselage 1 are respectively provided with a landing gear 2 symmetrically , a tie rod 27 for reinforcing the structure is also added between the two landing gears 2 relative to the prior art. Wherein, FIG. 4 shows a schematic diagram of a foldable landing gear according to a specific embodiment of the present application.

In order to facilitate the description of the structure and folding principle of the foldable landing gear of the present application, in the following description, the landing gear located on one side of the fuselage 1 is respectively defined as the first folding bracket 20 , and the landing gear corresponding to the first folding bracket 20 is defined as the first folding bracket 20 . The landing gear on the other side of the fuselage 1 is the second folding bracket 30 . The structures of the first folding bracket 20 and the second folding bracket 30 are basically the same, and two tie rods 27 are connected between them. That is to say, after definition, the foldable landing gear of the present application includes a first folding bracket 20 located on one side of the fuselage 1 , and a first folding bracket 20 located on the other side of the fuselage 1 corresponding to the first folding bracket 20 . Two folding brackets 30 , two pull rods 27 are connected between the first folding bracket 20 and the second folding bracket 30 . The above structure is actually basically the same as the landing gear of the UAV mentioned in the background art, the difference is that the first folding bracket 20 and the second folding bracket 30 of the foldable landing gear of the present application both have foldable Moreover, the first folding bracket 20 and the second folding bracket 30 can be folded in a specific manner, which can significantly reduce the volume of the landing gear.

4-6, the improved landing gear of the present application with respect to the prior art will be further described in detail. As for the structures not explained in the description of the present application, those skilled in the art can refer to the accompanying drawings and the prior art. understand. 5 and 6 show schematic diagrams of the folded state of the foldable landing gear shown in FIG. 4 from different perspectives.

As shown in the figure, in a specific embodiment of the present application, the first folding bracket 20 is provided with a fourth folding mechanism 212 below the position where it is connected with the pull rod 27 , and the first folding bracket 20 can be oriented toward the first folding bracket 212 through the fourth folding mechanism 212 The second folding bracket 30 is folded to a state substantially parallel to the pulling rod 27 ; the second folding bracket 30 is provided with a fifth folding mechanism 213 below the position connected to the pulling rod 27 , and the second folding bracket 30 can pass through the fifth folding mechanism 213 It is folded toward the first folding bracket 20 to a state substantially parallel to the pull rod 27 . The state after the first folding bracket 20 and the second folding bracket 30 are folded is shown in FIGS. 5 and 6 . Wherein, the fourth folding mechanism 212 and the fifth folding mechanism 213 may adopt any existing folding structure suitable for rod connection and folding, such as a folder for a foldable bicycle, etc., which can be used in the concept of the present application.

In the specific embodiment shown in FIGS. 5 and 6 , the first folding bracket 20 is adjacent to the pull rod 27 after being folded; the second folding bracket 30 is adjacent to the first folding bracket 20 after being folded, and clamps the first folding bracket 20 on the first folding bracket 20 . Two fold between the bracket 30 and the pull rod 27 . That is, in the illustrated embodiment, the first folding bracket 20 is folded first, and then the second folding bracket 30 is folded. In order to ensure that this folding method does not interfere, preferably, the vertical distance between the fourth folding mechanism 212 and the pull rod 27 is smaller than the vertical distance between the fifth folding mechanism 213 and the pull rod 27 .

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

Also in order to avoid folding interference, it is preferable that the fourth folding mechanism 212 on the two vertical bars 21 of the first folding bracket 20 and the corresponding pulling bar 27 are located in the same plane. The fifth folding mechanisms 212 on the two vertical rods 21 of the second folding bracket 30 and the corresponding pull rods 27 are located in the same plane.

To sum up, the present application provides folding structures on the first folding bracket and the second folding bracket on both sides of the fuselage of the drone, so that the first folding bracket and the second folding bracket can be folded relative to each other, and the folding Afterwards, the first foldable bracket and the second foldable bracket can be substantially parallel to the pull rod between them, which greatly reduces the volume of the landing gear. Since the foldable landing gear of the present application does not need to be disassembled from the UAV, it can be directly folded to reduce the volume, and it is also very convenient to restore from the folded state to the use state, which greatly improves the storage and transportation efficiency of the UAV.

In addition, in the fully foldable six-rotor UAV of the present application, the six cantilevers of the cantilever system can be folded in one section and two sections respectively, and the two folding brackets of the landing gear can also be folded relative to each other, so that the The six-rotor UAV can obtain a smaller structural size as a whole, which can greatly reduce the volume of the UAV and facilitate the storage and transportation of the UAV.

Those skilled in the art should understand that although the present invention is described in terms of multiple embodiments, not every embodiment only includes an independent technical solution. This description in the description is only for the sake of clarity, and those skilled in the art should understand the description as a whole, and regard the technical solutions involved in each embodiment as being able to be combined into different embodiments to understand the present utility. A new range of protection.

The above descriptions are only exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention. Any equivalent changes, modifications and combinations made by any person skilled in the art without departing from the concept and principle of the present invention shall fall within the protection scope of the present 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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