Multi-rotor unmanned aerial vehicle framework structure

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle framework structure which comprises a rotating pedestal, the rotating pedestal is composed of a first rotating piece, a second rotating piece and a middle piece which are matched on a longitudinally-arranged rotating shaft, and plugs are arranged at the front ends and the rear ends of the first rotating piece, the second rotating piece and the middle piece respectively; the cantilevers are of a plurality of arranged pipe body structures, the corresponding plugs are fixedly sleeved with one ends of the cantilevers, and rotor motors are arranged at the ends, away from the rotating pedestal, of the cantilevers; the plurality of flexible belts are respectively connected to the middle parts of any two adjacent cantilevers at the front end and the rear end of the corresponding rotating pedestal; a lock head and a lock seat which are matched with each other are arranged in the middle of the connecting belt, and the two ends of the connecting belt are connected to the middles of the two cantilevers on the outer side of the front end and the outer side of the rear end of the rotating pedestal. No matter the framework structure is in an unfolded state or a folded state, the rigid structure of the cantilever cannot be damaged all the time, and therefore the flying stability and the bearing capacity are guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a skeleton structure of a multi-rotor UAV. Background Art

[0002] Multi-rotor drones are a common type of drone in the drone industry. They typically consist of four or more arms with rotors mounted on them to provide lift. Multi-rotor drones are relatively large, making them difficult to transport and operate. Therefore, to facilitate portability, multi-rotor drones are designed to be foldable. However, most existing foldable multi-rotor drones are relatively complex, and the folding arms affect their strength to a certain extent. This is especially true when there is clearance, which not only affects the payload but also the control stability of the drone. Utility Model Content

[0003] The utility model provides a multi-rotor UAV skeleton structure, which is easier to place and carry than the rectangular space formed by the traditional UAV after folding and storing. Moreover, the rigid structure of the cantilever will not be destroyed whether in the unfolded or stored state, thereby ensuring the flight stability and carrying capacity.

[0004] In order to achieve the above-mentioned purpose, the present invention provides the following technical solutions: a multi-rotor UAV skeleton structure, comprising: a rotating base, the rotating base is composed of a first rotor, a second rotor and an intermediate plate fitted on a longitudinally arranged rotating shaft, and the front and rear ends of the first rotor, the second rotor and the intermediate plate are respectively provided with plugs; a cantilever, the cantilever is a plurality of arranged tubular structures, and is respectively fixedly sleeved on the corresponding plugs through one end, and each cantilever is provided with a rotor motor at one end away from the rotating base; a flexible belt, the flexible belt is arranged in plurality, and is respectively connected to the middle parts of any two adjacent cantilevers at the front and rear ends of the corresponding rotating base; a connecting belt, the middle part of the connecting belt is provided with a lock head and a lock seat that cooperate with each other, and the two ends of the connecting belt are connected to the middle parts of the two cantilevers on the outside of the front end and the outside of the rear end of the rotating base.

[0005] Preferably, the cantilevers located at the front end and the rear end of the rotating pedestal are parallel to each other in a closed state.

[0006] Preferably, each of the lock heads and the lock seats is provided with an adjustment buckle, and the connecting belt is connected to the corresponding lock head and the lock seat via the adjustment buckle.

[0007] Preferably, the first rotating blade, the second rotating blade and the intermediate blade are respectively a plurality of flat plate structures, which are alternately overlapped and fitted on the rotating shaft.

[0008] Preferably, each of the cantilevers is connected to the rotating base via a through-pin passing through the corresponding plug, and a gasket for filling the interlayer gap is provided in the same plug.

[0009] The beneficial effects of the present invention are as follows: the drone frame adopts a rotating folding scheme. Unlike traditional folding schemes, the drone cantilever of this scheme remains a single-piece structure after folding. The space occupied by the drone is reduced only by changing the angle, forming a long rectangular storage space. Compared with the rectangular space formed by the folding and storage of traditional drones, the drone cantilever is easier to place and carry. Moreover, the rigid structure of the cantilever is always intact, whether in the unfolded or stored state, thus ensuring flight stability. The structure is used in a six-rotor drone. In the unfolded state, the cantilever is stretched to both sides, causing the angle between the first and second rotors of the rotating base and the middle plate to change, and the unfolding angle is maintained under the constraint of the flexible belt. When the cantilever is unfolded, the two connecting belts corresponding to the front and rear ends of the rotating base are connected by a lock head and a lock seat, thereby forming a closed loop structure with the flexible belt, thereby ensuring the angular stability of each cantilever. The connecting belt is adjustable in length by an adjustment buckle, thereby ensuring the positioning tension of the cantilever. The multi-piece rotating base improves its own strength and reduces the left-right height difference, making the UAV's flight more stable. At the same time, the gasket ensures the connection strength between the cantilever and the plug, reduces the vertical swing amplitude of each cantilever, and further improves the UAV's carrying capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0011] Figure 1 This is a schematic diagram of the skeleton structure of the utility model in an expanded state;

[0012] Figure 2 This is a schematic diagram of the skeleton structure of the utility model in a contracted state;

[0013] Figure 3 This is an exploded schematic diagram of the rotating pedestal of the utility model.

[0014] In the figure: 1. Rotating base; 2. First rotary vane; 3. Second rotary vane; 4. Intermediate vane; 5. Plug; 6. Cantilever; 7. Rotor motor; 8. Flexible belt; 9. Connecting belt; 10. Lock head; 11. Lock seat; 12. Adjustment buckle. DETAILED DESCRIPTION

[0015] The following will be combined with the accompanying drawings of the present invention to clearly and completely describe the technical solution of the present invention. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0016] according to Figure 1 、 Figure 2 、 Figure 3 As shown, a multi-rotor drone skeleton structure comprises: a rotating base 1, the rotating base 1 being composed of a first rotor 2, a second rotor 3, and an intermediate plate 4 fitted on a longitudinal rotating shaft, wherein the first rotor 2, the second rotor 3, and the intermediate plate 4 are provided with plugs 5 at their front and rear ends; cantilevers 6, the cantilevers 6 being a plurality of tubular structures, each of which is fixedly sleeved on a corresponding plug 5 at one end, and each cantilever 6 having a rotor motor 7 at its end away from the rotating base 1; a plurality of flexible belts 8, each of which is connected to the middle of any two adjacent cantilevers 6 at the front and rear ends of the rotating base 1; and a connecting belt 9, the middle of which is provided with a lock head 10 and a lock seat 11 that cooperate with each other, and the ends of the connecting belt 9 being connected to the middle of the two cantilevers 6 at the front and rear ends of the rotating base 1. In the closed state, the cantilevers 6 at the front and rear ends of the rotating base 1 are parallel to each other.

[0017] Through the above structure, the drone skeleton adopts a rotating folding scheme. Unlike the traditional folding scheme, the drone cantilever 6 of this scheme remains an integrated structure after folding. Only by changing the angle, its space occupancy is reduced, and a long strip of storage space is formed. Compared with the rectangular space formed by the folding and storage of the traditional drone, it is easier to place and carry. Moreover, whether in the unfolded or stored state, the rigid structure of the cantilever 6 is always intact, thus ensuring flight stability. The structure is used in a six-rotor drone. In its unfolded state, by stretching the cantilever 6 to both sides, the angle between the first rotor 2 and the second rotor 3 of the rotating base 1 and the intermediate plate 4 is changed respectively, and the unfolding angle is maintained under the constraint of the flexible belt 8. When the cantilever 6 is unfolded, the two connecting belts 9 corresponding to the front and rear ends of the rotating base 1 are connected by the lock head 10 and the lock seat 11, so that the connecting belt 9 and the flexible belt 8 form a closed loop structure, thereby ensuring the angular stability of each cantilever 6. In the storage state, the connecting straps 9 at the front and rear ends of the rotating base 1 can be locked by the cooperation between the lock head 10 and the lock base 11, thereby further facilitating transportation and packaging.

[0018] Each of the lock heads 10 and the lock seats 11 is provided with an adjustment buckle 12 , and the connecting belt 9 is connected to the corresponding lock head 10 and the lock seat 11 via the adjustment buckle 12 .

[0019] With this arrangement, the length of the connecting belt 9 is adjusted through the adjusting buckle 12 , thereby ensuring the positioning tension of the cantilever 6 .

[0020] The first rotating blade 2, the second rotating blade 3, and the intermediate blade 4 are each a plurality of flat plate structures, alternately overlapping and fitting onto the rotating shaft. Each cantilever 6 is connected to the rotating base 1 via a through-pin extending through the corresponding plug 5, and each plug 5 is provided with a gasket to fill the gap between the interlayers.

[0021] Through this arrangement, the rotating base 1 with a multi-piece structure improves its own strength and reduces the left-right height difference, thereby making the flight of the UAV more stable. At the same time, the connection strength between the cantilever 6 and the plug 5 is guaranteed under the action of the gasket, reducing the vertical swing amplitude of each cantilever 6, and further improving the carrying capacity of the UAV.

[0022] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any modifications or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A multi-rotor UAV skeleton structure, characterized in that ,include: A rotating base (1), the rotating base (1) is composed of a first rotating blade (2), a second rotating blade (3) and an intermediate blade (4) which are matched on a vertical rotating shaft, and plugs (5) are respectively provided at the front and rear ends of the first rotating blade (2), the second rotating blade (3) and the intermediate blade (4); A cantilever (6), wherein the cantilever (6) is a plurality of tubular structures, and each cantilever is fixedly sleeved on the corresponding plug (5) through one end, and a rotor motor (7) is provided at one end of each cantilever (6) away from the rotating platform (1); A flexible belt (8), wherein the flexible belt (8) is provided in a plurality and is respectively connected to the middle portions of any two adjacent cantilevers (6) at the front end and the rear end of the corresponding rotating pedestal (1); A connecting belt (9) is provided with a lock head (10) and a lock seat (11) that cooperate with each other in the middle of the connecting belt (9), and the two ends of the connecting belt (9) are connected to the middle of the two cantilevers (6) on the outer front end and the outer rear end of the rotating platform (1).

2. The multi-rotor UAV skeleton structure according to claim 1, characterized in that: The cantilevers (6) located at the front end and the rear end of the rotating pedestal (1) are parallel to each other in a closed state.

3. The multi-rotor UAV skeleton structure according to claim 1, characterized in that: Each of the lock heads (10) and the lock seats (11) is provided with an adjustment buckle (12), and the connecting belt (9) is connected to the corresponding lock head (10) and the lock seat (11) via the adjustment buckle (12).

4. The multi-rotor UAV skeleton structure according to claim 1, characterized in that: The first rotating blade (2), the second rotating blade (3) and the intermediate blade (4) are respectively a plurality of flat plate structures, and are alternately overlapped and matched on the rotating shaft.

5. The multi-rotor UAV skeleton structure according to claim 4, characterized in that: Each of the above The cantilever (6) is connected to the rotating pedestal (1) through a through-nail that passes through the corresponding plug (5). Furthermore, a gasket for filling the gap between the layers is provided in the same plug (5).

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