CN220640237U

CN220640237U - Folding locking mechanism of power arm of unmanned aerial vehicle

Info

Publication number: CN220640237U
Application number: CN202321343657.9U
Authority: CN
Inventors: 王忠义; 李志科
Original assignee: Liaoning Aerospace Hongtu Drone Technology Co ltd
Current assignee: Liaoning Aerospace Hongtu Drone Technology Co ltd
Priority date: 2023-05-30
Filing date: 2023-05-30
Publication date: 2024-03-22
Anticipated expiration: 2033-05-30

Abstract

The utility model discloses a folding locking mechanism of a power arm of an unmanned aerial vehicle, which comprises a first folding component, a second folding component and a folding component locking piece, wherein one ends of the first folding component and the second folding component are connected through a rotating shaft screw, and the other ends of the first folding component and the second folding component are detachably connected through the folding component locking piece; the first folding assembly and the second folding assembly are respectively provided with an installation through hole, and the first folding assembly and the second folding assembly are respectively provided with a locking mechanism. Through the setting of the folding subassembly of both sides freely dismouting, realize the free unblock folding between unmanned aerial vehicle power arm and the middle section wing. In the whole process, the locking or folding mode is simple and quick, and the operation is more accurate and the placement is more stable. Simultaneously, the assembled spring, the folding assembly locking piece and the guide inclined plane promote the unfolding time of the unmanned aerial vehicle, and the problem that a traditional bolt connection power arm is easy to loosen is also solved.

Description

Folding locking mechanism of power arm of unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a folding and locking mechanism of a power arm of an unmanned aerial vehicle.

Background

Four rotors of unmanned aerial vehicle, through power arm carbon tube and fuselage fixed connection, the carbon tube of its power arm is an integral, and the mode of equipment is pegged graft the middle-end of carbon tube on unmanned aerial vehicle middle section wing, and rethread bolt lock, this kind of mode needs screw up the bolt, wastes time and energy, and unmanned aerial vehicle expansion time is longer, if the bolt does not screw up, the power arm can rock to influence flight quality.

Disclosure of Invention

The utility model aims to provide a folding and locking mechanism for a power arm of an unmanned aerial vehicle, so as to reduce unfolding time and storage space, and avoid the problem that shaking exists after the power arm is installed to influence flight.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the folding locking mechanism of the power arm of the unmanned aerial vehicle comprises a first folding component, a second folding component and a folding component locking block, wherein one ends of the first folding component and the second folding component are connected through a rotating shaft screw, and the other ends of the first folding component and the second folding component are detachably connected through the folding component locking block;

the first folding assembly and the second folding assembly are respectively provided with an installation through hole, and the first folding assembly and the second folding assembly are respectively provided with a locking mechanism.

Compared with the prior art, the utility model has the beneficial effects that: through the setting of the folding subassembly of both sides freely dismouting, realize the free unblock or folding between unmanned aerial vehicle power arm and the middle section wing. In the whole process, the locking or folding mode is simple and quick, and the operation is more accurate and the placement is more stable.

Simultaneously, the assembled spring, the folding assembly locking piece and the guide inclined plane shorten the separation time of the power arm and the middle section wing of the unmanned aerial vehicle, and also solve the problem that the traditional bolt connection power arm is easy to loosen.

Drawings

Fig. 1 is a schematic diagram of an assembled structure of a folding and locking mechanism of a power arm of an unmanned aerial vehicle.

Fig. 2 is a schematic diagram of a folding and locking mechanism of an unmanned aerial vehicle power arm after being disassembled.

Fig. 3 is a schematic structural view of a second folding assembly according to the present utility model.

Fig. 4 is a schematic structural view of a first folding assembly according to the present utility model.

Fig. 5 is a schematic view of the second folding assembly of the present utility model when the folding assembly locking piece is assembled.

FIG. 6 is a schematic illustration of the present utility model connecting a power arm with a midspan wing.

Fig. 7 is a schematic view of the folding assembly locking block of the present utility model mated with the arcuate flap guide ramp.

1. A first folding component; 2. a second folding assembly; 3. a rotation shaft screw; 4. positioning protrusions; 5. a positioning groove; 6. folding the assembly locking piece; 7. a locking piece screw; 8. a threaded hole; 9. folding the assembly knob; 10. a mounting plate; 11. a notch; 12. positioning and perforating; 13. mounting through holes; 14. installing a round hole; 15. a gasket; 16. a power arm; 17. a middle wing.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-5, the present utility model provides a technical solution: the utility model provides a folding locking mechanism of unmanned aerial vehicle power arm, includes first folding subassembly 1, second folding subassembly 2 and folding subassembly locking piece 6, the one end of first folding subassembly 1 and second folding subassembly 2 is passed through rotation axis screw 3 and is connected for both can be along rotation axis screw 3 free rotation. When the unmanned aerial vehicle is not in use, keep first folding subassembly 1 and second folding subassembly 2 separately to reduce the holistic occupation space of device.

The first folding component 1 and the second folding component 2 are of diamond structures, the first folding component 1 and the second folding component 2 are provided with mounting round holes 14, and the mounting round holes 14 are used for assisting the middle section wings 17 and the power arms 16 of the unmanned aerial vehicle to be fixed. The contact surfaces of the first folding assembly 1 and the second folding assembly 2 on the rotating shaft screw 3 are provided with gaskets 15, so that abrasion is reduced. While the material of the spacer 15 is not the same as the first folding member 1 and the second folding member 2.

The other ends of the first folding component 1 and the second folding component 2 are detachably connected through the folding component locking piece 6, and after the first folding component 1 and the second folding component 2 are locked through the folding component locking piece 6, the unmanned aerial vehicle power arm 16 is kept stable, so that a flight task can be executed.

The first folding component 1 and the second folding component 2 are respectively provided with a mounting through hole 13, the mounting through holes 13 are used for respectively plugging power arms 16 and middle section wings 17 of the unmanned aerial vehicle (the unmanned aerial vehicle is provided with 4 power arms, each power arm is respectively provided with 1 propeller, the power arms 16 are connected with the middle section wings 17 through a folding locking mechanism, and the middle section wings 17 are connected with a machine body-see figure 6). The first folding component 1 and the second folding component 2 are respectively provided with a locking mechanism, and after the structure is spliced, the locking mechanisms are used for fixing the structure, so that the installation stability of the structure is ensured.

The locking mechanism comprises a pair of mounting plates 10, a notch 11 is formed in each mounting through hole 13, and a round hole is formed in each notch 11. Effect 1 of round hole: when the pair of mounting plates 10 lock the unmanned aerial vehicle parts through screws, the integral compression amount of the first folding assembly 1 and the second folding assembly 2 is increased, so that the locking contact area of the unmanned aerial vehicle parts in the mounting through holes 13 is increased, and the locking is firm; effect 2 of round mouth: the round holes are formed, so that stress concentration is avoided on the inner side of the notch 11, and the notch 11 is prevented from cracking.

The pair of mounting plates 10 are symmetrically arranged on two sides of the notch 11, positioning holes 12 are formed in the mounting plates 10, screws are inserted into the positioning holes 12, nuts are used for fixing the screws, and therefore the opening and closing angles of the notch 11 of the mounting through hole 13 can be fixed, and the unmanned aerial vehicle component in the mounting through hole 13 is locked.

The first folding subassembly 1 is equipped with the location protruding 4, the second folding subassembly 2 is equipped with constant head tank 5, and constant head tank 5 and the cooperation of location protruding 4, as shown in fig. 3 and 4, location protruding 4 and constant head tank 5 are semi-circular, and the laminating that both can be accurate. The folding assembly locking piece 6 is provided with a locking piece screw 7, the positioning protrusion 4 is provided with a threaded hole 8, the threaded hole 8 is matched with the locking piece screw 7, and at the moment, the folding assembly locking piece 6 is used for fixing the outer walls of the first folding assembly 1 and the second folding assembly 2, so that the assembly of the first folding assembly 1 and the second folding assembly 2 is completed, and further the middle wing 17 and the power arm 16 of the unmanned aerial vehicle are fixed. A folding assembly knob 9 is arranged outside the locking block screw 7, so that an operator can conveniently rotate the locking block screw 7. When the folding assembly knob 9 is rotated to enable the locking block screw 7 to be separated from the threaded hole 8, the middle section wing 17 and the power arm 16 of the unmanned aerial vehicle can be folded normally, so that the whole storage space of the unmanned aerial vehicle is reduced.

The outer side walls of the first folding component 1 and the second folding component 2 are respectively provided with arc-shaped petals, and the arc-shaped petals on two sides are symmetrically arranged and are conical after being combined. The inner cavity of the folding component locking piece 6 is matched with the arc-shaped valve; the positioning groove 5 and the positioning protrusion 4 are both arranged on the arc-shaped valve. The arc-shaped valve is provided with a spring, the spring is matched with the folding assembly locking piece 6, and when the locking piece screw 7 is separated from the threaded hole 8, the spring has the effect of accelerating the separation of the folding assembly locking piece 6. The outer side wall of the arc-shaped valve is provided with a guide inclined plane, so that the folding assembly locking piece 6 can be separated from the arc-shaped valve more smoothly, and molybdenum disulfide lubricating grease can be smeared between the folding assembly locking piece and the arc-shaped valve.

Working principle: when unmanned aerial vehicle uses, with the middle section wing 17 of power arm 16 and unmanned aerial vehicle fixed and aim at through-hole 13 of the installation of first folding subassembly 1 and second folding subassembly 2, with folding subassembly locking piece 6 lid in the arc lamella department of first folding subassembly 1 and second folding subassembly 2 and with locking piece screw 7 lock into screw hole 8 this moment, power arm 16 and unmanned aerial vehicle's middle section wing 17 are sharp, unmanned aerial vehicle can normal use.

When unmanned aerial vehicle accomodates, only need break away from screw hole 8 and locking piece screw 7, the spring pops up folding assembly locking piece 6 this moment, with power arm 16 and unmanned aerial vehicle's middle section wing 17 folding 90 and normally accomodate can.

Claims

1. The utility model provides a folding locking mechanism of unmanned aerial vehicle power arm which characterized in that: the folding device comprises a first folding component (1), a second folding component (2) and a folding component locking piece (6), wherein one ends of the first folding component (1) and the second folding component (2) are connected through a rotating shaft screw (3), and the other ends of the first folding component (1) and the second folding component (2) are detachably connected through the folding component locking piece (6);

the folding device is characterized in that the first folding component (1) and the second folding component (2) are respectively provided with an installation through hole (13), and the first folding component (1) and the second folding component (2) are respectively provided with a locking mechanism.

2. The unmanned aerial vehicle power arm fold and lock mechanism of claim 1, wherein: the first folding assembly (1) is provided with a positioning protrusion (4), the second folding assembly (2) is provided with a positioning groove (5), the positioning groove (5) is matched with the positioning protrusion (4), the folding assembly locking piece (6) is provided with a locking piece screw (7), the positioning protrusion (4) is provided with a threaded hole (8), and the threaded hole (8) is matched with the locking piece screw (7).

3. The unmanned aerial vehicle power arm fold and lock mechanism of claim 1, wherein: the locking mechanism comprises a pair of mounting plates (10), the mounting through holes (13) are provided with notches (11), round holes are formed in the inner sides of the notches (11), the pair of mounting plates (10) are symmetrically arranged on two sides of the notches (11), and positioning holes (12) are formed in the mounting plates (10).

4. The unmanned aerial vehicle power arm fold and lock mechanism of claim 1, wherein: the first folding component (1) and the second folding component (2) are of diamond structures, and the first folding component (1) and the second folding component (2) are provided with mounting round holes (14).

5. The unmanned aerial vehicle power arm fold and lock mechanism of claim 1, wherein: the contact surfaces of the first folding component (1) and the second folding component (2) on the rotating shaft screw (3) are provided with gaskets (15).

6. The unmanned aerial vehicle power arm fold and lock mechanism of claim 2, wherein: a folding assembly knob (9) is arranged outside the locking block screw (7).

7. The unmanned aerial vehicle power arm fold and lock mechanism of claim 2, wherein: the outer side walls of the first folding component (1) and the second folding component (2) are respectively provided with an arc-shaped valve, and the folding component locking piece (6) is matched with the arc-shaped valve;

the positioning groove (5) and the positioning protrusion (4) are both arranged on the arc-shaped valve.

8. The unmanned aerial vehicle power arm fold and lock mechanism of claim 7, wherein: the arc-shaped valve is provided with a spring which is matched with the folding component locking block (6);

the outer side wall of the arc-shaped valve is provided with a guide inclined plane, and molybdenum disulfide lubricating grease is smeared between the guide inclined plane and the folding assembly locking piece (6).