Up-and-down superimposable unmanned aerial vehicle propeller mechanism

Abstract

The application discloses an upper and lower overlapped unmanned aerial vehicle propeller mechanism, and belongs to the technical field of aircraft manufacturing, installation and maintenance. The mechanism comprises a motor and at least two propeller bodies. Each propeller body comprises a fixed part at the root. The plurality of propeller bodies are coaxially arranged in layers, and the fixed parts at the roots of the plurality of propeller bodies are kept in a coaxial state by a concave-convex limiting assembly. The limiting assembly comprises a propeller root seat, a fixed shell and an upper propeller root seat. The upper and lower overlapped unmanned aerial vehicle propeller mechanism has the advantages that each blade comprises its own fixed part at the root, the plurality of blades are coaxially arranged in layers, a corresponding concave-convex limiting structure is designed, the blades are automatically unfolded and positioned by centrifugal force in a flight state, the blades can be overlapped and folded in a storage and transportation state, the occupied area of the aircraft is reduced, and the portability is improved. In addition, a solution is provided for folding three or more propellers, and the blank in the field is filled.

Description

Technical Field

[0001] This invention relates to aircraft propeller mechanisms, specifically to an overlapping unmanned aerial vehicle (UAV) propeller mechanism, belonging to the field of aircraft manufacturing, installation, and maintenance technology. Background Technology

[0002] Existing aircraft propellers are divided into two-bladed propellers and multi-bladed propellers, and their external features are divided into one-piece molding (see the instruction manual). Figure 1 ) and coplanar folding type (see instruction manual appendix) Figure 2 With the increasing use of small aircraft, especially multi-rotor drones, higher demands have been placed on their portability. As a result, folding propellers are being adopted more and more often than one-piece propellers.

[0003] However, since it is a planar fold, it still occupies a large area after folding, which limits the size of the drone in storage and transportation. At the same time, this folding method is only applicable to two-bladed propellers. Folding structures for multi-bladed propellers are not yet available on the market, which makes it difficult to design portable drones with multi-bladed propellers.

[0004] To address this issue, we propose an overlapping UAV propeller mechanism. Summary of the Invention

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] An overlapping UAV propeller mechanism includes a motor and at least two blade bodies. Each blade body includes a fixed part at its root. Multiple blade bodies are arranged coaxially in layers, and the fixed parts at the roots of the multiple blade bodies are fastened together by concave-convex limiting components to maintain a coaxial state. The limiting components include a lower blade root seat, a fixed housing for the upper and lower blade root seats, and an upper blade root seat.

[0007] As a further preferred option, it also includes:

[0008] The lower blade assembly includes upper and lower blade root seat fixing housings, lower blade root seat and blade body stacked from top to bottom. The lower blade root seat is connected to the lower blade fixing screw, and the lower blade fixing screw passes through the lower blade root seat and the blade body and is fixed to the motor.

[0009] The upper blade assembly includes a blade body and an upper blade root seat. The root fixing part of the blade body is provided with a set of upper blade fixing screws. A locking nut is connected to the upper blade fixing screws, and the blade body is fixed to the upper blade root seat by the upper blade fixing screws and the locking nut.

[0010] As a further preferred embodiment, the bottom end of the upper and lower blade root seat fixing shell is constructed with an annular flange one, and the outer edge surface of the lower blade root seat is constructed with an annular flange two, and the flange one of the upper and lower blade root seat fixing shell is engaged below the flange two of the lower blade root seat.

[0011] As a further preferred embodiment, the upper blade assembly and the lower blade assembly are stacked and installed. The outer edge of the upper and lower blade root seat fixing housing is provided with threaded holes for the installation of housing fixing screws. The housing fixing screws are threaded into the upper and lower blade root seat fixing housing, and their ends are threaded into the upper blade root seat of the upper blade assembly.

[0012] As a further preferred embodiment, the lower outer edge of the upper blade root seat is designed with a quarter-circle arc-shaped boss, and the upper outer edge of the lower blade root seat is designed with a three-quarter-circle arc-shaped groove, and the upper blade root seat and the lower blade root seat are coupled through the arc-shaped boss and the arc-shaped groove.

[0013] Compared with existing technologies, the present invention has the following advantages:

[0014] 1. Multiple blade bodies can be stacked and folded vertically. The length of the folded propeller is half the length of the integrated two-blade propeller, and the width is half the width of the folded blade, which greatly improves the portability of the aircraft.

[0015] 2. It fills the gap in multi-bladed foldable propellers, resolving the contradiction between multi-bladed propellers and portable design while meeting the power and propeller efficiency requirements of drones.

[0016] 3. In the event of any blade being damaged by collision, the outer fixed shell of the propeller mechanism can be removed, and the damaged blade body can be replaced with a new blade, which can save blade costs and is relatively convenient. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a one-piece molded propeller in the prior art;

[0018] Figure 2 This is a schematic diagram of a planar folding propeller in the prior art;

[0019] Figure 3 This is an axonometric view of the three blades of the present invention.

[0020] Figure 4 This is a side view of the folded three-bladed propeller of the present invention;

[0021] Figure 5 This is a side view of the double-bladed propeller folding mechanism of the present invention;

[0022] Figure 6This is a schematic diagram of the upper blade assembly structure layout of the present invention;

[0023] Figure 7 This is a schematic diagram of the lower blade assembly structure layout of the present invention;

[0024] Figure 8 This is a schematic diagram of the overall cross-sectional structure of the present invention;

[0025] Figure 9 This is an overall isometric view of the present invention;

[0026] Figure 10 This is a schematic diagram of the concave-convex limiting structure of the present invention.

[0027] In the diagram: 1. Blade body; 2. Motor; 3. Lower blade root seat; 4. Upper and lower blade root seats; 5. Upper blade root seat; 6. Lower blade fixing screw; 7. Upper blade fixing screw; 8. Locking nut; 9. Housing fixing screw. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0029] Reference Figure 3-10 As shown, an overlapping unmanned aerial vehicle (UAV) propeller mechanism includes a motor 2 and at least two blade bodies 1. Each blade body 1 includes a fixed portion at its root. The mechanism is characterized in that multiple blade bodies 1 are arranged coaxially in layers, and the fixed portions at the roots of the multiple blade bodies 1 are held in a coaxial state by concave-convex limiting components. The limiting components include a lower blade root seat 3, upper and lower blade root seat fixing housings 4, and an upper blade root seat 5. In flight mode, the blade bodies 1 are automatically deployed and positioned by centrifugal force; in storage and transportation mode, they can be overlapped and folded.

[0030] It also includes: a lower blade assembly and an upper blade assembly. The lower blade assembly includes upper and lower blade root seat fixing housings 4, lower blade root seat 3 and blade body 1 stacked from top to bottom. The lower blade root seat 3 is connected to a lower blade fixing screw 6, and the lower blade fixing screw 6 passes through the lower blade root seat 3 and the blade body 1 and is fixed to the motor 2. The upper blade assembly includes a blade body 1 and an upper blade root seat 5. The root fixing part of the blade body 1 is provided with a set of upper blade fixing screws 7. The upper blade fixing screws 7 are connected to a locking nut 8, and the blade body 1 is fixed to the upper blade root seat 5 by the upper blade fixing screws 7 and the locking nut 8.

[0031] The bottom end of the upper and lower blade root seat fixing housing 4 has an annular flange 1, and the outer edge of the lower blade root seat 3 has an annular flange 2. The flange 1 of the upper and lower blade root seat fixing housing 4 is engaged with the lower flange 2 of the lower blade root seat 3. Due to the engagement between the annular protrusion at the bottom of the upper and lower blade root seat fixing housing 4 and the annular protrusion on the outer edge of the lower blade root seat 3, the upper and lower blade root seat fixing housing 4 can only rotate in the circumferential direction.

[0032] The upper and lower blade assemblies are stacked and installed. The outer edge of the upper and lower blade root seat fixing housing 4 has threaded holes for the installation of housing fixing screws 9. The housing fixing screws 9 are threaded into the upper and lower blade root seat fixing housing 4, and their ends are threaded into the upper blade root seat 5 of the upper blade assembly. At this point, the assembly of the upper and lower blades is completed. The lower blade assembly is fixed to the motor 2 and rotates with the motor 2. The upper blade assembly is connected to the lower blade assembly through the upper and lower blade root seat fixing housing 4 and can rotate relative to it in the circumferential direction.

[0033] The lower outer edge of the upper blade root seat 5 is designed with a quarter-circle arc-shaped boss, and the upper outer edge of the lower blade root seat 3 is designed with a three-quarter-circle arc-shaped groove. The upper blade root seat 5 and the lower blade root seat 3 are coupled through the arc-shaped boss and the arc-shaped groove. After the upper blade root seat 5 and the lower blade root seat 3 are connected and fitted by the upper and lower blade root seat fixing shell 4, the arc-shaped boss can rotate 180° within the arc-shaped groove, so that the upper and lower blades have two defined positions, namely the storage and transportation state position where the blades overlap and are folded (see reference). Figure 5 ) and the flight state position that is automatically deployed and limited by centrifugal force during takeoff (refer to Figure 9 ).

[0034] Furthermore, as Figure 3 and Figure 4 As shown, this structure can be extended to aircraft with three or more propeller blades.

[0035] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A vertically overlapping unmanned aerial vehicle (UAV) propeller mechanism, comprising a motor (2) and at least three blade bodies (1), each blade body (1) comprising a fixed portion at its root, characterized in that, Multiple blade bodies (1) are arranged coaxially in layers, and the fixed parts at the roots of multiple blade bodies (1) are fastened together by concave and convex limiting components to maintain a coaxial state. The limiting components include a lower blade root seat (3), a fixed housing (4) for the upper and lower blade root seats, and an upper blade root seat (5). The bottom end of the upper and lower blade root seat fixing shell (4) is constructed with an annular flange one, and the outer edge of the lower blade root seat (3) is constructed with an annular flange two, and the flange one of the upper and lower blade root seat fixing shell (4) is fastened to the lower blade root seat (3) below the flange two. The lower outer edge of the upper blade root seat (5) is designed with a quarter-circle arc-shaped boss, and the upper outer edge of the lower blade root seat (3) is a three-quarter circle arc-shaped groove. The upper blade root seat (5) and the lower blade root seat (3) are coupled through the arc-shaped boss and the arc-shaped groove. The arc-shaped boss can rotate 180° within the arc-shaped groove, giving the two adjacent blades two defined positions: the storage and transportation state where they overlap and are folded together, and the flight state where they are automatically unfolded and limited by centrifugal force during takeoff.

2. The overlapping UAV propeller mechanism according to claim 1, characterized in that, Also includes: The lower blade assembly includes an upper and lower blade root seat fixing shell (4), a lower blade root seat (3) and a blade body (1) stacked from top to bottom. The lower blade root seat (3) is connected to a lower blade fixing screw (6), and the lower blade fixing screw (6) passes through the lower blade root seat (3) and the blade body (1) and is fixed to the motor (2). The upper blade assembly includes a blade body (1) and an upper blade root seat (5). The root fixing part of the blade body (1) is provided with a set of upper blade fixing screws (7). A locking nut (8) is connected to the upper blade fixing screws (7). The blade body (1) is fixed to the upper blade root seat (5) by the upper blade fixing screws (7) and the locking nut (8).

3. The overlapping UAV propeller mechanism according to claim 2, characterized in that, The upper blade assembly and the lower blade assembly are stacked and installed. The outer edge of the upper and lower blade root seat fixing housing (4) is provided with threaded holes for the installation of the housing fixing screw (9). The housing fixing screw (9) is threaded into the upper and lower blade root seat fixing housing (4), and its end is threaded into the upper blade root seat (5) of the upper blade assembly.

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