Aircraft paddle

Abstract

The utility model relates to the technical field of aircrafts, in particular to an aircraft paddle which comprises a paddle seat, a paddle hub and a plurality of blades. The plurality of blades are arranged along the periphery of the propeller hub; the propeller hub and the plurality of blades are integrally formed; and the propeller hub is connected with the propeller seat. The propeller hub and the blades are integrally formed, so that the sealing performance between the propeller hub and the blades can be guaranteed, gaps between the propeller hub and the blades can be completely eliminated, the connection stability between the propeller hub and the blades can also be guaranteed, and the stability and the safety of an aircraft in the flying process can be improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft, specifically relates to an aircraft paddle. BACKGROUND

[0002] In modern drone design, in order to improve efficiency, reduce noise and enhance safety, a ducted fan is usually used as a propulsion device. The ducted fan is composed of a closed annular shell (i.e. duct) and rotating paddles inside it, which include a central hub and multiple blades connected to the outer periphery of the hub, which work together to generate thrust or lift.

[0003] Due to the high cost of paddles, the current market unmanned aerial vehicle paddles adopt a detachable connection between the hub and the blade. This design allows individual replacement of damaged blades, thereby reducing maintenance costs and improving resource utilization.

[0004] However, the detachable structure may cause small gaps or looseness between the hub and the blade, which may affect the aerodynamic characteristics and lead to efficiency decline. More seriously, in the case of high-speed rotation, any loose connection may cause mechanical failure, thereby threatening the safety and reliability of the unmanned aerial vehicle. SUMMARY

[0005] The utility model aims at the above-mentioned insufficient in prior art, provides a kind of aircraft paddle.

[0006] The utility model discloses the purpose is realized by the following technical scheme: a kind of aircraft paddle, including paddle seat, hub and multiple blades;Multiple blades are arranged along the outer periphery of hub;The hub is integrally formed with multiple blades;The hub is connected with paddle seat.

[0007] The utility model further is provided, the hub is equipped with containing cavity;The paddle seat is sleeved in containing cavity.

[0008] The utility model further is provided, the shape of hub is circular truncated cone;The shape of containing cavity is circular truncated cone;The diameter of hub top is less than the diameter of hub bottom;The diameter of containing cavity top is less than the diameter of containing cavity bottom.

[0009] The utility model further is provided, the paddle seat includes connecting column, the upper connecting ring of being equipped in the top of connecting column and the lower connecting ring of being equipped in the bottom of connecting column;The outer periphery of upper connecting ring is sealedly connected with the top of containing cavity;The outer periphery of lower connecting ring is sealedly connected with the bottom of containing cavity.

[0010] The utility model further sets up, the upper connecting ring is equipped with a plurality of upper vent holes along the circumferential direction, the lower connecting ring is equipped with a plurality of lower vent holes along the circumferential direction, and the connecting column is equipped with a shaft hole along the length direction.

[0011] The utility model further sets up, a plurality of upper vent holes are distributed along the central angle of the upper connecting ring, and a plurality of lower vent holes are distributed along the central angle of the lower connecting ring.

[0012] The utility model further sets up, the outer wall of connecting column is equipped with the flow guide inclined plane.

[0013] The utility model further sets up, the outer periphery of upper connecting ring and the inner wall between the top of accommodating cavity are sealed by adhesive bonding, and the outer periphery of lower connecting ring and the inner wall between the bottom of accommodating cavity are sealed by adhesive bonding.

[0014] The utility model further sets up, the inner wall of accommodating cavity is equipped with a plurality of limiting grooves, and the outer wall of lower connecting ring is equipped with a plurality of limiting blocks matched with the limiting grooves.

[0015] The utility model further sets up, a plurality of blades are arranged at the outer periphery of the hub at equal angles.

[0016] The utility model has the advantages that the hub and the plurality of blades are integrally formed, which can ensure the sealing between the hub and the blades, completely eliminate the gap between the hub and the blades, and ensure the stability of the connection between the hub and the blades, thereby improving the stability and safety of the aircraft during flight. BRIEF DESCRIPTION OF DRAWINGS

[0017] The embodiments in the drawings do not constitute any limitation on the utility model, and other drawings can be obtained by the ordinary skilled in the art without creative labor on the premise of not paying the creative labor.

[0018] Figure 1 It is the structure schematic diagram of the utility model;

[0019] Figure 2 It is the structure schematic diagram of another view of the utility model;

[0020] Figure 3 It is the sectional view of the utility model;

[0021] Figure 4 It is the structure schematic diagram of the utility model hidden behind the paddle seat;

[0022] Figure 5 It is the structure schematic diagram of the paddle seat of the utility model;

[0023] Wherein: 1, the paddle seat; 11, connecting column;12, upper connecting ring;13, lower connecting ring;2, the hub;21, the accommodation cavity;3, the blade;41, the upper vent;42, the lower vent;43, the shaft hole;5, the guide slope;61, the limit slot;62, the limit block. DETAILED DESCRIPTION

[0024] The utility model is further described in combination with the following examples.

[0025] By Figures 1 to 5 It can be known that the aircraft paddle blade comprises a paddle seat 1, a hub 2 and a plurality of blades 3;The plurality of blades 3 are arranged along the outer periphery of the hub 2;The hub 2 and the plurality of blades 3 are integrally formed;The hub 2 is connected with the paddle seat 1.

[0026] Specifically, in the production process of the aircraft paddle blade, the hub 2 and the plurality of blades 3 are integrally formed first to ensure the sealing and connection stability between the hub 2 and the blades 3, and then the hub 2 and the paddle seat 1 are fixedly connected together, the top of the paddle seat 1 can be installed with a fairing, and the bottom of the paddle seat 1 can be installed with a motor, so that the aircraft has a flight function.

[0027] In the embodiment, the hub 2 and the plurality of blades 3 are integrally formed, which can ensure the sealing between the hub 2 and the blades 3, completely eliminate the gap between the hub 2 and the blades 3, and ensure the connection stability between the hub 2 and the blades 3, thereby improving the stability and safety of the aircraft in flight.

[0028] The aircraft paddle blade comprises a hub 2, and the hub 2 is provided with an accommodation cavity 21;The paddle seat 1 is sleeved in the accommodation cavity 21 in the hub 2. Specifically, by sleeving the paddle seat 1 in the accommodation cavity 21 in the hub 2, the stability of the connection between the paddle seat 1 and the hub 2 can be enhanced.

[0029] The aircraft paddle blade comprises a hub 2, and the hub 2 is provided with an accommodation cavity 21;The paddle seat 1 is sleeved in the accommodation cavity 21 in the hub 2. Specifically, by sleeving the paddle seat 1 in the accommodation cavity 21 in the hub 2, the stability of the connection between the paddle seat 1 and the hub 2 can be enhanced.

[0030] The aircraft blade provided by the embodiment comprises a connecting column 11, an upper connecting ring 12 arranged on the top of the connecting column 11, and a lower connecting ring 13 arranged on the bottom of the connecting column 11. The outer periphery of the upper connecting ring 12 is in sealing connection with the top of the accommodating cavity 21, and the outer periphery of the lower connecting ring 13 is in sealing connection with the bottom of the accommodating cavity 21. Specifically, in the production process, the hub 2 and the plurality of blades 3 are integrally formed first, so as to ensure the sealing property and the connection stability between the hub 2 and the blades 3, then the connecting column 11 is sleeved into the accommodating cavity 21 in the hub 2, and the outer periphery of the upper connecting ring 12 is in sealing connection with the top of the accommodating cavity 21, and the outer periphery of the lower connecting ring 13 is in sealing connection with the bottom of the accommodating cavity 21, so that the connecting column 11 and the hub 2 are connected stably and reliably. The upper connecting ring 12 can be provided with a flow guide cover, and the lower connecting ring 13 can be provided with a motor, so that the aircraft has a flight function.

[0031] The aircraft blade provided by the embodiment comprises a plurality of upper air holes 41 arranged along the circumference of the upper connecting ring 12, a plurality of lower air holes 42 arranged along the circumference of the lower connecting ring 13, and a shaft hole 43 arranged along the length direction of the connecting column 11. Specifically, the wind flow can enter the accommodating cavity 21 through the upper air holes 41, and then the motor can be cooled through the lower air holes 42. Meanwhile, the wind flow can cool the motor through the shaft hole 43.

[0032] The aircraft blade provided by the embodiment comprises a plurality of upper air holes 41 arranged along the circumference of the upper connecting ring 12, a plurality of lower air holes 42 arranged along the circumference of the lower connecting ring 13, and a shaft hole 43 arranged along the length direction of the connecting column 11. Specifically, the wind flow can enter the accommodating cavity 21 through the upper air holes 41, and then the motor can be cooled through the lower air holes 42. Meanwhile, the wind flow can cool the motor through the shaft hole 43.

[0033] The aircraft blade provided by the embodiment comprises a plurality of upper air holes 41 arranged along the circumference of the upper connecting ring 12, a plurality of lower air holes 42 arranged along the circumference of the lower connecting ring 13, and a shaft hole 43 arranged along the length direction of the connecting column 11. Specifically, the wind flow can enter the accommodating cavity 21 through the upper air holes 41, and then the motor can be cooled through the lower air holes 42. Meanwhile, the wind flow can cool the motor through the shaft hole 43.

[0034] The aircraft blade provided by the embodiment comprises a plurality of upper air holes 41 arranged along the circumference of the upper connecting ring 12, a plurality of lower air holes 42 arranged along the circumference of the lower connecting ring 13, and a shaft hole 43 arranged along the length direction of the connecting column 11. Specifically, the wind flow can enter the accommodating cavity 21 through the upper air holes 41, and then the motor can be cooled through the lower air holes 42. Meanwhile, the wind flow can cool the motor through the shaft hole 43.

[0035] The inner wall of the accommodating cavity 21 is provided with a plurality of limiting grooves 61, and the outer wall of the lower connecting ring 13 is provided with a plurality of limiting blocks 62 matched with the limiting grooves 61. Specifically, through the above setting, after the upper connecting ring 12 and the lower connecting ring 13 are respectively installed with the inner wall of the accommodating cavity 21, the relative rotation between the paddle base 1 and the hub 2 can be prevented.

[0036] The plurality of blades 3 are arranged at equal angles on the outer periphery of the hub 2. Through the above setting, the stability and efficiency during the flight of the aircraft can be ensured.

[0037] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not intended to limit the scope of protection of the present application. Although the present application has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solutions of the present application can be modified or replaced equivalently without departing from the essence and scope of the technical solutions of the present application.

Claims

1. An aircraft propeller blade, characterized in that: It includes a propeller base (1), a propeller hub (2) and multiple blades (3); the multiple blades (3) are arranged along the outer periphery of the propeller hub (2); the propeller hub (2) and the multiple blades (3) are integrally formed; the propeller hub (2) is connected to the propeller base (1).

2. The aircraft propeller blade according to claim 1, characterized in that: The propeller hub (2) is provided with a receiving cavity (21); the propeller seat (1) is sleeved in the receiving cavity (21).

3. The aircraft propeller blade according to claim 2, characterized in that: The shape of the propeller hub (2) is frustum-shaped; the shape of the accommodating cavity (21) is frustum-shaped; the diameter of the top of the propeller hub (2) is smaller than the diameter of the bottom of the propeller hub (2); the diameter of the top of the accommodating cavity (21) is smaller than the diameter of the bottom of the accommodating cavity (21).

4. The aircraft propeller blade according to claim 3, characterized in that: The propeller base (1) includes a connecting column (11), an upper connecting ring (12) disposed at the top of the connecting column (11), and a lower connecting ring (13) disposed at the bottom of the connecting column (11); the outer periphery of the upper connecting ring (12) is sealed to the top of the accommodating cavity (21); the outer periphery of the lower connecting ring (13) is sealed to the bottom of the accommodating cavity (21).

5. The aircraft propeller blade according to claim 4, characterized in that: The upper connecting ring (12) is provided with a plurality of upper vent holes (41) in the circumferential direction; the lower connecting ring (13) is provided with a plurality of lower vent holes (42) in the circumferential direction; the connecting post (11) is provided with a shaft hole (43) in the length direction.

6. The aircraft propeller blade according to claim 5, characterized in that: Multiple upper vents (41) are distributed at equal angles along the center of the upper connecting ring (12); multiple lower vents (42) are distributed at equal angles along the center of the lower connecting ring (13).

7. The aircraft propeller blade according to claim 4, characterized in that: The outer wall of the connecting column (11) is provided with a flow guiding slope (5).

8. The aircraft propeller blade according to claim 4, characterized in that: The outer periphery of the upper connecting ring (12) is bonded and sealed to the inner wall of the top of the accommodating cavity (21) by adhesive; the outer periphery of the lower connecting ring (13) is bonded and sealed to the inner wall of the bottom of the accommodating cavity (21) by adhesive.

9. A propeller blade for an aircraft according to claim 4, characterized in that: The inner wall of the accommodating cavity (21) is provided with a plurality of limiting grooves (61); the outer wall of the lower connecting ring (13) is provided with a plurality of limiting blocks (62) that cooperate with the limiting grooves (61).

10. The aircraft propeller blade according to claim 1, characterized in that: Multiple blades (3) are set at equal angles on the outer periphery of the hub (2).

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