A ducted carbon fiber blade for a vertical takeoff and landing aircraft

Abstract

This utility model discloses a ducted carbon fiber blade for vertical takeoff and landing (VTOL) aircraft, relating to the field of unmanned aerial vehicle (UAV) technology. It includes a housing, with a first bevel gear rotatably connected inside the housing. Several second bevel gears mesh with the surface of the first bevel gear via their teeth. Pulling the sliding sleeve disengages the gear plate from the inner gear ring. At this time, a compressed spring stores energy and releases its rotational freedom, driving the first and second bevel gears to rotate via a square rod. This, in turn, drives the carbon fiber fan blade to achieve angle adjustment. After adjustment, the spring resets, causing the gear plate to re-mesh with the inner gear ring, forming a mechanical self-locking mechanism to ensure the fixed angle of the carbon fiber fan blade during flight. This significantly improves the rapid adjustment capability to adapt to various complex operating conditions, solving the problem of fixed fan blades being unable to adjust aerodynamic efficiency. It provides a convenient and highly reliable fan blade adjustment solution for VTOL aircraft.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a ducted carbon fiber blade for vertical take-off and landing (VTOL) aircraft. Background Technology

[0002] The ducted carbon fiber blades of unmanned vertical takeoff and landing aircraft produce greater thrust at the same rotational speed when the blades are tilted at large angles, making them suitable for high-speed flight or heavy-load missions. However, this requires higher power, increases the motor load, and may reduce the range. At smaller tilt angles, the thrust is lower, but the rotational speed can be higher, making them suitable for high-efficiency cruise or long-endurance missions.

[0003] Currently, traditional ducted carbon fiber blades for vertical takeoff and landing aircraft use a fixed angle, which cannot be quickly and flexibly adjusted according to complex operating conditions, making it difficult to obtain the best aerodynamic performance, resulting in reduced efficiency and increased energy consumption. We provide a ducted carbon fiber blade for vertical takeoff and landing aircraft. Utility Model Content

[0004] The purpose of this invention is to provide a ducted carbon fiber blade for vertical takeoff and landing (VTOL) aircraft, in order to solve the problem mentioned in the background art that traditional ducted carbon fiber blades for VTOL aircraft use a fixed angle, which cannot be quickly and flexibly adjusted according to complex operating conditions, thus making it difficult to obtain the best aerodynamic performance, resulting in reduced efficiency and increased energy consumption.

[0005] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a ducted carbon fiber blade for a vertical take-off and landing aircraft, comprising a housing, a first bevel gear rotatably connected inside the housing, a plurality of second bevel gears meshing with the surface of the first bevel gear through teeth, a round rod fixedly connected inside the second bevel gear, a carbon fiber fan blade fixedly connected to the other end of the round rod, the housing being rotatably connected to the round rod, a square rod fixedly connected to the top of the first bevel gear, and a toothed plate slidably connected to the surface of the square rod.

[0006] Preferably, the top of the housing is provided with an internal gear ring that matches the toothed plate, and the bottom of the toothed plate engages with the internal gear ring.

[0007] Preferably, a sliding sleeve is fixedly connected to the top of the toothed plate, a spring is sleeved on the surface of the square rod, a plug is fixedly connected to the top of the square rod, and the inside of the sliding sleeve is slidably connected to the plug.

[0008] Preferably, the number of the second bevel gears is three, and a mounting sleeve is fixedly connected to the bottom of the housing.

[0009] This utility model has the following beneficial effects:

[0010] Pulling the sliding sleeve allows the toothed plate to disengage from the inner gear ring. At this time, the compressed spring stores energy and releases its rotational freedom, driving the first and second bevel gears to rotate via the square rod. This, in turn, drives the carbon fiber fan blades to achieve angle rotation adjustment. After adjustment, the spring resets, causing the toothed plate to re-engage with the inner gear ring, forming a mechanical self-locking mechanism to ensure the fixed angle of the carbon fiber fan blades during flight. This significantly improves the rapid adjustment capability to adapt to various complex operating conditions, solving the problem of fixed fan blades being unable to adjust aerodynamic efficiency. It provides a convenient and highly reliable fan blade adjustment solution for vertical take-off and landing aircraft. Attached Figure Description

[0011] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0012] Figure 2 This is an exploded view of the structure of this utility model;

[0013] Figure 3 This is a three-dimensional schematic diagram of a partial structure of this utility model.

[0014] Reference numerals: 1. Housing; 2. First bevel gear; 3. Second bevel gear; 4. Round rod; 5. Carbon fiber fan blade; 6. Square rod; 7. Gear plate; 8. Internal gear ring; 9. Spring; 10. Sliding sleeve; 11. Plug; 12. Mounting sleeve. Detailed Implementation

[0015] The present invention will be further described in detail below with reference to the accompanying drawings.

[0016] Example 1:

[0017] refer to Figure 1-3 A ducted carbon fiber blade for a vertical takeoff and landing aircraft includes a housing 1. A first bevel gear 2 is rotatably connected inside the housing 1. Several second bevel gears 3 are meshed on the surface of the first bevel gear 2 through teeth. A round rod 4 is fixedly connected inside the second bevel gears 3. A carbon fiber fan blade 5 is fixedly connected to the other end of the round rod 4. The inside of the housing 1 is rotatably connected to the round rod 4. A square rod 6 is fixedly connected to the top of the first bevel gear 2. A toothed plate 7 is slidably connected to the surface of the square rod 6.

[0018] Specifically, by pulling the sliding sleeve 10, the toothed plate 7 can be disengaged from the inner toothed ring 8. At this time, the compressed spring 9 stores energy and releases its rotational degree of freedom. Through the square rod 6, it drives the first bevel gear 2 and the second bevel gear 3 to rotate, which in turn drives the carbon fiber fan blade 5 to achieve angle rotation adjustment. After the adjustment is completed, the spring 9 resets, causing the toothed plate 7 to re-mesh with the inner toothed ring 8, forming a mechanical self-locking mechanism to ensure the angle of the carbon fiber fan blade 5 is fixed in flight. This significantly improves the rapid adjustment capability to adapt to various complex working conditions, solves the problem of fixed fan blades being unable to adjust aerodynamic efficiency, and provides a convenient and highly reliable fan blade adjustment solution for vertical take-off and landing aircraft.

[0019] refer to Figure 2 The top of the housing 1 is provided with an internal gear ring 8 that is adapted to the toothed plate 7. The bottom of the toothed plate 7 meshes with the internal gear ring 8. By providing the internal gear ring 8, the toothed plate 7 can be easily fixed.

[0020] refer to Figure 2 A sliding sleeve 10 is fixedly connected to the top of the toothed plate 7, a spring 9 is sleeved on the surface of the square rod 6, and a plug 11 is fixedly connected to the top of the square rod 6. The inside of the sliding sleeve 10 is slidably connected to the plug 11. By setting the spring 9, the toothed plate 7 can be easily reset and fixed. By setting the plug 11, one end of the spring 9 can be effectively limited.

[0021] refer to Figure 1 and Figure 3 There are three second bevel gears 3. The bottom of the housing 1 is fixedly connected with a mounting sleeve 12. By setting the mounting sleeve 12, it is easy to fix and connect it to the motor output end.

[0022] Brief description of the usage process: The user can pull the sliding sleeve 10 to cause the toothed plate 7 to disengage from the inner toothed ring 8. At the same time, the toothed plate 7 slides on the surface of the square rod 6, compressing the spring 9. Then, rotating the toothed plate 7 causes the square rod 6 to rotate, which in turn causes the first bevel gear 2 to rotate. Then, the first bevel gear 2 causes the second bevel gear 3 to rotate, which in turn causes the carbon fiber fan blade 5 to rotate and be adjusted via the round rod 4. Then, the sliding sleeve 10 is released, allowing the spring 9 to reset the toothed plate 7 and re-engage it inside the inner toothed ring 8, thus facilitating the rotation adjustment of the carbon fiber fan blade 5.

[0023] This specific embodiment is merely an explanation of the present utility model and is not intended to limit the present utility model. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of the claims of the present utility model, they are protected by patent law.

Claims

1. A ducted carbon fiber blade for a vertical takeoff and landing aircraft, comprising a shell (1), characterized in that: The housing (1) is rotatably connected to a first bevel gear (2), and the surface of the first bevel gear (2) is meshed with several second bevel gears (3) by teeth. The second bevel gear (3) is fixedly connected to a round rod (4), and the other end of the round rod (4) is fixedly connected to a carbon fiber fan blade (5). The housing (1) is rotatably connected to the round rod (4), and the top of the first bevel gear (2) is fixedly connected to a square rod (6). The surface of the square rod (6) is slidably connected to a toothed plate (7).

2. The ducted carbon fiber blade for a vertical takeoff and landing aircraft according to claim 1, characterized in that: The top of the housing (1) is provided with an internal gear ring (8) that is adapted to the toothed plate (7), and the bottom of the toothed plate (7) meshes with the internal gear ring (8).

3. A ducted carbon fiber blade for a vertical takeoff and landing aircraft according to claim 2, characterized in that: The top of the toothed plate (7) is fixedly connected to a sliding sleeve (10), the surface of the square rod (6) is fitted with a spring (9), the top of the square rod (6) is fixedly connected to a plug (11), and the inside of the sliding sleeve (10) is slidably connected to the plug (11).

4. A ducted carbon fiber blade for a vertical takeoff and landing aircraft according to claim 1, characterized in that: The number of the second bevel gears (3) is three, and the bottom of the housing (1) is fixedly connected with a mounting sleeve (12).

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