一种方向合成型飞行器
By replacing the traditional swashplate system with the action cylinder and disc structure of the directional synthesis aircraft, and combining it with a hollow shaft motor and bearing wheel, the complexity and high cost of the traditional helicopter swashplate system are solved, achieving low-cost, high-precision all-around control.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- 董伟国
- Filing Date
- 2025-04-09
- Publication Date
- 2026-07-17
AI Technical Summary
The swashplate systems of traditional helicopters and coaxial twin-rotor helicopters are complex, have many parts, are difficult to manufacture, and are costly. Furthermore, the servos are prone to wear, which leads to a decrease in control accuracy and makes maintenance difficult.
The aircraft adopts a directional synthesis type aircraft, using a simple action tube and disc structure to replace the complex swashplate, combined with a hollow shaft motor and conventional bearing wheel, simplifying the servo structure, and achieving directional control through electromagnetic drive, reducing the number of ball joint components.
It reduces manufacturing and maintenance costs, improves the control precision and sensitivity of the aircraft, and enables all-around tilt control, making it suitable for different types of UAVs.
Smart Images
Figure CN224511495U_ABST
Abstract
Claims
1. A directionally synthesized aircraft comprising a fuselage mechanism, a lift mechanism provided on the fuselage mechanism, and a direction control mechanism for controlling the flight direction of the aircraft, characterized in that: The lifting mechanism includes a hub (1), blades (2) mounted on the hub (1), and a power device that drives the blades (2) and the hub (1) to rotate synchronously. The direction control mechanism includes a control rod (3) for adjusting the blade angle of the blade (2), a reset mechanism for pushing the control rod (3) to reset, a disk (4) for pushing the control rod (3) to move, and a drive mechanism for driving the disk (4) to move. One end of the control rod (3) is connected to the blade (2), and the other end of the control rod (3) is in contact with the disk (4). The drive mechanism includes an action cylinder (5) that drives the disc (4) to tilt and a support rod (14) that serves as a support point for the rotation of the disc (4).
2. A directionally composite flying vehicle according to claim 1, characterized in that: Both the lift mechanism and the directional control mechanism are provided in twos. One lift mechanism and one directional control mechanism constitute a set of directional linkage mechanisms. Two sets of directional linkage mechanisms are provided on the fuselage mechanism. The directional control mechanism in each set of directional linkage mechanisms controls the corresponding lift mechanism. The two sets of directional linkage mechanisms constitute the all-round control mechanism of the aircraft. The action cylinder (5) and the support rod (14) are both provided on the fuselage mechanism.
3. A directionally composite flying machine according to claim 2, wherein: The upper and lower parts of the fuselage mechanism are symmetrically arranged with two disks (4). The two inclined action cylinders (5) of the drive disk (4) located on the upper part of the fuselage mechanism are arranged in a cross shape with the two inclined action cylinders (5) of the drive disk (4) located on the lower part of the fuselage mechanism. Each disk (4) is movably connected to two support rods (14). The two action cylinders (5) acting on the same disk (4) are arranged in a cross shape with the two support rods (14).
4. A directionally composite flying machine according to claim 3, wherein: Two support ears (40) are provided on the disc (4). One end of the two support rods (14) is movably connected to the support ears (40), and the other end is connected to the body mechanism.
5. A directionally synthesized flying vehicle according to claim 1, wherein: The actuating cylinder (5) includes a cylinder wall (50), a support spring (51) disposed inside the cylinder wall (50), a magnetic rod (52) for adjusting the angle of the disk (4), and an electromagnetic coil (53) for causing the magnetic rod (52) to move; the magnetic rod (52) is inserted into the cylinder wall (50), the support spring (51) is disposed at the bottom of the magnetic rod (52), and the electromagnetic coil (53) is embedded in the cylinder wall (50).
6. A directionally composite flying vehicle as claimed in claim 5, characterized in that: The magnetic rod (52) is provided with a hemispherical cap (15) for pushing the disk (4), and the hemispherical cap (15) is in contact with the disk surface of the disk (4).
7. A directionally synthesized flying vehicle as claimed in claim 5, characterized in that: The support rod (14) is an actuating cylinder (5), and the magnetic rod (52) inside the actuating cylinder (5) which serves as the support rod (14) is provided with a perforated cap (9) that is movably connected to the disc (4).
8. A directionally syndetic aircraft as in claim 1, wherein: The power unit is a hollow shaft motor (6). The reset mechanism includes a connecting plate (7) and a reset spring (8). A limiting hole is provided on the control rod (3). One end of the connecting plate (7) is fixedly connected to the lifting mechanism. The other end of the connecting plate (7) passes through the limiting hole of the reset spring (8) and the control rod (3) in sequence. One end of the control rod (3) is connected to the blade (2). The other end of the control rod (3) is provided with a bearing wheel (10). The bearing wheel (10) is in contact with the disc (4).
9. A directionally composite flying machine according to claim 2, wherein: The fuselage mechanism includes a central rod (11), an equipment box (12) and a landing gear (13). The central rod (11) is arranged through the central axis of the equipment box (12). The landing gear (13) is fixed at the lower end of the central rod (11). The equipment box (12) is provided with a groove for installing the action cylinder (5) or the support rod (14).