Coaxial dual-rotor unmanned aerial vehicle
By adopting a coaxial twin-rotor main rotor and multiple auxiliary rotors design on the UAV, the problems of low safety and propulsion efficiency in the existing technology are solved, and efficient and reliable flight control and automatic driving capabilities are achieved.
Patent Information
- Application Number
- CN202510985194.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-10
- Publication Date
- 2025-09-16
AI Technical Summary
The existing multi-rotor structure of vertical take-off and landing UAVs is prone to accidents when one rotor fails, has low safety and reliability, and low propulsion efficiency. The mechanical complexity and flight control problems of the traditional coaxial twin-rotor structure make it difficult to achieve autonomous driving.
It adopts a coaxial twin rotor as the main rotor and is equipped with no less than three auxiliary rotors for center of gravity balance and flight status control. The rotor pitch change mechanism is eliminated, which reduces costs and improves reliability.
It achieves efficient propulsion and safe and reliable flight control, simplifies the mechanical structure, is suitable for automatic driving, and improves the safety and efficiency of drones.
Smart Images
Figure CN120646271A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of vertical take-off and landing UAVs, and in particular relates to the technology of vertical take-off and landing UAVs driven by motors. Technical Background
[0002] Current vertical take-off and landing electric drones typically use at least four rotors. A single rotor failure can result in a crash, leading to low safety and reliability. Multi-rotor structures also have low propulsion efficiency (i.e., high power consumption). While coaxial twin-rotor structures offer high propulsion efficiency, conventional helicopters utilize variable-pitch rotor mechanisms for center-of-gravity balance and flight control. These complex mechanical structures pose reliability issues and numerous challenges in flight control, making them unsuitable for autonomous driving. Summary of the Invention
[0003] Based on the above problems, the present invention proposes an electric UAV that uses a coaxial dual rotor as the main rotor, and uses no less than three auxiliary rotors to undertake center of gravity balance regulation and flight state control. It has no rotor pitch change mechanism, low cost and high reliability.
[0004] The technical solution of the present invention is as follows: A UAV comprises: a main engine and an auxiliary rotor. The main engine adopts a coaxial dual-rotor structure, comprising: a main rotor consisting of upper and lower main wing blades, and upper and lower wing motors; the auxiliary rotor comprises auxiliary wing blades, an auxiliary motor, and an auxiliary wing rod, and is characterized in that: the upper and lower wing motors and the auxiliary rotor are located between the upper and lower main wing blades; the auxiliary rotor is directly or indirectly connected to the motor base of the upper or lower wing motor via the auxiliary wing rod. BRIEF DESCRIPTION OF THE DRAWINGS
[0005] The following will clearly and completely describe the implementation of the present invention in conjunction with the drawings in the embodiments of the present invention. The described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.
[0006] Figure 1 This is a characteristic schematic diagram of the present invention.
[0007] Figure 2 yes Figure 1 A characteristic schematic top view of .
[0008] Figure 3 This is a characteristic schematic diagram of the present invention.
[0009] Figure 4 yes Figure 3 A characteristic schematic top view of .
[0010] Figures 5-7 The three are characteristic schematic diagrams of the present invention.
[0011] In the figure: 1. Main engine, 11. Upper main wing, 111. Upper wing motor, 12. Lower main wing, 121. Lower wing motor, 13. Main axis, 2. Auxiliary rotor, 21. Auxiliary wing, 22. Auxiliary motor, 23. Auxiliary wing rod, 3. Body, 4. Fence, 41. Lower side guardrail, 5. Handle, 6. Support, 7 Pendant, 71. Connector. DETAILED DESCRIPTION
[0012] Figure 1 and Figure 2 The present invention, as shown, employs a coaxial twin-rotor structure. The main rotor is comprised of an upper main wing 11 and a lower main wing 12 of the main engine 1. The upper main wing 11 is driven by an upper wing motor 111, mounted directly on the upward-facing power shaft of the upper wing motor 111. The lower main wing 12 is driven by a lower wing motor 121, mounted directly on the downward-facing power shaft of the lower wing motor 121. The fuselage 3 is positioned between the upper and lower wing motors 111, 121, and a battery should be located within the fuselage 3. The upper and lower main wing 11 and 12 are each comprised of two blades, though more blades are possible, rotating in opposite directions. The upper and lower wing motors 111 and 121 are coaxial (as indicated by the main axis 13). The flight control circuitry should be directly or indirectly fixedly connected to the motor mounts of the main rotor (the upper and lower wing motors 111, 121), and the flight control circuitry may also be located within the fuselage 3.
[0013] The three auxiliary rotors 2 facing the same direction as the main rotor (vertical) are located between the upper main wing 11 and the lower main wing 12, and should be symmetrically and evenly distributed around the main axis 13. The auxiliary wing rod 23 should be directly or indirectly fixed to the motor seat of the main rotor, and the connection is through the fuselage 3 in the figure; the auxiliary wing piece 21 of the auxiliary rotor 2 is directly installed on the power shaft of the auxiliary motor 22, and the auxiliary wing rod 23 should adopt a hollow tube structure, and the cable driving the auxiliary motor 22 is set in the tube.
[0014] Most of the required lift (even 100%) is borne by the main rotor, at least 60% of the lift is borne by the main rotor, it is reasonable that more than 80% of the lift is borne by the main rotor, and it is best that more than 90% of the lift is borne by the main rotor. The three auxiliary rotors 2 are mainly responsible for flight attitude control, and control the level flight speed and direction by adjusting the inclination angle of the main axis 13 of the main rotor. If necessary, they are also responsible for center of gravity balance adjustment.
[0015] During design, the maximum distance B between the tip of the auxiliary wing 21 and the main axis 13 should not be greater than the radius A of the main rotor, so that the maximum main rotor radius can be obtained, which is conducive to improving propulsion efficiency.
[0016] Figure 3 and Figure 4The present invention shown is equipped with four auxiliary rotors 2, which are symmetrically and evenly distributed around the main axis 13. The upper main blades 11 are directly mounted on the rotor disk of the upper wing motor 111, which faces upward. The lower main blades 12 are directly mounted on the rotor disk of the lower wing motor 121, which faces downward. The auxiliary blades 21 are directly mounted on the rotor disk of the auxiliary motor 22. As shown in the figure, a fence 4 surrounds the upper main blades 11 and lower main blades 12. The fence 4 is fixedly connected to the aircraft (the fuselage 3 in the figure) via the extended auxiliary rotor 2 aileron rod 23, protecting the main and auxiliary rotors 2 from collision.
[0017] Figure 5 In the illustrated embodiment, the upper wing motor 111 and the lower wing motor 121 are fixedly connected back-to-back (the motor bases of the two motors), with two fuselages 3 positioned on either side. They are symmetrically distributed about the main axis 13, so that the center of gravity of the entire aircraft lies on the main axis 13. The figure shows a handle 5 connected to the lower wing motor 121. The aircraft operator can grasp the handle 5 to launch or receive the aircraft. The handle 5 does not rotate with the rotor disk of the lower wing motor 121. The handle 5 can be fixedly connected to the stator or motor base of the lower wing motor 121 via a connector. The handle 5 can also be connected to the rotor disk (or rotating shaft) of the lower wing motor 121 via a bearing (or a sliding sleeve structure similar to a bearing).
[0018] Figure 6 The present invention shown in the figure is equipped with a support member 6 connected to the lower wing motor 121. The support member 6 has no fewer than three legs. The figure shows a lower guardrail 41 connected to the fence 4, located on the underside of the lower main wing 12 and also connected to the support member 6. The support member 6 can be fixedly connected to the stator or motor base of the lower wing motor 121 via a connector. The support member 6 can also be connected to the rotor disk (or rotating shaft) of the lower wing motor 121 via a bearing (or a sliding sleeve structure similar to a bearing).
[0019] Figure 7 The present invention shown is provided with a hanger 7 connected to the lower wing motor 121, located at the lower end. The hanger 7 can be a camera, or a sensor such as a radar probe, or a mechanical actuator (such as a hook mechanism, a launching mechanism). The hanger 7 can also be set at the upper end of the upper wing motor (111). The lower wing motor 121 or the upper wing motor 111 should adopt a central through-hole structure, with a wire passing through the central through-hole to form an electrical connection between the hanger 7 and the body 3 (for example, with the flight control device). The hanger 7 cannot rotate with the rotor of the lower wing motor 121. The hanger 7 can be fixedly connected to the stator or motor seat of the lower wing motor 121 through the connecting member 71 (central through-hole structure). The connecting member 71 can also be connected to the rotor disk (or rotating shaft) of the lower wing motor 121 through a bearing (or a sliding sleeve structure similar to a bearing).
[0020] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.
Claims
1. A coaxial twin-rotor drone, comprising: a main engine (1), an auxiliary rotor (2), wherein the main engine (1) adopts a coaxial twin-rotor structure, comprising: a main rotor consisting of an upper main wing (11) and a lower main wing (12), an upper wing motor (111) and a lower wing motor (121), and the auxiliary rotor (2) comprises an auxiliary wing (21), an auxiliary motor (22) and an auxiliary wing rod (23), and is characterized in that: The upper wing motor (111), the lower wing motor (121) and the auxiliary rotor (2) are located between the upper main wing (11) and the lower main wing (12).
2. The drone according to claim 1, characterized in that: The upper wing motor (111) and the lower wing motor (121) are connected back to back.
3. The drone according to claim 1, wherein: The upper main wing (11) is mounted on the rotor disk with the upper wing motor (111) facing upward, and the lower main wing (12) is mounted on the rotor disk with the lower wing motor (121) facing downward.
4. The UAV according to claim 1, 2 or 3, characterized in that: The maximum distance B between the tip of the auxiliary wing (21) and the main axis (13) is not greater than the radius A of the main rotor.
5. The UAV according to claim 1, 2 or 3, characterized in that: A handle (5) or a support member (6) connected to the lower wing motor (121) is provided.
6. The drone according to claim 5, characterized in that: The handle (5) or the support member (6) is fixedly connected to the stator or motor seat of the lower wing motor (121) through a connecting member, or is connected to the rotor disk or rotating shaft of the lower wing motor (121) through a bearing or a sliding sleeve structure similar to a bearing.
7. The UAV according to claim 1, 2 or 3, characterized in that: A hanging piece (7) connected to the lower wing motor (121) or the upper wing motor (111) is provided. The lower wing motor (121) or the upper wing motor (111) adopts a central through-hole structure, and a wire passes through the central through-hole.
8. The UAV according to claim 1, 2 or 3, characterized in that: A surrounding fence (4) is provided.
9. The drone according to claim 8, characterized in that: The fence (4) is fixed by the auxiliary wing rod (23) of the auxiliary rotor (2).
10. The drone according to claim 8, characterized in that: A lower guardrail (41) connected to the fence (4) is provided and located on the lower side of the lower main wing (12).