Ornithopter combined with rotor

Abstract

This invention provides a flapping-wing aircraft combined with a rotor, relating to the field of flapping-wing aircraft technology. The invention includes a frame beam, a head, and a tail, connected by the frame beam. Two flapping-wing mechanisms are symmetrically arranged at the middle of the frame beam. A power mechanism is housed inside the frame beam. A first reinforcing plate and a second reinforcing plate are welded and fixed to the inner wall of the frame beam. The head includes a base plate, a cover plate, and two side plates. One side of each of the base plate, cover plate, and two side plates is welded and fixed to the frame beam. The two side plates are located between the cover plate and the base plate, and their surfaces are welded and fixed to the base plate and cover plate, respectively. The tail includes a horizontal tail fin and a vertical tail fin. The horizontal tail fin is welded and fixed to the side of the frame beam away from the head. This invention enables the flapping-wing aircraft to increase its payload capacity, eliminates the need for launching during takeoff, eliminates the need for a runway, and allows for fixed-point monitoring.

Description

Technical Field

[0001] This invention relates to the field of flapping-wing aircraft technology, and in particular to flapping-wing aircraft combined with rotors. Background Technology

[0002] Modern aircraft are mainly classified into fixed-wing aircraft, rotary-wing aircraft, and ornithopter aircraft based on their wings. Fixed-wing aircraft often require runways designed to suit their takeoff distance, while rotary-wing aircraft have the advantage of vertical takeoff and landing. In order to develop fixed-wing aircraft capable of vertical takeoff and landing, humans have applied the advantages of rotary-wing aircraft to fixed-wing aircraft, combining rotors and fixed wings to develop fixed-wing aircraft capable of vertical takeoff and landing.

[0003] Ornithopter is an aircraft that mimics the flight patterns of birds or insects. It is characterized by its flexibility, small size, and excellent camouflage capabilities. However, existing ornithopter has insufficient payload capacity. Summary of the Invention

[0004] The technical problem to be solved by this invention is the insufficient load-bearing capacity of flapping-wing aircraft.

[0005] The technical solution adopted by the present invention to solve its technical problem is: a flapping-wing aircraft combined with a rotor, including a frame beam, a head and a tail, wherein the head and tail are connected by the frame beam, two flapping-wing mechanisms are symmetrically arranged in the middle of the frame beam, a power mechanism is arranged inside the frame beam, and a first reinforcing plate and a second reinforcing plate are welded and fixed to the inner wall of the frame beam.

[0006] The effects achieved by the above components are as follows: the present invention can enable flapping-wing aircraft to carry a large load, take off without dropping, without a runway, and can be monitored at fixed points.

[0007] Preferably, the head includes a base plate, a cover plate, and two side plates. One side of the base plate, the cover plate, and the two side plates are welded and fixed to the frame beam. The two side plates are located between the cover plate and the base plate, and the surfaces of the two side plates are welded and fixed to the base plate and the cover plate, respectively.

[0008] The effect achieved by the above components is that the two side plates, together with the bottom plate and the cover plate, form a cone shape, which reduces wind resistance during flight and increases the flight speed of the flapping-wing aircraft.

[0009] Preferably, the tail section includes a horizontal tail fin and a vertical tail fin. The horizontal tail fin is welded and fixed to the side of the frame beam away from the head, and the vertical tail fin is welded perpendicularly to the middle position of the horizontal tail fin.

[0010] The effect achieved by the above components is that the horizontal and vertical tail fins can increase the stability of the flapping-wing aircraft.

[0011] Preferably, the flapping wing mechanism includes a servo motor, a rocker arm, a hinge, and a flapping wing plate. The servo motor is welded and fixed to the first reinforcing plate, the rocker arm is welded and fixed to the flapping wing plate, one end of the rocker arm is mounted on the output end of the servo motor, and the other end of the rocker arm is rotatably connected to the second reinforcing plate through a hinge.

[0012] The effect achieved by the above components is as follows: by controlling the flapping wing, pitch torque control is achieved. When the flapping frequency increases, the flapping wing aircraft pitches up and flies upward. When the flapping frequency decreases, the flapping wing aircraft pitches down and flies downward.

[0013] Preferably, the power mechanism includes a reinforcing rod, a dual-axis motor, and two rotors. The reinforcing rod is welded and fixed to the inner wall of the frame beam, the dual-axis motor is welded to the surface of the reinforcing rod, and the two rotors are respectively assembled at the two output ends of the dual-axis motor.

[0014] The effect achieved by the above components is that the dual-axis motor controls the rotor to rotate, thereby generating lift. When flying forward, the dual-axis motor controls the rotation of the two rotors to generate lift.

[0015] The beneficial effects of this invention are: this invention can improve the payload capacity of flapping-wing aircraft, eliminate the need for launching during takeoff, eliminate the need for a runway, and enable fixed-point monitoring. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments;

[0017] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0018] Figure 2 This is a three-dimensional structural diagram of the side plate of the present invention;

[0019] Figure 3 This is a three-dimensional structural diagram of the flapping wing plate of the present invention;

[0020] Figure 4 This is a three-dimensional structural diagram of the rotor of the present invention.

[0021] Legend: 1. Frame beam; 11. First reinforcing plate; 12. Second reinforcing plate; 2. Head; 21. Side plate; 22. Cover plate; 23. Base plate; 3. Flapping wing mechanism; 31. Servo; 32. Rocker arm; 33. Hinge; 34. Flapping wing plate; 4. Tail; 41. Horizontal tail fin; 42. Vertical tail fin; 5. Power mechanism; 51. Reinforcing rod; 52. Dual-axis motor; 53. Rotor. Detailed Implementation

[0022] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0024] Figure 1-4 The flapping-wing aircraft shown includes a frame beam 1, a head 2, and a tail 4. The head 2 and tail 4 are connected by the frame beam 1. Two flapping-wing mechanisms 3 are symmetrically arranged in the middle of the frame beam 1. A power mechanism 5 is arranged inside the frame beam 1. A first reinforcing plate 11 and a second reinforcing plate 12 are welded and fixed to the inner wall of the frame beam 1. This invention can enable the flapping-wing aircraft to carry a large load, take off without dropping, without a runway, and can be monitored at a fixed point.

[0025] Figure 2 , Figure 3 and Figure 4 The head 2 shown includes a cover plate 22, a bottom plate 23, and two side plates 21. One side of the cover plate 22, the bottom plate 23, and the two side plates 21 are welded and fixed to the frame beam 1. The two side plates 21 are located between the cover plate 23 and the bottom plate 22. The surfaces of the two side plates 21 are welded and fixed to the cover plate 22 and the bottom plate 23 respectively. The two side plates 21, together with the cover plate 22 and the bottom plate 23, form a cone shape, which reduces wind resistance during flight and increases the flight speed of the flapping-wing aircraft.

[0026] Figure 2 , Figure 3 and Figure 4 The tail section 4 shown includes a horizontal tail 41 and a vertical tail 42. The horizontal tail 41 is welded and fixed to the side of the frame beam 1 away from the head 2. The vertical tail 42 is welded perpendicularly to the middle position of the horizontal tail 41. The horizontal tail 41 and the vertical tail 42 can increase the stability of the flapping-wing aircraft.

[0027] Figure 2 , Figure 3 and Figure 4 The flapping wing mechanism 3 shown includes a servo motor 31, a rocker arm 32, a hinge 33, and a flapping wing plate 34. The servo motor 31 is welded and fixed to the first reinforcing plate 11, and the rocker arm 32 is welded and fixed to the flapping wing plate 34. One end of the rocker arm 32 is mounted on the output end of the servo motor 31, and the other end of the rocker arm 32 is rotatably connected to the second reinforcing plate 12 through the hinge 33. Pitch torque control is achieved by controlling the flapping wing plate 34. When the flapping frequency increases, the flapping wing aircraft pitches up and flies upward. When the flapping frequency decreases, the flapping wing aircraft pitches down and flies downward.

[0028] Figure 2 , Figure 3 and Figure 4 The power mechanism 5 shown includes a reinforcing rod 51, a dual-axis motor 52, and two rotors 53. The reinforcing rod 51 is welded and fixed to the inner wall of the frame beam 1. The dual-axis motor 52 is welded to the surface of the reinforcing rod 51. The two rotors 53 are respectively mounted on the two output ends of the dual-axis motor 52. The dual-axis motor 52 controls the rotors 53 to rotate to generate lift. When flying forward, the dual-axis motor 52 controls the two rotors 53 to rotate to generate lift.

[0029] Working principle: Power control: The program design enables the dual-axis motor 52 to control the rotation of the two rotors 53, while the two servo motors 31 control the movement of the two flapping wing plates 34, thereby providing lift for the aircraft;

[0030] Direction control: Two servo motors 31 control the two flapping wing panels 34 to control the direction by flapping at different frequencies;

[0031] Pitch torque control: Two servos 31 control the movement of two flapping wings 34. When the flapping frequency increases, the flapping wing aircraft pitches up and flies upward. When the flapping frequency decreases, the flapping wing aircraft pitches down and flies downward.

[0032] The program controls two servo motors 31 to make the two flapping wing plates 34 flap quickly downwards and slowly upwards. At the same time, two dual-axis motors 52 control the rotation of the two rotors 53 to generate lift. When flying forward, the dual-axis motors 52 control the rotation of the two rotors 53 to generate lift. At the same time, the flapping wing plates 34 accelerate their flapping speed under the control of the two servo motors 31. The airflow generated by the flapping wing plates 34 flapping up and down increases, and the airflow acting on the horizontal tail 41 increases. The lift of the flapping wing plates 34 increases, and the flapping wing aircraft pitches up and flies forward and upward. When turning, the flapping frequency of the two flapping wing plates 34 is different under the differential control of the two servo motors 31. The force generated by the flapping of the two flapping wing plates 34 has different components in the forward direction, generating a yaw moment and realizing the turn.

[0033] Based on the above-described preferred embodiments of the present invention, and through the foregoing description, those skilled in the art can make various changes and modifications without departing from the inventive concept. The technical scope of this invention is not limited to the contents of the specification, but must be determined according to the scope of the claims.

Claims

1. A flapping-wing aircraft combining a rotor, comprising a frame beam (1), a nose (2), and a tail (4), characterized in that: The head (2) and tail (4) are connected by a frame beam (1). Two flapping wing mechanisms (3) are symmetrically arranged in the middle of the frame beam (1). A power mechanism (5) is arranged inside the frame beam (1). A first reinforcing plate (11) and a second reinforcing plate (12) are welded and fixed to the inner wall of the frame beam (1). The head (2) includes a cover plate (22), a bottom plate (23), and two side plates (21). One side of the cover plate (22), the bottom plate (23), and the two side plates (21) are welded and fixed to the frame beam (1). The two side plates (21) are located between the bottom plate (23) and the cover plate (22). The surfaces of the two side plates (21) are welded and fixed to the cover plate (22) and the bottom plate (23), respectively. The tail section (4) includes a horizontal tail fin (41) and a vertical tail fin (42). The horizontal tail fin (41) is welded and fixed to the side of the frame beam (1) away from the head (2). The vertical tail fin (42) is welded vertically to the middle position of the horizontal tail fin (41). The flapping wing mechanism (3) includes a servo motor (31), a rocker arm (32), a hinge (33), and a flapping wing plate (34). The servo motor (31) is welded and fixed to the first reinforcing plate (11), and the rocker arm (32) is welded and fixed to the flapping wing plate (34). One end of the rocker arm (32) is mounted on the output end of the servo motor (31), and the other end of the rocker arm (32) is rotatably connected to the second reinforcing plate (12) through the hinge (33). The power mechanism (5) includes a reinforcing rod (51), a dual-axis motor (52) and two rotors (53). The reinforcing rod (51) is welded and fixed to the inner wall of the frame beam (1). The dual-axis motor (52) is welded to the surface of the reinforcing rod (51). The two rotors (53) are respectively assembled at the two output ends of the dual-axis motor (52).

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