Rotor-combined ornithopter

Abstract

The invention provides an ornithopter combined with rotor wings, and relates to the technical field of ornithopters, the ornithopter comprises a frame beam, a head part and a tail part, the head part and the tail part are connected through the frame beam, two flapping wing mechanisms are symmetrically arranged in the middle of the frame beam, a power mechanism is arranged in the frame beam, and the power mechanism is connected with the tail part. A first reinforcing plate and a second reinforcing plate are fixedly welded to the inner wall of the frame beam, the head comprises a bottom plate, a cover plate and two side plates, one side of the bottom plate, one side of the cover plate and one side of each side plate are fixedly welded to the frame beam, the two side plates are located between the cover plate and the bottom plate, and the surfaces of the two side plates are fixedly welded to the bottom plate and the cover plate respectively. The tail comprises a horizontal empennage and a vertical empennage, the horizontal empennage is welded and fixed to the side, away from the head, of the frame beam, the loading capacity of the ornithopter can be improved, throwing and runways are not needed when the ornithopter takes off, and fixed-point monitoring can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of flapping-wing aircraft, in particular to a flapping-wing aircraft combined with a rotor. Background Art

[0002] Modern aircraft are mainly classified into fixed-wing aircraft, rotorcraft, and flapping-wing aircraft based on their wings. Fixed-wing aircraft often need to design a runway that meets their take-off distance for take-off, while rotorcraft have the advantage of vertical take-off and landing. In order to develop fixed-wing aircraft with vertical take-off and landing, humans applied the advantages of rotorcraft to fixed-wing aircraft, combined rotors with fixed wings, and developed fixed-wing aircraft that can take off and land vertically.

[0003] A flapping-wing aircraft is an aircraft that imitates the flight style of birds or insects. It is flexible, small in size, and has excellent camouflage capabilities. However, existing flapping-wing aircraft have insufficient load-bearing capacity. Summary of the invention

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

[0005] The technical solution adopted by the present invention to solve its technical problems is: a flapping-wing aircraft combined with a rotor, including a frame beam, a head and a tail, the head and the tail are connected by the frame beam, two flapping-wing mechanisms are symmetrically arranged in the middle position of the frame beam, a power mechanism is arranged inside the frame beam, and a first reinforcement plate and a second reinforcement 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 realize the flapping-wing aircraft to suspend a large load, does not need to be thrown during take-off, does not need a runway, and can be monitored at a fixed point.

[0007] Preferably, the head includes a bottom plate, a cover plate and two side plates, one side of the bottom 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 bottom plate, and the surfaces of the two side plates are respectively welded and fixed to the bottom plate and the cover plate.

[0008] The effects achieved by the above components are: the two side panels cooperate with the bottom panel and the cover panel to form a cone, thereby reducing the wind resistance during flight and increasing the flight speed of the flapping-wing aircraft.

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

[0010] The effects achieved by the above components are: the horizontal tail and the vertical tail can increase the stability of the flapping-wing aircraft.

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

[0012] The effect achieved by the above components is: pitch moment control is achieved by controlling the flapping wing plate. When the flapping frequency increases, the flapping-wing aircraft raises its head and flies upward. When the flapping frequency decreases, the flapping-wing aircraft lowers its head 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 on the two output ends of the dual-axis motor.

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

[0015] The beneficial effects of the present invention are as follows: the present invention can improve the load-bearing capacity of a flapping-wing aircraft, does not require throwing during take-off, does not require a runway, and can be monitored at a fixed point. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention is further described below in conjunction with the accompanying drawings and embodiments; Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention; Figure 2 It is a schematic diagram of the three-dimensional structure of the side panel of the present invention; Figure 3 It is a schematic diagram of the three-dimensional structure of the flapping wing plate of the present invention; Figure 4 It is a schematic diagram of the three-dimensional structure of the rotor of the present invention.

[0017] Legend: 1. Frame beam; 11. First reinforcement plate; 12. Second reinforcement plate; 2. Head; 21. Side plate; 22. Cover plate; 23. Bottom plate; 3. Flapping-wing mechanism; 31. Servo; 32. Rocker arm; 33. Hinge; 34. Flapping-wing plate; 4. Tail; 41. Horizontal tail; 42. Vertical tail; 5. Power mechanism; 51. Reinforcement rod; 52. Dual-axis motor; 53. Rotor. DETAILED DESCRIPTION

[0018] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, which only illustrate the basic structure of the present invention in a schematic manner, and therefore only show the components related to the present invention.

[0019] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0020] Figure 1-4 The flapping-wing aircraft combined with a rotor shown includes a frame beam 1, a head 2 and a tail 4, the head 2 and the tail 4 are connected by the frame beam 1, two flapping-wing mechanisms 3 are symmetrically arranged in the middle position of the frame beam 1, a power mechanism 5 is arranged inside the frame beam 1, and 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 present invention can realize the flapping-wing aircraft to suspend a large load, does not need to be thrown during takeoff, does not need a runway, and can be monitored at a fixed point.

[0021] 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. The cover plate 22, the bottom plate 23 and one side of 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 cooperate with the cover plate 22 and the bottom plate 23 to form a cone, thereby reducing the wind resistance caused during flight and improving the flight speed of the flapping-wing aircraft.

[0022] Figure 2 , Figure 3 and Figure 4 The tail 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, and the vertical tail 42 is vertically welded 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.

[0023] Figure 2 , Figure 3 and Figure 4 The flapping-wing mechanism 3 shown includes a servo 31, a rocker arm 32, a hinge 33 and a flapping-wing plate 34. The servo 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 assembled on the output end of the servo 31, and the other end of the rocker arm 32 is rotatably connected to the second reinforcing plate 12 through the hinge 33. The pitch moment control is achieved by controlling the flapping-wing plate 34. When the flapping frequency increases, the flapping-wing aircraft raises its head and flies upward, and when the flapping frequency decreases, the flapping-wing aircraft lowers its head and flies downward.

[0024] 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, and the two rotors 53 are respectively assembled on the two output ends of the dual-axis motor 52. The dual-axis motor 52 controls the rotation of the rotors 53 to generate lift. When flying forward, the dual-axis motor 52 controls the rotation of the two rotors 53 to generate lift.

[0025] Working principle: Power control: The design program enables the dual-axis motor 52 to control the rotation of the two rotors 53, while the two servos 31 control the movement of the two flapping wing plates 34, thereby providing lift for the aircraft; Direction control: two servos 31 control two flapping wing plates 34 to control direction with different flapping frequencies; Pitch moment control: Two servos 31 control the movement of two flapping wing plates 34. When the flapping frequency increases, the flapping-wing aircraft raises its head and flies upward. When the flapping frequency decreases, the flapping-wing aircraft lowers its head and flies downward.

[0026] The two servos 31 are controlled by a program so that the two flapping panels 34 have a fast speed when flapping down and a slow speed when flapping up. At the same time, the two dual-axis motors 52 control the two rotors 53 to rotate to generate lift. When flying forward, the dual-axis motors 52 control the two rotors 53 to rotate to generate lift. At the same time, the two flapping panels 34 accelerate the flapping speed under the control of the two servos 31. The airflow generated by the up and down flapping of the flapping panels 34 increases, the airflow acting on the horizontal tail 41 increases, the lift of the flapping panels 34 increases, and the flapping-wing aircraft raises its head and flies forward and upward. When turning, the flapping frequencies of the two flapping panels 34 are different under the differential control of the two servos 31. The forces generated by the flapping of the two flapping panels 34 have different components in the forward direction, generating a yaw moment to achieve a turn.

[0027] Based on the above ideal embodiments of the present invention, the relevant staff can make various changes and modifications without departing from the technical concept of the present invention through the above description. The technical scope of the present invention is not limited to the contents of the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A flapping-wing aircraft combined with a rotor, comprising a frame beam (1), a head (2) and a tail (4), characterized in that: The head (2) and the tail (4) are connected via 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); and a first reinforcing plate (11) and a second reinforcing plate (12) are welded and fixed to the inner wall of the frame beam (1).

2. The flapping-wing aircraft combined with a rotor according to claim 1, characterized in that: The head (2) comprises 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); and the surfaces of the two side plates (21) are respectively welded and fixed to the cover plate (22) and the bottom plate (23).

3. The flapping-wing aircraft combined with a rotor according to claim 1, characterized in that: The tail portion (4) comprises a horizontal tail wing (41) and a vertical tail wing (42); the horizontal tail wing (41) is welded and fixed to a side of the frame beam (1) away from the head portion (2); and the vertical tail wing (42) is vertically welded to a middle portion of the horizontal tail wing (41).

4. The flapping-wing aircraft combined with a rotor according to claim 1, characterized in that: The flapping-wing mechanism (3) comprises a steering gear (31), a rocker arm (32), a hinge (33) and a flapping-wing plate (34); the steering gear (31) is fixedly welded to the first reinforcing plate (11); the rocker arm (32) is fixedly welded to the flapping-wing plate (34); one end of the rocker arm (32) is mounted on the output end of the steering gear (31); and the other end of the rocker arm (32) is rotatably connected to the second reinforcing plate (12) via the hinge (33).

5. The flapping-wing aircraft combined with a rotor according to claim 1, characterized in that: The power mechanism (5) comprises 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); and the two rotors (53) are respectively mounted on two output ends of the dual-axis motor (52).

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