Bionic butterfly aircraft

Abstract

The utility model relates to the field of bionic butterflies, in particular to a bionic butterfly aircraft which comprises a mounting plate, at least two swing rods are symmetrically arranged on the mounting plate, rocking rods are arranged on the swing rods, front wings are symmetrically connected to the two rocking rods, a mounting rod is jointly and rotatably connected between the two front wings, and rear wings are further symmetrically connected to the mounting rod. The mounting plate is further provided with a driving piece used for driving the swing rod to swing. According to the utility model, the driven gear, the driven gear, the reduction gear and the driving gear are meshed with one another, so that the flapping frequency of wings on two sides is uniform, the torsion inertia is reduced, and meanwhile, the deflection of the wings is continuously and finely adjusted and the direction is corrected in the flight by utilizing digital steering engine control and algorithm, so that the effect of directional linear flight is realized.

Description

Technical Field

[0001] The utility model relates to the field of bionic butterflies, in particular to a bionic butterfly aircraft. Background Art

[0002] Bionic butterflies are derived from human beings' in-depth exploration and awe of biodiversity and biological mechanisms in nature. By imitating the biological structure, behavior and function of butterflies, we can improve and optimize existing engineering design and technical applications, especially in the fields of robotics and aircraft design. By imitating the flight mechanism of butterflies, we can design more flexible and efficient flying robots, which have important application value in unmanned reconnaissance, environmental monitoring and other fields. By learning from the structural characteristics of butterfly wings, we can improve the wing design of aircraft, reduce energy consumption, reduce noise, and improve controllability and stability.

[0003] However, when ordinary bionic butterfly aircraft turn in flight, they usually increase the wing area on one side or use dual power sources to perform differential wing flapping. For the current method of increasing the wing area on one side to achieve attitude control, due to the small increased wing area, the yaw and roll force generated during the actual movement process is still insufficient. For differential flapping, there is often a phenomenon of unequal lift and inconsistent flapping amplitude before attitude adjustment.

[0004] Therefore, based on the above-stated viewpoints, there is still room for improvement in the existing bionic butterfly aircraft. Utility Model Content

[0005] In order to solve the above problems, the utility model provides a bionic butterfly aircraft, including a mounting plate, on which at least two rocker arms are symmetrically arranged, on which rocker arms are arranged, front wings are symmetrically connected to the two rocker arms, a mounting rod is connected between the two front wings for common rotation, a rear wing is also symmetrically connected to the mounting rod, and a driving member for driving the rocker arm to swing is also arranged on the mounting plate.

[0006] Preferably, the lower ends of the wing surfaces of the front and rear wings are provided with limiting bars connected to the rockers, and a supporting frame connected to the front and rear wings is formed between all the limiting bars, rockers and mounting rods.

[0007] Preferably, the driving member comprises a passive gear symmetrically mounted on the mounting plate, a connecting pin rod is eccentrically arranged on the passive gear, and a connecting bar rod connected to the rocker arm is sleeved on the connecting pin rod.

[0008] Preferably, the two passive gears are meshed with each other, and a driven gear is also meshed on any one of the passive gears. A driven wheel rod connected to the mounting plate is passed through the middle of the driven gear, and a reduction gear is also sleeved on the driven wheel rod. A driving gear is meshed on the reduction gear, and a rotating shaft is passed through the driving gear. A driving motor is connected to the end of the rotating shaft away from the driving gear.

[0009] Preferably, a steering member is provided at the lower side of the mounting rod, and the steering member comprises at least two servos symmetrically arranged at the lower end of the supporting frame, and the servos are provided with a control bar connected to the rear wing for driving the connected rear wing to swing.

[0010] Preferably, a counterweight sleeve is provided at one end of the mounting rod away from the rocker arm.

[0011] Preferably, at least two limit struts are commonly arranged between the two swing arms, and the two limit struts are symmetrically located at two opposite sides of the swing arm.

[0012] Preferably, the wing surface material of the front wing and the rear wing is P31N kite cloth, and the front wing and the rear wing located on the same side of the mounting rod are flexibly connected together.

[0013] In summary, the present application includes at least one of the following beneficial technical effects:

[0014] 1. The utility model utilizes the structure of a servo plus a control bar to simulate the muscles of the butterfly's hind wing. Through the flexible connection structure between the front and rear wings, the hind wing surface can be deflected while the front wing surface can be driven, and the flapping of the front wing surface does not affect the hind wing surface. When turning, the hind wing surface deflects, driving the wings on both sides to move to produce a phase difference and generate a torsional torque, so that the bionic butterfly turns and achieves the effect of tailless turning.

[0015] 2. The utility model utilizes the mutual engagement between the passive gear, the driven gear, the reduction gear and the driving gear to ensure the uniform flapping frequency of the wings on both sides and reduce the torsional inertia. At the same time, it utilizes digital servo control and algorithms to continuously fine-tune the wing deflection and correct the direction during flight to achieve the effect of directional straight-line flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0017] Figure 1 It is a structural schematic diagram of the utility model.

[0018] Figure 2 It is a structural schematic diagram of the utility model from another viewing angle.

[0019] Figure 3 It is a structural schematic diagram of the driving component of the utility model.

[0020] Figure 4 It is a structural schematic diagram of the passive gear of the utility model.

[0021] Figure 5 It is a structural schematic diagram of the driving gear of the utility model.

[0022] Figure 6 It is a cross-sectional view of the mounting plate of the utility model.

[0023] Figure 7 It is a structural schematic diagram of the steering member of the utility model.

[0024] In the figure, 1, mounting plate; 10, rocker arm; 11, rocker arm; 12, front wing; 13, mounting rod; 14, rear wing; 15, limit bar; 2, driving member; 20, passive gear; 21, connecting pin rod; 22, connecting bar; 23, driven gear; 24, driven wheel rod; 25, reduction gear; 26, driving gear; 27, rotating shaft; 28, driving motor; 3, steering member; 30, servo; 31, control bar; 4, counterweight sleeve; 5, limit support rod. DETAILED DESCRIPTION

[0025] The following is combined with Figure 1 To Attachment Figure 7 Although the embodiments of the present invention have been described in detail, the present invention can be implemented in many different ways as defined and covered by the claims.

[0026] The embodiment of the present application discloses a bionic butterfly aircraft, which explains that the bionic butterfly aircraft is mainly used in the process of simulating butterfly flight experiments, and can simulate the flight effect of a butterfly flying state in terms of technical effects; in particular, by utilizing the mutual meshing state between gears, the flapping frequency of the wings on both sides is guaranteed to be unified, thereby achieving the effect of directional straight-line flight; further, the bionic butterfly aircraft also controls the rotation of the servo to achieve the relative position movement of the simulated bionic butterfly wings, thereby generating a rolling torque to roll the fuselage, thereby achieving the effect of tailless steering.

[0027] Reference Figure 1 and Figure 2 As shown, a bionic butterfly aircraft comprises a mounting plate 1, a rocker 10, a rocking arm 11, a front wing 12, a mounting rod 13, a rear wing 14 and a driving member 2. At least two rocker arms 10 are symmetrically arranged on the mounting plate 1. The rocker arms 10 are limitedly sleeved on the mounting plate 1. A rocker arm 11 is arranged on the rocker arm 10. The front wings 12 are symmetrically connected to the two rocker arms 11. The two front wings 12 are symmetrically connected to the mounting rod 13 for common rotation. The rear wing 14 is also symmetrically connected to the mounting rod 13. A driving member 2 for driving the rocker arms 10 to swing is also arranged on the mounting plate 1.

[0028] When in use, the driving member 2 drives the rocker 11 and the swing arm 10 to swing, and the rocker 11 drives the connected front wing 12 and rear wing 14 to swing, so as to achieve the effect of making the device fly in the air.

[0029] Reference Figure 2 As shown, the lower ends of the wing surfaces of the front wing 12 and the rear wing 14 are provided with limiting bars 15 connected to the rocker 11, and a supporting frame connected to the front wing 12 and the rear wing 14 is formed between all the limiting strips, the rocker 11 and the mounting rod 13.

[0030] When in use, the basic form of the bionic butterfly aircraft is constructed by the mutual cooperation of the limiting strips, the rocker 11 and the mounting rod 13, so that the front wing 12 and the rear wing 14 are limitedly connected to the limiting frame, and the front wing 12 and the rear wing 14 are supported and installed by the limiting frame, so as to limit the swinging path of the front wing 12 and the rear wing 14.

[0031] Reference Figures 3 to 6 As shown, the driving member 2 includes a passive gear 20, a connecting pin 21 and a connecting bar 22. The passive gear 20 is symmetrically mounted on the mounting plate 1. The passive gear 20 is eccentrically provided with a connecting pin 21. The connecting bar 22 connected to the rocker arm 10 is sleeved on the connecting pin 21. One end of the connecting bar 22 away from the connecting pin 21 is rotatably connected to the rocker arm 10. When in use, the passive gear 20 is driven to rotate, and the passive gear 20 rotates to drive the connected connecting bar 22 to swing. Due to the eccentric connection between the connecting bar 22 and the passive gear 20, the passive gear 20 rotates to drive the connecting pin 21 between the connecting bar 22 to rotate circumferentially around the axis of the passive gear 20, thereby driving one end of the connected connecting bar 22 to swing circumferentially, and then driving the connected swing rod 10 and the rocker 11 to swing, achieving the effect of driving the front wing 12 to flap up and down. In the process of upward paddling, the front wing 12 and the rear wing 14 are cup-shaped to form an air vortex. When the two front wings 12 swing in a direction close to each other, the air in the middle air vortex is squeezed out to form a backward airflow, which pushes the butterfly forward.

[0032] Further, refer to Figures 3 to 6As shown, the two passive gears 20 are meshed with each other, and a driven gear 23 is also meshed on any one of the passive gears 20. A driven wheel rod 24 rotatably connected to the mounting plate 1 is penetrated in the middle of the driven gear 23, and a reduction gear 25 is also sleeved on the driven wheel rod 24. The rotation of the driven gear 23 drives the driven wheel rod 24 and the reduction gear 25 to rotate with the driven wheel rod 24 as the axis; a driving gear 26 is meshed on the reduction gear 25, and the driving gear 26, the reduction gear 25, the driven wheel rod 24 and the driven gear 23 together constitute a reduction group, and a rotating shaft 27 is penetrated on the driving gear 26, and a driving motor 28 is connected to the end of the rotating shaft 27 away from the driving gear 26.

[0033] When in use, the rotating shaft 27 is driven to rotate by the driving motor 28, and the rotating shaft 27 rotates to drive the driving gear 26 to rotate, and the driving gear 26 rotates to drive the meshing reduction gear 25 to rotate, and at the same time drives the driven wheel rod 24 and the driven gear 23 to rotate, and the driven gear 23 rotates to drive one of the meshing driven gears 20 to rotate, and the driven gear 20 rotates to drive the other meshing driven gear 20 to rotate, so as to achieve the effect of driving the connecting bar 22 and the front wing 12 to swing up and down, and by controlling the rotation speed of the driving motor 28 and the reduction group limiting the rotation speed of the output shaft of the driving motor 28, the effect of controlling the swing rate of the rocker 11 and the rocker 10 is achieved, thereby achieving the effect of controlling the speed of the flapping of the aircraft. The driving motor 28 in this embodiment is a hollow cup motor, which can drive the rotating shaft 27 to rotate more smoothly when in use.

[0034] Reference Figure 7 As shown, a steering member 3 for driving the aircraft to turn is arranged at the lower side of the mounting rod 13, and the steering member 3 includes a steering gear 30 and a control bar 31. At least two steering gears 30 are symmetrically arranged at the lower end of the support frame, and a control bar 31 connected to the rear wing 14 is arranged on the steering gear 30, which is used to drive the connected rear wing 14 to swing. When in use, the steering gear 30 drives the connected control bar 31 to rotate an angle, and the rotation of the control bar 31 drives the connected rear wing 14 to rotate, so that an angle is formed between the rear wing 14 and the front wing 12, and the relative position of the entire wing is changed, so as to achieve the effect of making the aircraft turn as a whole.

[0035] Reference Figure 7 As shown, the abdomen of the butterfly has the function of improving the flight stability during the flight, and the change of the flight speed is achieved by changing the pitch of the abdomen. Therefore, a counterweight sleeve 4 is provided at the end of the mounting rod 13 away from the rocker arm 10 to increase the stability of the device during flight. The counterweight sleeve 4 is a rubber sleeve.

[0036] Reference Figure 6As shown, at least two limit struts 5 are provided for common rotation between the two swing rods 10, the two limit struts 5 are symmetrically located at two opposite sides of the swing rod 10, and a limit frame connected to the mounting plate 1 is provided between the opposite sides of the two limit struts 5, and the limit frame rotates through the swing rod 10 and is connected to the limit struts 5. When in use, the connected swing rod 10 is driven to swing by eccentric rotation of the connecting bar 22, and the swing rod 10 swings around the through axis between the connected limit frames and drives the connected swing rod 10 to swing at the same time.

[0037] Reference Figure 1 As shown, the wing surface material of the front wing 12 and the rear wing 14 is P31N kite cloth, and the front wing 12 and the rear wing 14 on the same side of the mounting rod 13 are flexibly connected together. When the wing surface of a real butterfly slides upward, the wings are cup-shaped, forming a pocket filled with air between them. When the wings collide, the air will be squeezed out, forming a backward airflow, pushing the butterfly forward, so P31N kite cloth is selected as the wing surface of the bionic butterfly. It is very light and can reduce the weight of the bionic butterfly, thereby improving the flight performance. It is also very strong and can withstand strong winds during flight and maintain structural stability. It also has the characteristics of durability and low air permeability.

[0038] When in use, for example, when turning left, the left servo 30 is controlled to drive the connected control bar 31 to move downward, thereby driving the rear wing 14 to tilt downward, and the opposite servo 30 drives the control bar 31 to move upward, so that the opposite rear wing 14 tilts upward. Because the rear wing 14 and the front wing 12 are flexibly connected, when the angle of the rear wing 14 changes, the angle of the front wing 12 will also change, thereby changing the relative position of the entire wing. Due to the change in the relative position of the entire wing, the cyclonic vortex and the upper and lower airflows of the wing surface generate a rolling moment to roll the fuselage, so that the horizontal components of the lift of the left and right wings generate a yaw moment, thereby achieving the effect of turning left. It should be noted that the rear wing 14 of the butterfly aircraft is not used to provide flight lift, but is specifically used to enhance the flexibility of the body when turning.

[0039] It should be noted that, in order to facilitate the control of the flight path of the butterfly aircraft in the air, a controller is provided on the aircraft for receiving signals and controlling the drive motor 28 and the servo 30. A remote controller is also provided outside the aircraft for outputting signals to control the aircraft. A battery is provided between the two servos 30. The battery is powered by a 3.7V, 80mah battery with a single flight time of 5 minutes. The drive motor 28 and the two servos 30 are connected to the battery through electrical wires, and the drive motor 28 is limitedly installed on the outer side of the battery.

[0040] When in use, by operating the remote control, the remote control sends a signal which is received by the controller on the aircraft, driving the servo 30 and the drive motor 28 to operate, so as to make the aircraft automatically hover in the air, and to operate flight acceleration, deceleration, left and right flying, U-turn and other functions, so as to achieve the effect of controlling the flight path of the aircraft in the air.

[0041] During operation: the first step is to start the drive motor 28, and drive the reduction group to rotate through the drive motor 28, thereby driving the swing arm 10 and the rocker arm 11 to swing up and down, thereby achieving the effect of flapping wings up and down.

[0042] Step 2: After the aircraft flies to a certain height, a signal is sent through the remote controller to drive the steering gear 30 to operate, and the operation of the steering gear 30 drives the connected control bar 31 to swing, thereby driving the connected rear wing 14 to deflect an angle, so that the aircraft can turn in the air.

[0043] Step 3: After the flight is completed, a signal is sent again through the remote controller to slow down the rotation rate of the drive motor 28, so that the frequency of flapping wings is reduced, thereby causing the aircraft to slowly fall in the air.

[0044] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0045] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description 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 may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A bionic butterfly aircraft, comprising a mounting plate (1), characterized in that: At least two swing arms (10) are symmetrically arranged on the mounting plate (1), a rocker (11) is arranged on the swing arm (10), front wings (12) are symmetrically connected to the two rockers (11), a mounting rod (13) is rotatably connected between the two front wings (12), a rear wing (14) is symmetrically connected to the mounting rod (13), and a driving member (2) for driving the swing arm (10) to swing is also arranged on the mounting plate (1).

2. A bionic butterfly flying vehicle according to claim 1, characterized in that: The lower ends of the wing surfaces of the front wing (12) and the rear wing (14) are both provided with limiting bars (15) connected to the rocker (11), and a supporting frame connected to the front wing (12) and the rear wing (14) is formed between all the limiting bars, the rocker (11) and the mounting rod (13).

3. The bionic butterfly flying vehicle according to claim 1, characterized in that: The driving member (2) comprises a passive gear (20) symmetrically mounted on the mounting plate (1), a connecting pin (21) being eccentrically arranged on the passive gear (20), and a connecting bar (22) connected to the swing rod (10) being sleeved on the connecting pin (21).

4. The bionic butterfly flying vehicle according to claim 3, characterized in that: The two passive gears (20) are meshed with each other, and a driven gear (23) is meshed on any one of the passive gears (20). A driven wheel rod (24) connected to the mounting plate (1) is passed through the middle of the driven gear (23), and a reduction gear (25) is sleeved on the driven wheel rod (24). A driving gear (26) is meshed on the reduction gear (25), and a rotating shaft (27) is passed through the driving gear (26). The end of the rotating shaft (27) away from the driving gear (26) is connected to a driving motor (28).

5. The bionic butterfly flying vehicle according to claim 1, characterized in that: A steering member (3) is arranged at the lower side of the mounting rod (13), and the steering member (3) comprises at least two steering gears (30) symmetrically arranged at the lower end of the supporting frame, and a control bar (31) connected to the rear wing (14) is arranged on the steering gear (30) for driving the connected rear wing (14) to swing.

6. The bionic butterfly flying vehicle according to claim 1, characterized in that: A counterweight sleeve (4) is provided at one end of the mounting rod (13) away from the swing rod (10).

7. The bionic butterfly flying vehicle according to claim 1, characterized in that: At least two limiting struts (5) are commonly arranged between the two swing rods (10), and the two limiting struts (5) are symmetrically located at two opposite sides of the swing rod (10).

8. The bionic butterfly flying vehicle according to claim 1, characterized in that: The wing surface material of the front wing (12) and the rear wing (14) is P31N kite cloth, and the front wing (12) and the rear wing (14) located on the same side of the mounting rod (13) are flexibly connected together.

Images