Lightweight bionic butterfly aircraft

Abstract

The utility model discloses a lightweight bionic butterfly aircraft, which relates to the technical field of bionic aircrafts and comprises a front wing and a rear wing. The front wing and the rear wing are respectively composed of a carbon fiber framework and a thermoplastic polyester film and comprise a left wing and a right wing, and the front ends of the left wing and the right wing of the front wing and the rear wing are hinged to the two sides of the front-back connecting piece; the front connecting piece and the rear connecting piece are connected through a carbon fiber connecting rod, and the tail end of the carbon fiber connecting rod is located at the rear end of the rear wing. A coreless motor is arranged on the front connecting piece, and the output end of the coreless motor is connected with the front end of the front wing through a gear transmission mechanism and a reciprocating connecting rod mechanism in sequence; the front wing and the rear wing are connected through a flexible string, and the connecting position is located between the rear edge of the front wing and the front edge of the rear wing. Steering engines are arranged at the tail ends of the carbon fiber connecting rods, and rudder arms of the steering engines are connected to wing tips of the left wing and the right wing of the front wing through flexible thin ropes. The weight is greatly reduced while the strength is guaranteed, and the flying direction is rapidly adjusted.

Description

Technical Field

[0001] This utility model belongs to the field of biomimetic aircraft and relates to a lightweight biomimetic butterfly aircraft. Background Technology

[0002] The main design principle of the biomimetic butterfly aircraft is to mimic the flight mechanism of a butterfly, including the flapping of its wings and its aerodynamic characteristics.

[0003] Traditional biomimetic aircraft mostly employ fixed-amplitude flapping wing structures, which suffer from drawbacks such as poor maneuverability, high energy consumption, and short range. Some designs attempt to control steering using dual servos, but these structures are complex and have slow response times. Furthermore, existing biomimetic butterfly aircraft have excessively rigid wings, making it difficult to simulate the flexible deformation of a real butterfly, resulting in low lift efficiency. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a lightweight biomimetic butterfly flying machine that significantly reduces weight while maintaining strength and enables rapid adjustment of flight direction.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A lightweight biomimetic butterfly flying machine, comprising forewings and hindwings;

[0007] The forewing and hindwing are made of carbon fiber skeleton and thermoplastic polyester film respectively. Both the forewing and hindwing include left and right wings. The front ends of the left and right wings of the forewing are hinged to the two sides of the front connector through the forewing fixing hinge. The front ends of the left and right wings of the hindwing are hinged to the two sides of the rear connector through the rear wing fixing hinge.

[0008] The front connector and the rear connector are connected by a carbon fiber connecting rod, with the end of the carbon fiber connecting rod located at the rear end of the rear wing.

[0009] A hollow cup motor is installed on the front connector. The output end of the hollow cup motor is connected to the front end of the front wing in sequence through a gear transmission mechanism and a reciprocating linkage mechanism.

[0010] The forewings and hindwings are connected by a flexible thin rope, with the connection point located between the trailing edge of the forewing and the leading edge of the hindwing.

[0011] A servo motor is installed at the end of the carbon fiber connecting rod, and the servo motor arm is connected to the wingtips of the left and right wings of the forewing via a flexible thin rope.

[0012] Preferably, there is an overlapping area between the trailing edge of the forewing and the leading edge of the hindwing, with the overlapping area being 10%-15% of the total area of ​​the forewing and hindwing.

[0013] Preferably, the gear transmission mechanism includes a central reduction gear, a left drive gear, and a right drive gear. The central reduction gear meshes with the output end of the hollow cup motor, and the left drive gear and the right drive gear are each connected to a reciprocating linkage mechanism.

[0014] Preferably, the front end of the reciprocating linkage mechanism is connected to the front wing fixed hinge via a hinge.

[0015] Preferably, the forewing includes primary veins and secondary veins, with the primary veins located at the leading edge and middle of the forewing, and the secondary veins located at the trailing edge of the forewing and the edge of the hindwing.

[0016] Preferably, the main wing veins are composed of carbon fiber rods with diameters of 1.0 mm and 0.8 mm, and the secondary wing veins are composed of carbon fiber rods with a diameter of 0.5 mm.

[0017] Preferably, the wing membrane is made of a thermoplastic polyester film with a thickness of 0.1 mm, which is glued to the carbon fiber skeleton of the forewing and hindwing.

[0018] Preferably, a flight control module is provided on the rear connector, and the coreless motor is connected to the servo and the flight control module via a cable.

[0019] Preferably, the flight control module includes a receiver, a controller, and an ESC. The receiver is used to receive external signals, and the controller is electrically connected to the coreless motor and servo motor.

[0020] Preferably, a battery is provided at the end of the carbon fiber connecting rod, and the battery is connected to the hollow cup motor and the servo motor.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] This invention employs a composite structure of carbon fiber skeleton and thermoplastic polyester film, significantly reducing weight while maintaining strength. Flight direction can be rapidly adjusted remotely: the tail servo is electrically connected to the main flight control board, and the wing attitude during flight is finely adjusted via flexible ropes attached to the tips of the left and right forewings using the servo joystick. A continuous power transmission system is used: the forewings and hindwings partially overlap and are connected by flexible ropes, simulating the flexible deformation of a real butterfly to avoid lift interruption and extend gliding time; a centralized power supply and control system at the tail improves flight stability by optimizing the center of gravity distribution; the coreless motor and differential gear set work together, combined with wireless communication, to achieve remote and precise control. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of the biomimetic butterfly flying device of this utility model;

[0024] Figure 2 This is a schematic diagram of the gear transmission mechanism of this utility model;

[0025] Figure 3 This is a schematic diagram of the transmission principle of the gear transmission mechanism of this utility model.

[0026] Among them, 1. Gear transmission mechanism; 2. Front connector; 3. Rear connector; 4. Carbon fiber connecting rod; 5. Forewing fixing hinge; 6. Rearwing fixing hinge; 7. Forewing; 8. Rearwing; 9. Central reduction gear; 10. Left drive gear; 11. Right drive gear; 12. Reciprocating linkage mechanism; 13. Flexible thin rope. Detailed Implementation

[0027] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.

[0028] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0029] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terms “installation,” “connection,” and “linkage” should be interpreted broadly, for example, as a fixed connection, a detachable connection, or an integral connection; a mechanical connection, an electrical connection, or a connection that allows communication; a direct connection or an indirect connection via an intermediate medium; or a connection within two elements or an interaction between two elements. The term “and / or” as used herein includes any and all combinations of one or more of the associated listed items. Those skilled in the art will understand the specific meaning of the above terms in this invention according to the specific circumstances. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention.

[0030] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0031] The following disclosure provides many different embodiments or examples for implementing various structures of this invention. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of the invention. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, examples of various specific processes and materials are provided in this invention, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0032] Any adaptive changes made according to actual needs are within the protection scope of this utility model.

[0033] like Figure 1As shown, the lightweight biomimetic butterfly aircraft of this embodiment includes a gear transmission mechanism 1, a front connector 2, a rear connector 3, a carbon fiber connecting rod 4, a forewing fixing hinge 5, a rear wing fixing hinge 6, a forewing 7, and a rear wing 8. It also includes a reciprocating linkage mechanism 12, a flexible thin rope 13, and a control system, which constitute a head transmission system, a wing flapping system, a steering control system, a flight control system, and a tail power supply and balance system.

[0034] Both the forewing 7 and the hindwing 8 include left and right wings. The front ends of the left and right wings of the forewing 7 are connected by a front connector 2. The front ends of the left and right wings of the forewing 7 are hinged to both sides of the front connector 2 by forewing fixing hinges 4. The front ends of the left and right wings of the hindwing 8 are connected by a rear connector 3. The front ends of the left and right wings of the hindwing 8 are hinged to both sides of the rear connector 3 by rear wing fixing hinges 5. The front connector 2 and the rear connector 3 are connected by a carbon fiber connecting rod 4, with the end of the carbon fiber connecting rod 4 located at the rear end of the hindwing 8.

[0035] The forewing 7 and hindwing 8 together constitute a biomimetic wing flapping system, constructed from a carbon fiber skeleton and a thermoplastic polyester film composite. The main wing veins, located at the leading edge and middle of the forewing 7, are made of carbon fiber rods with diameters of 1.0 mm and 0.8 mm, ensuring rigidity and lift support. The secondary wing veins are distributed along the trailing edge of the forewing 7 and the edge of the hindwing 8, using carbon fiber rods with a diameter of 0.5 mm to enhance the overall elastic structure. The forewing and hindwings are connected by a flexible thin rope 13, with the overlapping area accounting for 12% of the total wing surface area. The connection point is located between the wing edge of the hindwing 8 and the tip of the hindwing vein of the forewing 7.

[0036] The flexible cord 13 is made of cotton and has moderate elasticity and extensibility. It buffers instantaneous load fluctuations during flight while maintaining power transmission efficiency, and its length can be adjusted within a range of 58 mm. This connection structure mimics the synchronous movement of the forewings and hindwings of a real swallowtail butterfly, ensuring the continuity of force transmission during wing flapping and preventing lift interruption.

[0037] like Figure 2 and Figure 3 As shown, the head transmission system includes a 617 hollow cup motor mounted on the front connector 2. Its output shaft meshes with a central reduction gear 9 within the gear transmission mechanism 1, with a reduction ratio of 1:8. The gear transmission mechanism 1 also includes a left drive gear 10 and a right drive gear 11. The central reduction gear 9 meshes with the right drive gear 11, and the left drive gear 10 and right drive gear 11 mesh with each other. The left drive gear 10 and right drive gear 11 are respectively connected to the left and right wing front hinges 5 of the forewing 7 via reciprocating linkage mechanisms 12, thereby achieving symmetrical reciprocating flapping of the left and right wings of the forewing 7. The hollow cup motor has a rated voltage of 3.7V and a maximum speed of approximately 45,000 rpm, capable of driving the forewing 7 to produce vertical vibrations with an amplitude of ±25° at a frequency of 10Hz.

[0038] The reciprocating linkage mechanism 12 is 3D printed from photosensitive resin material and is connected to the forewing hinge 5 via a hinge, so that its end can drive the forewing 7 to produce flexible bending and twisting, thereby enhancing the aerodynamic response capability of the wing.

[0039] The fin membrane is made of 0.1mm thick thermoplastic polyester film and is fixed to the carbon fiber frame with B7000 adhesive. A partial elastic release area is reserved at the fin vein connection to accommodate deformation caused by airflow disturbances and improve the fin's lift efficiency.

[0040] The flight control system is mounted on rear connector 3 and integrates an AR3201 receiver, a PID controller, and a micro ESC. The receiver enables 2.4GHz wireless communication with the remote transmitter, receiving control signals from the transmitter. These control signals are then output to the coreless motor and servo motors via the PID controller, achieving precise control of flight attitude and power output. The module weighs no more than 1.5g, has a maximum control frequency of 100Hz, and a system response delay of less than 0.5 seconds.

[0041] The steering control system is mounted at the end of the carbon fiber connecting rod 4 and includes a miniature digital servo weighing 3g. Its servo arm is connected to the wingtips of the left and right forewings 7 via flexible thin ropes 13. When the servo deflection angle changes, the amplitude of the left and right wings is adjusted through differential tension, thereby achieving left-right flight attitude adjustment. Compared with traditional dual-rudder systems, this structure is simpler and more efficient, with advantages such as lightweight structure and rapid response.

[0042] The aircraft's power supply balancing system is located at the end of the carbon fiber connecting rod 4, and includes a 40mAh, 2g lithium polymer battery that powers the coreless motor, flight control system, and servos. The lithium battery is connected to the carbon fiber connecting rod 4, and its placement keeps the aircraft's center of gravity about one-third of the way behind the rear connector 3, effectively improving overall flight stability and gliding ability.

[0043] In flight tests, under windless indoor conditions, takeoff was conducted with 80% throttle input. The coreless motor output speed was 31,000 rpm, the flapping frequency was maintained at 9.8~10.2Hz, and the peak lift was approximately 0.15N. The aircraft could achieve stable flight for a maximum of approximately 12 minutes. Steering control was achieved through servo motor oscillation, resulting in an average yaw angle change of 12° / s in the left and right directions, with a response delay consistently within 0.35 seconds.

[0044] During the assembly process, the carbon fiber connecting rod 4 is made of high-modulus carbon fiber and shaped by hot pressing mold. The wing membrane is laser-cut according to the biomimetic swallowtail butterfly pattern and then bonded to the wing veins. All electrical connections are hand-soldered using heat-resistant enameled wire and sealed with UV glue for protection. After the aircraft is assembled, flight control initialization, center of gravity testing, frequency calibration, and servo angle calibration are required to ensure that the flight attitude response is consistent with the remote control logic.

[0045] This lightweight biomimetic butterfly flying vehicle can be widely used in environmental monitoring, biomimetic teaching, smart toys, agricultural observation and other scenarios. It also has good scalability and can be equipped with sensors to perform data acquisition tasks or cooperate with AI image recognition systems for target tracking research.

[0046] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0047] In the above embodiments of this application, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0048] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units can be a logical functional division, and in actual implementation, there may be other division methods. For instance, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual coupling, direct coupling, or communication connection may be through some interfaces; the indirect coupling or communication connection between units or modules may be electrical or other forms.

[0049] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0050] The above description is only a preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

[0051] It should be understood that the above description is for illustrative purposes and not for limitation. Many embodiments and applications beyond the provided examples will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of this patent should not be determined by reference to the above description, but rather by reference to the foregoing claims and the full scope of their equivalents. For purposes of completeness, all articles and references, including patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended as a waiver of that subject matter, nor should it be construed as an indication that the applicant has not considered that subject matter as part of the disclosed utility model subject matter.

Claims

1. A lightweight biomimetic butterfly flying machine, characterized in that, Including the forewings (7) and hindwings (8) The forewing (7) and the hindwing (8) are respectively composed of a carbon fiber skeleton and a wing membrane. Both the forewing (7) and the hindwing (8) include left and right wings. The front ends of the left and right wings of the forewing (7) are hinged to the front connector (2) on both sides through the forewing fixing hinge (5). The front ends of the left and right wings of the hindwing (8) are hinged to the rear connector (3) on both sides through the rear wing fixing hinge (6). The front connector (2) and the rear connector (3) are connected by a carbon fiber connecting rod (4), with the end of the carbon fiber connecting rod (4) located at the rear end of the rear wing (8); A hollow cup motor is provided on the front connector (2). The output end of the hollow cup motor is connected to the front end of the front wing (7) in sequence through a gear transmission mechanism (1) and a reciprocating linkage mechanism (12). The forewing (7) and hindwing (8) are connected by a flexible thin rope (13), with the connection point located between the trailing edge of the forewing (7) and the leading edge of the hindwing (8); A servo motor is provided at the end of the carbon fiber connecting rod (4), and the servo arm of the servo motor is connected to the wingtips of the left and right wings of the forewing (7) via a flexible thin rope (13).

2. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, An overlapping area is provided between the trailing edge of the forewing (7) and the leading edge of the hindwing (8), with the overlapping area being 10%-15% of the total area of ​​the forewing (7) and the hindwing (8).

3. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, The gear transmission mechanism (1) includes a central reduction gear (9), a left drive gear (10) and a right drive gear (11). The central reduction gear (9) meshes with the output end of the hollow cup motor. The left drive gear (10) and the right drive gear (11) are each connected to a reciprocating linkage mechanism (12).

4. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, The front end of the reciprocating linkage mechanism (12) is connected to the front wing fixed hinge (5) via a hinge.

5. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, The forewing (7) includes primary veins and secondary veins. The primary veins are located at the leading edge and middle of the forewing (7), while the secondary veins are located at the trailing edge of the forewing (7) and the edge of the hindwing (8).

6. The lightweight biomimetic butterfly flying vehicle according to claim 5, characterized in that, The main wing veins are composed of carbon fiber rods with diameters of 1.0 mm and 0.8 mm, while the secondary wing veins are composed of carbon fiber rods with a diameter of 0.5 mm.

7. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, The wing membrane is made of thermoplastic polyester film with a thickness of 0.1 mm and is glued to the carbon fiber skeleton of the forewing (7) and hindwing (8).

8. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, The rear connector (3) is equipped with a flight control module, and the hollow cup motor is connected to the servo and the flight control module via a cable.

9. The lightweight biomimetic butterfly flying vehicle according to claim 8, characterized in that, The flight control module includes a receiver, a controller, and an ESC. The receiver is used to receive external signals, and the controller is electrically connected to the coreless motor and servo motor.

10. The lightweight biomimetic butterfly flying vehicle according to claim 1, characterized in that, A battery is installed at the end of the carbon fiber connecting rod (4), and the battery connects the hollow cup motor and the servo motor.

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