Aircraft based on bionic butterfly

Abstract

The aircraft based on the bionic butterfly comprises a rack, a wing fixing part, a power module and a transmission mechanism, the rack is of a plate-shaped hollow structure and is vertically arranged, two first assembly holes are symmetrically formed in the top of the rack, two second assembly holes are symmetrically formed in the bottom of the rack, the first assembly holes are used for installing the wing fixing part, and the second assembly holes are used for installing the wing fixing part. The second assembly holes are used for mounting the driving motors in the power module, and the driving motors and the transmission mechanisms are arranged in two groups and are used for respectively controlling the flapping speed of the flapping wings fixed on the wing fixing parts. According to the aircraft based on the bionic butterfly, the flapping speeds of the two flapping wings can be controlled respectively, so that flight steering is achieved, a matched structural part used for deformation of the flapping wings does not need to be additionally arranged on a wing fixing part, the design space of a transmission mechanism is large, the structural strength is easier to guarantee, and the design cost is low. Therefore, the reliability of the aircraft based on the bionic butterfly can be effectively guaranteed.

Description

Technical Field

[0001] This utility model relates to the field of flapping-wing aircraft technology, and in particular to an aircraft based on a biomimetic butterfly. Background Technology

[0002] Bionics is the science of imitating biological systems. It studies the structure, function, and working principles of organisms to provide new design ideas and operating principles for technology and engineering. Butterflies, as a highly distinctive insect in nature, possess advantages such as low frequency, low noise, and low power consumption in their flapping flight, attracting numerous researchers to conduct in-depth studies of their flight mechanisms.

[0003] In existing biomimetic butterfly aircraft, most of them use traction lines to deform the wings on both sides when turning, so that the effective areas of the wings providing lift and thrust are different, thereby achieving the purpose of turning. However, in order to realize the deformability of the wings, matching structural components need to be set on the wing fixing parts. However, the available space on the wing fixing parts is small, which makes the size of the matching structural components small and the structural strength low, thus reducing the reliability of the biomimetic butterfly aircraft. Utility Model Content

[0004] Therefore, the purpose of this utility model is to provide an aircraft based on a biomimetic butterfly, so as to solve the problem that the structural strength of the supporting structural components for the steering design of existing biomimetic butterfly aircraft is low, which reduces the reliability of the biomimetic butterfly aircraft.

[0005] This utility model provides a biomimetic butterfly-based aircraft, comprising: a frame, wing fixing components, a power module, and a transmission mechanism, wherein...

[0006] The frame is a plate-shaped hollow structure and is set upright. The top of the frame is symmetrically provided with two first mounting holes and the bottom is symmetrically provided with two second mounting holes.

[0007] Two wing fasteners are symmetrically arranged at both ends of the top of the frame. The main body of the wing fastener is a plate structure, and a first opening is provided on the inner side. A first rotating shaft parallel to the inner side is provided in the first opening. The wing fastener is embedded into the frame through the first opening. The first rotating shaft is rotatably connected to the first mounting hole. The wing fastener is fixedly connected to the flapping wing.

[0008] The power module includes a control board and two drive motors. The two drive motors are respectively fixedly installed in the two second mounting holes and are respectively communicatively connected to the control board.

[0009] The transmission mechanism is provided in two sets, which are respectively connected between the two drive motors and the two wing fixing parts.

[0010] Optionally, the wing fixing member further includes a downwardly extending hinge lug, the transmission mechanism includes a crank and a rocker arm, the middle part of the crank is fixedly connected to the output shaft of the drive motor, one end of the crank is hinged to one end of the rocker arm, and the other end of the rocker arm is hinged to the hinge lug.

[0011] Optionally, the drive motor is located at the front of the frame, and the transmission mechanism is located at the rear of the frame.

[0012] Optionally, the hinge ear is a single-ear structure, the hinge ear is located behind the first opening, the rocker arm is located on the rear side of the hinge ear, and the lower surface of the wing fixing member is also provided with a first slot, the location of the first slot being consistent with the installation position of the rocker arm.

[0013] Optionally, the inner side of the wing fixing member is further provided with a second opening, the second opening being positioned in the same position as the first slot, and the first rotating shaft passing through the second opening.

[0014] Optionally, the bottom of the frame further includes a bottom support frame extending downwards, and the bottom support frame is provided with a third mounting hole. A longitudinal beam extending towards the rear of the frame is fixedly installed in the third mounting hole, and a power battery is installed on the longitudinal beam.

[0015] Optionally, the longitudinal beam is also provided with a biomimetic abdominal structure.

[0016] Optionally, the control board is positioned above the drive motor, and the control board is also provided with a head-bionic sensor module.

[0017] Optionally, the drive motor is a hollow cup geared motor with a built-in planetary gear reducer.

[0018] Optionally, the wing fixing component is further provided with flapping wing frame assembly holes, which are extended from the front end face, rear end face and outer side face of the wing fixing component.

[0019] This invention provides a biomimetic butterfly-based aircraft comprising: a frame, wing fixing components, a power module, and a transmission mechanism. The frame is a plate-shaped, hollow structure, erected vertically. Two first mounting holes are symmetrically arranged on the top of the frame, and two second mounting holes are symmetrically arranged on the bottom. The first mounting holes are used for mounting the wing fixing components, and the second mounting holes are used for mounting the drive motor in the power module. Two sets of drive motors and transmission mechanisms are provided, each controlling the flapping speed of the wings fixed to the wing fixing components. This biomimetic butterfly-based aircraft can control the flapping speed of the two wings separately, thereby achieving flight steering. It eliminates the need for additional structural components on the wing fixing components for wing deformation. Furthermore, the transmission mechanism has greater design space, making it easier to ensure structural strength, thus effectively guaranteeing the reliability of the biomimetic butterfly-based aircraft. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the biomimetic butterfly-based aircraft of this utility model;

[0021] Figure 2 This is a schematic diagram of the main structure of the biomimetic butterfly-based aircraft of this utility model;

[0022] Figure 3 This is a schematic diagram of the transmission-related structure of the biomimetic butterfly-based aircraft in this utility model;

[0023] Figure 4 This is a schematic diagram of the frame structure of the biomimetic butterfly-based aircraft of this utility model;

[0024] Figure 5 and Figure 6 This is a three-dimensional structural diagram of the wing fixing component of the biomimetic butterfly-based aircraft in this utility model;

[0025] Figure 7 This is a partial cross-sectional structural diagram of the wing fixing component of the biomimetic butterfly-based aircraft of this utility model.

[0026] The following detailed description, in conjunction with the accompanying drawings, will further illustrate this utility model. Detailed Implementation

[0027] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. Several embodiments of this utility model are shown in the drawings. However, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure of this utility model will be more thorough and complete.

[0028] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[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 terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0030] To address the issue of low structural strength in the steering design of existing biomimetic butterfly aircraft, which reduces their reliability, this invention provides a biomimetic butterfly-based aircraft. Each of the two wing fixing components is equipped with a drive motor and transmission mechanism, allowing for independent control of the flapping speed of the wings fixed to the wing fixing components, thus achieving flight steering. This eliminates the need for additional structural components on the wing fixing components for flapping wing deformation, while also providing greater design space for the transmission mechanism and making it easier to ensure structural strength, thereby effectively guaranteeing the reliability of the biomimetic butterfly-based aircraft.

[0031] For details, please refer to Figures 1 to 7 The diagram shows the structural schematics of various parts of the biomimetic butterfly-based aircraft according to an embodiment of this utility model.

[0032] The aircraft in this embodiment mainly consists of a frame 10, a wing fixing component 20, a flapping wing 101, a power module, and a transmission mechanism. The power module, transmission mechanism, and wing fixing component 20 are mounted on the frame 10. The flapping wing 101 is fixedly mounted on the wing fixing component 20. The output power of the power module is transmitted to the wing fixing component 20 through the transmission structure, driving the wing fixing component 20 and the flapping wing 101 fixed on the wing fixing component 20 to flap.

[0033] To achieve the lightweight design requirement, in this embodiment, as follows: Figure 4 As shown, the frame 20 has a plate-shaped hollow structure and is set upright. The top of the frame 20 has two first mounting holes 11 symmetrically arranged for the assembly of the wing fixing parts 20, and the bottom has two second mounting holes 12 symmetrically arranged for the installation of the drive motor 31 in the power module.

[0034] Two wing fasteners 20 are symmetrically arranged at both ends of the top of the frame 10. The main body of the wing fastener 20 is a plate structure, and a first opening 21 is provided on the inner side. A first rotating shaft 201 parallel to the inner side is provided in the first opening 21. The wing fastener 20 is embedded into the frame 10 through the first opening 21. The first rotating shaft 201 is rotatably connected to the first mounting hole 11, so that the wing fastener 20 can rotate around the first rotating shaft 201 and flap.

[0035] The power module mainly includes a control board 32 and two drive motors 31. The two drive motors 31 are respectively fixedly installed in two second mounting holes 12 and are respectively connected to the control board 32 for communication, so that they can work under different working conditions under the control of the control board 32 and the output speed can be differentiated.

[0036] The transmission mechanism is provided in two sets, which are respectively connected between the two drive motors 31 and the two wing fixing parts 20. The two wing fixing parts 20 are driven to flap according to the output speed of the two drive motors 31. By controlling the difference in speed between the two drive motors 31, the flapping speed of the two flapping wings 101 fixed on the two wing fixing parts 20 can be controlled separately, which facilitates the realization of turning.

[0037] To reduce system weight, in this embodiment, such as Figure 3 , Figure 5 and Figure 6 As shown, the wing fixing member 20 also includes a downwardly extending hinge ear 24. The transmission mechanism includes a crank 41 and a rocker arm 42. The middle part of the crank 41 is fixedly connected to the output shaft of the drive motor 31. One end of the crank 41 is hinged to one end of the rocker arm 42, and the other end of the rocker arm 42 is hinged to the hinge ear 24. Compared with gear transmission, the transmission mechanism composed of the crank 41 and the rocker arm 42 is smaller in size, which can effectively reduce the system weight.

[0038] To facilitate balanced weight distribution, in this embodiment, the drive motor 31 is located at the front of the frame 10, and the transmission mechanism is located at the rear of the frame 10.

[0039] To reduce the weight of the connection structure, in this embodiment, the hinge ear 24 is a single-ear structure. The hinge ear 24 is located behind the first opening 21. The rocker arm 42 is located on the rear side of the hinge ear. The lower surface of the wing fixing member 20 is also provided with a first slot 23. The location of the first slot 23 is consistent with the installation position of the rocker arm 42. On the one hand, it can provide room for the rocker arm to move, and on the other hand, it can further reduce the weight of the wing fixing member 20.

[0040] The inner side of the wing fastener 20 is also provided with a second opening 22. The position of the second opening 22 is the same as that of the first slot 23, which can further reduce the weight of the wing fastener 20. The first rotating shaft 201 is also provided through the second opening 22, which can improve the assembly and fixing reliability between the first rotating shaft 201 and the wing fastener 20. The first rotating shaft 201 can also strengthen the mechanical strength of the wing fastener 20 and improve the structural strength of the wing fastener 20.

[0041] To ensure sufficient space for the crank 41 to move, in this embodiment, the bottom of the frame 10 further includes a downwardly extending bottom support frame 13, and the bottom support frame 13 is also provided with a third mounting hole 14. A longitudinal beam extending towards the rear of the frame 10 is fixedly installed in the third mounting hole 14. Figure 2 As shown, a power battery 104 is installed on the longitudinal beam.

[0042] The longitudinal beam is also equipped with a biomimetic abdominal structure 105, which can be used as a system counterweight and for the installation of data processing equipment. It is also equipped with biomimetic outriggers for supporting the aircraft.

[0043] The control board 32 is located above the drive motor 31. The control board 32 is also equipped with a head bionic sensor module 102, which can be used as a front and rear balance weight. The head bionic sensor module 102 can be equipped with a transceiver antenna for transmitting and receiving control signals, or the antenna can be set in the control board 32. The control board 32 can be implemented using an STC8H1K08 chip, for example.

[0044] Since there are two drive motors 31, their weight accounts for a large proportion of the system's total weight. To reduce the impact of the dual drive motors' weight on the overall system weight, in this embodiment, the drive motor 31 is a hollow cup geared motor with a built-in planetary gear reducer. This reduces the design requirements for the reduction structure and lowers the weight proportion of the additional reducer. In a specific example, the selected drive motor weighs only 1.2 grams and has a total length of 22.25 mm, effectively reducing the overall weight of the aircraft.

[0045] To reduce the weight of the fixing structure from the flapping wing 101 to the wing fixing member 20, in this embodiment, the wing fixing member 20 is also provided with a flapping wing frame mounting hole 25. The flapping wing frame mounting hole 25 is provided by extending from the front end face, rear end face, and outer side face of the wing fixing member 20. Specifically, as shown in... Figure 7 As shown, the flapping wing frame mounting hole 25 is a straight hole. The frame of the flapping wing 101 can be made of carbon fiber, which is lightweight and has high structural strength. The frame is inserted into the flapping wing frame mounting hole 25 for fixation.

[0046] In a specific example, using the Queen Alexandra swallowtail butterfly as a biomimetic model, the total wingspan is 300mm, the single wingspan of the upper wing is 140.12mm, the total wing height is 190.63mm, the single wing area of ​​the upper wing is 8630.43mm², and the single wing area of ​​the lower wing is 8857.08mm². The diameter of the main carbon fiber skeleton directly fixed to the wing fixing component 20 in the two upper wings of flapping wing 101 is 0.7mm, and the diameter of the auxiliary carbon fiber skeleton fixed to the main carbon fiber skeleton can be selected as 0.3mm. The wings are made of 0.025mm PET (polyethylene terephthalate) film, and the wing surface is connected to the frame with glue. The carbon fiber frame of the two lower wings has a diameter of 0.6mm, and the wing surface is made of 0.01mm PE (polyethylene) film. Other parts of the body are made of PLA (polylactic acid) material and manufactured using 3D printing technology. The printing layer height is 0.2mm and the printing density is 10%, which can meet the strength requirements. The wing flapping angle can reach more than 80 degrees, and the total weight of the prototype can reach 8.9g.

[0047] The biomimetic butterfly-based aircraft provided by this utility model has two sets of drive motors and transmission mechanisms, which respectively control the flapping speed of the flapping wings fixed to the wing fixing parts, thereby achieving flight turning. There is no need to add matching structural parts for flapping wing deformation to the wing fixing parts, and the transmission mechanism has a larger design space and the structural strength is easier to ensure, thus effectively ensuring the reliability of the biomimetic butterfly-based aircraft.

[0048] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0049] The embodiments described above are merely illustrative of several specific implementations of this utility model, and while the descriptions are detailed, they should not be construed as limiting the scope of this utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A flight vehicle based on a biomimetic butterfly, characterized in that, include: The frame, wing fixtures, power module, and transmission mechanism, among which, The frame is a plate-shaped hollow structure and is set upright. The top of the frame is symmetrically provided with two first mounting holes and the bottom is symmetrically provided with two second mounting holes. Two wing fasteners are symmetrically arranged at both ends of the top of the frame. The main body of the wing fastener is a plate structure, and a first opening is provided on the inner side. A first rotating shaft parallel to the inner side is provided in the first opening. The wing fastener is embedded into the frame through the first opening. The first rotating shaft is rotatably connected to the first mounting hole. The wing fastener is fixedly connected to the flapping wing. The power module includes a control board and two drive motors. The two drive motors are respectively fixedly installed in the two second mounting holes and are respectively communicatively connected to the control board. The transmission mechanism is provided in two sets, which are respectively connected between the two drive motors and the two wing fixing parts.

2. The biomimetic butterfly-based aircraft according to claim 1, characterized in that, The wing fixing member also includes a downwardly extending hinge lug, the transmission mechanism includes a crank and a rocker arm, the middle part of the crank is fixedly connected to the output shaft of the drive motor, one end of the crank is hinged to one end of the rocker arm, and the other end of the rocker arm is hinged to the hinge lug.

3. The biomimetic butterfly-based aircraft according to claim 2, characterized in that, The drive motor is located at the front of the frame, and the transmission mechanism is located at the rear of the frame.

4. The biomimetic butterfly-based aircraft according to claim 3, characterized in that, The hinge ear is a single-ear structure, and the hinge ear is located behind the first opening. The rocker arm is located on the rear side of the hinge ear. The lower surface of the wing fixing member is also provided with a first slot, and the location of the first slot is consistent with the installation position of the rocker arm.

5. The biomimetic butterfly-based aircraft according to claim 4, characterized in that, The inner side of the wing fixing member is also provided with a second opening, the second opening is located at the same position as the first slot, and the first rotating shaft also passes through the second opening.

6. The biomimetic butterfly-based aircraft according to claim 3, characterized in that, The bottom of the frame also includes a bottom support frame extending downwards, and the bottom support frame is provided with a third mounting hole. A longitudinal beam extending to the rear of the frame is fixedly installed in the third mounting hole, and a power battery is installed on the longitudinal beam.

7. The biomimetic butterfly-based aircraft according to claim 6, characterized in that, The longitudinal beam is also equipped with a biomimetic abdominal structure.

8. The biomimetic butterfly-based aircraft according to claim 3, characterized in that, The control board is located above the drive motor, and a head-bionic sensor module is also provided on the control board.

9. The aircraft based on a biomimetic butterfly according to claim 1, characterized in that, The drive motor is a hollow cup geared motor with a built-in planetary gear reducer.

10. The aircraft based on a biomimetic butterfly according to claim 1, characterized in that, The wing fixing component is also provided with flapping wing frame assembly holes, which are extended from the front end face, rear end face and outer side face of the wing fixing component.

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