Butterfly-imitating ornithopter

Abstract

The utility model discloses a simulated butterfly ornithopter, including engine base, press spring buckle, connector seat and blade socket type battery, blade socket type battery includes battery body, blade pin and extension buckle, blade pin and extension buckle are oppositely arranged at battery body both ends, the bottom of engine base is equipped with the open slot that matches battery body, and the battery body is equipped with the blade pin and extension buckle. The pressing elastic buckle is arranged at the bottom of the machine base, the connector base is arranged on the inner wall of the side, away from the pressing elastic buckle, of the open groove, the connector base is provided with a limiting groove matched with the blade pin, when the battery body is installed in the open groove, the blade pin is embedded in the limiting groove, the pressing elastic buckle can fasten the extending buckle, and the blade socket type battery is fixedly connected with the machine base. According to the embodiment of the utility model, the blade pin and the extension buckle are arranged at the two ends of the battery body and are matched with the pressing elastic buckle and the connector base on the machine base to install the blade socket type battery, and the rapid installation can be completed only by aligning and embedding the blade pin into the limiting groove and pressing the elastic buckle to fasten the extension buckle.

Description

Technical Field

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

[0002] Ornithoptery, as a type of biomimetic aircraft, mimics the flight movements of natural creatures such as birds and insects, demonstrating enormous application potential. In particular, butterfly-inspired aircraft, due to their agile flight characteristics, are attracting increasing research attention in various fields such as aerospace, reconnaissance, and surveillance. Although some bird-inspired aircraft have successfully entered the market, the commercialization level of butterfly-inspired ornithoptery is currently very low. Butterfly-inspired aircraft remain primarily in the laboratory stage, mainly consisting of research prototypes or prototypes built by individual enthusiasts, and have not yet achieved large-scale commercial application.

[0003] In existing technologies, the design of butterfly-inspired flapping-wing aircraft primarily aims to improve flight performance. This is achieved through various structural designs and control methods to realize efficient wing flapping and flight stability. For example, some Chinese patents (such as CN112278267B and CN221024190U) propose using hinged connections to the rear wing surface to ensure better control of wing movement and thus improve flight performance. Furthermore, servo-driven designs are widely used, employing sophisticated mechanical structures to drive wing flapping, thereby mimicking the agility and efficiency of butterfly flight.

[0004] However, existing technologies still present numerous challenges in the design of butterfly-inspired aircraft, particularly in the disassembly and assembly of components. Many butterfly-inspired aircraft employ complex wing-to-fuselage connections, often using hinges, making wing removal difficult. Furthermore, the output shafts in the servo drive systems utilize spline connections with gaps at the mounting points, leading to inconvenience during disassembly and assembly. Improper installation can result in instability and compromised flight performance. More seriously, the common JST connector design for model aircraft batteries is not only inconvenient for plugging and unplugging, but also exposes wires and makes them susceptible to damage from the external environment. This results in poor fit between the fuselage and the battery, affecting the aircraft's aesthetics and lifespan. Summary of the Invention

[0005] This invention provides a butterfly-inspired flapping-wing aircraft to solve the technical problem of difficult disassembly and assembly of battery components in existing flapping-wing aircraft.

[0006] To address the aforementioned technical problems, this utility model provides a butterfly-inspired flapping-wing aircraft, comprising a base, a push-button latch, a connector seat, and a blade-type socket battery. The blade-type socket battery includes a battery body, blade leads, and an extension buckle. The blade leads and the extension buckle are disposed opposite each other at both ends of the battery body. The base has an opening slot at its bottom that mates with the battery body. The push-button latch is disposed at the bottom of the base. The connector seat is disposed on the inner wall of the opening slot away from the push-button latch, and the connector seat has a limiting groove that mates with the blade leads. When the battery body is installed in the opening slot, the blade leads are embedded in the limiting groove, and the push-button latch engages with the extension buckle, thereby fixing the blade-type socket battery to the base.

[0007] Furthermore, the blade socket-type battery also includes a battery casing with a receiving cavity inside. The battery body is disposed within the receiving cavity. The blade pin includes a first base with an installation notch and a plurality of first conductive plates equally spaced within the installation notch. The first base is disposed at the end of the battery casing, and the first conductive plates are electrically connected to the battery body.

[0008] Furthermore, the connector seat includes a second base disposed on the inner wall of the opening groove and a plurality of second conductive pieces disposed at equal intervals on the base, wherein the limiting groove is formed between each of the second conductive pieces, and the first conductive piece is used to insert into the limiting groove so that the connector seat is electrically connected to the blade socket type battery.

[0009] Furthermore, each pair of adjacent sidewalls of the first conductive sheet is provided with protrusions for clamping the second conductive sheet.

[0010] Furthermore, it also includes a housing with a mounting hole at the bottom and a cover installed in the mounting hole, and the housing has a mounting cavity communicating with the mounting hole. The base, the push-button snap, the connector seat and the blade socket battery are located in the mounting cavity. The top of the cover is provided with an elastic claw, which can extend into the mounting cavity and clamp the extension buckle so that the top of the cover abuts against the bottom of the push-button snap.

[0011] Furthermore, the elastic gripper includes two elastic members spaced apart on the top of the compartment cover and two buckles disposed opposite to the free ends of the two elastic members. When the two elastic members clamp the extension buckle, the two buckles will engage with the extension buckle.

[0012] Furthermore, a positioning element is provided at the bottom of the base, and a positioning hole is provided at the bottom of the housing that extends through to the mounting cavity, and the positioning element is inserted into the positioning hole.

[0013] Furthermore, it also includes two symmetrically arranged wings and two servo motors for driving the wings to flap. Two through holes extending into the mounting cavity are symmetrically arranged on the two side walls of the housing. The servo motors are symmetrically arranged on the two side walls of the base and electrically connected to the connector seat. The wings are connected to the servo motors through the through holes.

[0014] Furthermore, the wing includes a connector and a fixing member disposed on the connector. The connector has a square groove and a first fixing hole that penetrates both sides of the connector to the square groove. The servo is provided with an output square shaft that matches the square hole, and the output square shaft is provided with a second fixing hole corresponding to the first fixing hole. The fixing member can pass through the first fixing hole and the second fixing hole to fix the servo and the connector together.

[0015] Furthermore, the wing also includes a skin, multiple skeletons, and multiple supports. The multiple skeletons are respectively disposed on the connectors and the supports. The skin is disposed on the skeletons and connected to the connectors. The supports are spaced apart on the side edge of the skin away from the connectors.

[0016] Compared with the prior art, the beneficial effects of this embodiment of the butterfly flapping-wing aircraft are as follows:

[0017] This utility model embodiment designs a blade socket battery with blade pins and an extension buckle. The blade pins and extension buckle serve as the two ends of the battery body. Combined with the push-button latch and connector seat on the base, when installing the blade socket battery onto the butterfly-shaped flapping-wing aircraft, simply align the end of the battery body with the blade pins with the limiting groove on the connector seat, then push the battery body into the opening groove on the base. After the blade pins are embedded in the limiting groove, gently press the battery body, and the push-button latch will lock the extension buckle, thus fixing both ends of the battery body in place. This ensures a secure connection between the blade socket battery and the base, preventing the blade socket battery from loosening or falling off during flight, resulting in superior stability and durability for the aircraft. To remove the blade socket battery, simply press the push-button latch again to release the locking effect on the extension buckle, and pull it out in the original direction to remove the blade socket battery. This optimized structural design not only significantly simplifies the operation process of existing flapping-wing aircraft batteries and improves the efficiency of battery installation and removal, but also significantly enhances the convenience and safety of the aircraft, enabling users to quickly complete battery replacement operations and providing users with a more reliable and efficient operating experience.

[0018] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of this utility model, nor is it intended to limit the scope of this utility model. Other features of this utility model will become readily apparent from the following description. Attached Figure Description

[0019] The accompanying drawings are provided for a better understanding of this solution and do not constitute a limitation on this utility model. Wherein:

[0020] Figure 1 This is a schematic diagram of the butterfly-shaped flapping-wing aircraft provided in this embodiment of the present invention at one angle.

[0021] Figure 2 This is a schematic diagram of the butterfly-shaped flapping-wing aircraft provided in this embodiment of the present invention from another angle;

[0022] Figure 3 This is a schematic diagram of the blade socket-type battery mounted on the base in the butterfly flapping-wing aircraft provided by this utility model embodiment;

[0023] Figure 4 This is a structural schematic diagram of the base and connector seat at an angle in the butterfly flapping-wing aircraft provided in this embodiment of the present invention;

[0024] Figure 5 This is a structural schematic diagram of the base and connector seat of the butterfly-shaped flapping-wing aircraft provided in this embodiment of the present invention from another angle;

[0025] Figure 6 This is a schematic diagram of the push-button mechanism in the butterfly flapping-wing aircraft provided in this embodiment of the utility model;

[0026] Figure 7 This is a schematic diagram of the blade socket-type battery at one angle in the butterfly flapping-wing aircraft provided in this embodiment of the present invention;

[0027] Figure 8 This is a schematic diagram and a half-sectional view of the blade socket battery in the butterfly flapping-wing aircraft provided in this embodiment of the present invention from another angle.

[0028] Figure 9 This is a schematic diagram of the charger structure in the butterfly flapping-wing aircraft provided in this embodiment of the utility model;

[0029] Figure 10 This is a schematic diagram of the connector seat in the butterfly flapping-wing aircraft provided in this embodiment of the present invention;

[0030] Figure 11 This is a schematic diagram of the shell structure of the butterfly-shaped flapping-wing aircraft provided in this embodiment of the present invention;

[0031] Figure 12 This is a schematic diagram of the structure of half of the shell in the butterfly flapping-wing aircraft provided in this embodiment of the utility model;

[0032] Figure 13 This is a schematic diagram of the structure of the canopy cover of the butterfly-shaped flapping-wing aircraft provided in this embodiment of the utility model;

[0033] Figure 14 This is a schematic diagram of the structure of the wings of the butterfly-like flapping-wing aircraft provided in this embodiment of the utility model;

[0034] Figure 15 yes Figure 14 A magnified schematic diagram of the local structure at point A;

[0035] Figure 16 This is a schematic diagram of the connection structure of the connectors, frame and reinforcing members in the butterfly flapping-wing aircraft provided in this embodiment of the utility model;

[0036] Figure 17 This is a schematic diagram of the servo mechanism in the butterfly flapping-wing aircraft provided in this embodiment of the utility model.

[0037] In the diagram, 10 is the housing; 11 is the mounting hole; 12 is the mounting cavity; 13 is the positioning hole; 14 is the through hole; 20 is the base; 21 is the opening slot; 22 is the positioning element; 30 is the blade socket battery; 31 is the battery body; 32 is the blade pin; 321 is the first base; 322 is the first conductive sheet; 323 is the protrusion; 33 is the extension clip; 34 is the battery casing; 341 is the heat dissipation hole; 40 is the connector seat; 41 is the second base; 42 is the second conductive sheet; 421 is the limiting groove; 43 is the opening... 50. Stop switch; 60. Press-button spring latch; 61. Compartment cover; 61. Elastic gripper; 611. Elastic element; 612. Inverted latch; 70. Wing; 71. Connector; 711. Square groove; 712. First fixing hole; 72. Support element; 73. Skin; 74. Frame; 75. Reinforcing element; 80. Servo; 81. Output square shaft; 811. Second fixing hole; 90. Charger; 91. Charger housing; 911. Charging notch; 92. Push-button switch; 93. Indicator light; 94. Charging interface. Detailed Implementation

[0038] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings and embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.

[0039] In the description of this utility model, it should be noted that the directional terms such as "middle", "upper", "lower", "inner", and "outer" indicate the orientation and positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and 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. They should not be construed as limiting the specific protection scope of this utility model.

[0040] 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 technical features. Thus, the use of "first" and "second" to define a feature may explicitly or implicitly include one or more of that feature, and in this description of the utility model, "at least" means one or more, unless otherwise explicitly specified.

[0041] In this utility model, unless otherwise explicitly specified and limited, the terms "assembly," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can also refer to a mechanical connection; they can refer to a direct connection or a connection through an intermediate medium; or they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0042] like Figure 1-10 As shown, this utility model embodiment provides a butterfly flapping-wing aircraft, including a base 20, a push-button snap 50, a connector seat 40, and a blade socket-type battery 30. The blade socket-type battery 30 includes a battery body 31, blade pins 32, and an extension buckle 33. The blade pins 32 and the extension buckle 33 are disposed opposite each other at both ends of the battery body 31. The bottom of the base 20 has an opening groove 21 adapted to the battery body 31. The push-button snap 50 is disposed at the bottom of the base 20. The connector seat 40 is disposed on the inner wall of the opening groove 21 away from the push-button snap 50, and the connector seat 40 is provided with a limiting groove 421 adapted to the blade pins 32. When the battery body 31 is installed in the opening groove 21, the blade pins 32 are embedded in the limiting groove 421, and the push-button snap 50 will fasten the extension buckle 33 to fix the blade socket-type battery 30 to the base 20.

[0043] This embodiment of the invention designs a blade socket-type battery 30 with blade pins 32 and extension buckles 33. The blade pins 32 and extension buckles 33 serve as the two end interfaces of the battery body 31. In conjunction with the push-button snap 50 and connector seat 40 on the base 20, when the blade socket-type battery 30 needs to be installed on the butterfly-like flapping-wing aircraft, simply align the end of the battery body 31 with the blade pins 32 with the limiting groove 421 on the connector seat 40, and then push the battery body 31 into the opening groove 21 on the base 20, where the blade pins 32 are embedded. After inserting the battery into the limiting slot 421, gently press the battery body 31, and pressing the spring clip 50 will lock the extension clip 33, thus fixing both ends of the battery body 31 in place. This ensures a secure connection between the blade socket battery 30 and the base 20, preventing the blade socket battery 30 from loosening or falling off during flight of the butterfly-shaped flapping-wing aircraft. This results in superior stability and durability for the aircraft. To remove the blade socket battery 30, simply press the spring clip 50 again to release the locking effect of the extension clip 33, and pull it out in the original direction to remove the blade socket battery 30. This optimized structural design not only significantly simplifies the operation process of existing flapping-wing aircraft batteries and improves the efficiency of battery installation and removal, but also significantly enhances the convenience and safety of the aircraft, allowing users to quickly complete battery replacement operations and providing a more reliable and efficient operating experience.

[0044] The extension buckle 33 is a strip-shaped structure, firmly set at the end of the battery body 31. When the battery body 31 is installed in the opening slot 21, the extension buckle 33 acts as a locking tongue, extending out of the opening slot 21 and engaging with the press-fit snap 50 at the bottom of the base 20 for locking. The press-fit snap 50 serves as the locking mechanism for the extension buckle 33. To facilitate its installation and fixation, the bottom of the base 20 is usually provided with a locking hole for installing the press-fit snap 50. The press-fit snap 50 is usually provided with an elastic limiting element, made of a spring or an elastic material. The elastic limiting element can move accordingly when subjected to external force, allowing the extension buckle 33 to be locked or released to complete the unlocking action. Such as spring locks, press-return locks, sliding press locks, and rotary locks (with pressing function), etc., can all utilize the elastic element 611 to provide elasticity. When the extension buckle 33 is inserted, the spring pushes the locking tongue to lock. When pressed, the spring retracts and the locking tongue is released.

[0045] The blade pins 32 are typically flat or narrow metal pieces, facilitating insertion into the retaining grooves 421 within the connector socket 40. Their shape can be optimized based on the structure of the retaining groove 421, for example, by adding curvature or chamfering, to improve insertion smoothness and alignment accuracy. The blade pins 32 are typically made of a highly conductive metal material (such as copper or nickel-plated metal), enabling not only mechanical positioning and fixation, allowing the blade socket battery 30 to be easily and accurately inserted, but also electrical connection, ensuring power transfer between the blade socket battery 30 and other components. This satisfies the charging needs of the battery body 31 while providing stable power support to other components. The interior of the retaining groove 421 typically matches the shape of the blade pins 32, designed as a precise locking structure to accommodate the blade pins 32 and provide stable support. The retaining groove 421 restricts the movement of the blade pins 32, ensuring the battery does not wobble or misalign after installation. Its depth and width are designed to prevent the blade pins 32 from dislodging due to vibration or external force.

[0046] It should be noted that, to facilitate charging of the blade socket battery 30, an optional embodiment of this invention also provides a charger 90 for use with the blade socket battery 30. The charger 90 includes a charger housing with an internal mounting compartment and a lithium battery charging module disposed within the mounting compartment. The charger housing also has a charging notch 911 adapted to the blade socket battery 30, and a connector 40 is provided on the charging notch 911. The connector 40 is electrically connected to the lithium battery charging module. During charging, simply align the side of the blade socket battery 30 with the blade pins 32 with the connector 40, and then connect the lithium battery charging module to an external power source via the charging interface 94 on the charger housing. To better observe, monitor, and control the charging status of the blade socket battery 30, the charger housing also includes a matching push-button switch 92, indicator light 93, and display window. The application of these functional components falls within the scope of existing technology and will not be described in detail here.

[0047] like Figure 7 and Figure 8 As shown, in an optional embodiment of the present invention, the blade socket type battery 30 further includes a battery housing 34, a receiving cavity is formed in the battery housing 34, the battery body 31 is disposed in the receiving cavity, and the blade pin 32 includes a first base 321 with an installation notch and a plurality of first conductive pieces 322 disposed at equal intervals in the installation notch. The first base 321 is disposed at the end of the battery housing 34, and the first conductive pieces 322 are electrically connected to the battery body 31.

[0048] Specifically, by setting multiple first conductive pieces 322 within the mounting notch on the first base 321, the first conductive pieces 322 can be easily embedded into the limiting groove 421 on the connector seat 40, ensuring that the battery body 31 can be firmly fixed in the opening groove 21, preventing the battery from loosening or shifting during use. Furthermore, the parallel connection of multiple first conductive pieces 322 provides a more uniform current distribution, increases the contact surface, smooths the current flow path, reduces the current contact impedance, and reduces energy loss during charging and discharging, thereby improving the overall charging and discharging efficiency of the battery.

[0049] In this design, multiple first conductive sheets 322 share the task of current transmission, preventing current from concentrating excessively on any single conductive sheet and reducing current imbalance during current flow. Lower contact resistance means the battery can charge and discharge more efficiently, minimizing energy loss. This not only improves the battery's charging and discharging efficiency but also reduces heat generation and energy loss caused by excessive contact resistance.

[0050] It should be noted that, in order to ensure that the butterfly-shaped flapping-wing aircraft is lightweight while maintaining good performance, the optional embodiment of this utility model adopts a structure with multiple heat dissipation holes 341 on the side walls of the battery casing 34 and the base 20. This not only effectively removes unnecessary materials, thereby reducing the overall weight of the battery and the aircraft, but also helps to promote the rapid release of heat inside the aircraft, increase the heat exchange area, improve the heat dissipation effect, prevent the battery from overheating, and avoid battery performance degradation or damage due to excessive temperature.

[0051] like Figure 4-10 As shown, in an optional embodiment of the present invention, the connector seat 40 includes a second base 41 disposed on the inner wall of the opening groove 21 and a plurality of second conductive sheets 42 disposed at equal intervals on the base. A limiting groove 421 is formed between each second conductive sheet 42. A first conductive sheet 322 is inserted into the limiting groove 421 so that the connector seat 40 is electrically connected to the blade socket type battery 30.

[0052] Specifically, through the design of a limiting groove 421 formed between multiple second conductive pieces 42 on the second base 41, when the blade socket battery 30 is connected to the connector seat 40, the first conductive piece 322 can be precisely embedded in the limiting groove 421 formed between the second conductive pieces 42 on the connector seat 40. The limiting groove 421 can not only effectively mechanically position the first conductive piece 322, but also prevent the battery from becoming loose or misaligned during use. The cooperation between the first conductive piece 322 and the limiting groove 421 plays a dual role: it ensures that the battery body 31 is fixed in the connector seat 40, and it prevents poor contact or misconnection between the battery and the connector, thus enhancing the stability and reliability of the device. It should be noted that, in order to ensure the safety of the blade socket battery 30 and the stability of current transmission, the first base 321 and the second base 41 are usually made of insulating material. The insulating material can effectively prevent short circuits during battery installation and use, and ensure electrical isolation between the battery and the connector seat 40, thereby ensuring the safety of battery use. In addition, the insulating base can reduce current leakage or loss, and improve the overall energy efficiency of the system.

[0053] like Figure 8 As shown, in an optional embodiment of the present invention, protrusions 323 are provided on each pair of adjacent sidewalls of the first conductive sheet 322 for clamping the second conductive sheet 42.

[0054] Specifically, by providing protrusions 323 on the adjacent sidewalls of the first conductive sheet 322, the second conductive sheet 42 can be effectively clamped between the first conductive sheets 322, thereby making the contact connection between the first conductive sheet 322 and the second conductive sheet 42 tighter. This tight contact not only reduces the gap between the contact surfaces but also enhances the current transmission efficiency between them, preventing the second conductive sheet 42 from shifting or loosening during use. With tighter contact, the current flows more smoothly between the conductive sheets, reducing the increase in resistance caused by poor contact or gaps, and further optimizing the charging and discharging performance of the battery.

[0055] It should be noted that the protrusion 323 can typically be made of the same conductive metal material (such as copper or nickel-plated material) as the first conductive sheet 322 and the second conductive sheet 42. This material selection ensures the consistency and reliability of conductivity, thereby optimizing the electrical connection performance of the first conductive sheet 322, the second conductive sheet 42, and the protrusion 323, and further improving the charging efficiency and discharging stability of the battery.

[0056] like Figure 11 , Figure 12 and Figure 13As shown, in an optional embodiment of this utility model, it further includes a housing 10 with a mounting hole 11 at the bottom and a compartment cover 60 installed in the mounting hole 11. The housing 10 has a mounting cavity 12 communicating with the mounting hole 11. The base 20, the push-button snap 50, the connector seat 40 and the blade socket battery 30 are located in the mounting cavity 12. The top of the compartment cover 60 is provided with an elastic claw 61. The elastic claw 61 can extend into the mounting cavity 12 and clamp the extension buckle 33 so that the top of the compartment cover 60 abuts against the bottom of the push-button snap 50.

[0057] Specifically, through the cooperative design of the snap-on latch 50 and the compartment cover 60, by pressing the compartment cover 60, which abuts against the bottom of the snap-on latch 50, the user can easily lock or release the extension buckle 33, simplifying the fixing and disassembly process of the blade socket battery 30. Simultaneously, the elastic claw 61 located at the top of the compartment cover 60 assists by extending into the mounting cavity 12 and clamping the extension buckle 33, allowing the loose blade socket battery 30 to be pulled out and easily removed. This design further improves the convenience of the disassembly process, avoiding inconvenience caused by the battery being stuck or difficult to operate.

[0058] The cooperation between the housing 10 and the cover 60 not only secures and protects the blade socket battery 30, but also provides external protection for other components of the aircraft. During flight, the aircraft will face external forces such as vibration and impact. The tight fit between the housing 10 and the cover 60 can effectively prevent these external forces from damaging the internal battery and its components, thereby improving the overall reliability and safety of the equipment.

[0059] Furthermore, to facilitate the manufacturing and disassembly of the housing 10, it can be made in a symmetrical manner, consisting of two halves. This design not only simplifies the manufacturing process but also improves production efficiency. The symmetrical structure allows for standardized production of all parts, reducing the complexity of molds and processing, and lowering production costs. In addition, the symmetrical design of the two halves of the housing 10 makes installation and disassembly more convenient during assembly and disassembly, facilitating rapid assembly and maintenance, and enhancing the user experience.

[0060] like Figure 13 As shown, in an optional embodiment of the present invention, the elastic gripper 61 includes two elastic members 611 spaced apart on the top of the cover 60 and two buckles 612 disposed opposite to the free ends of the two elastic members 611. When the two elastic members 611 clamp the extension buckle 33, the two buckles 612 will engage with the extension buckle 33.

[0061] Specifically, through the interlocking structure of the two inverted buckles 612 and the extension buckle 33, the elastic gripper 61 can provide a more stable clamping force. During battery removal, even when a large pulling force is applied, the extension buckle 33 is not prone to slipping off the elastic gripper 61, thus ensuring that the extension buckle 33 remains firmly connected during removal. This design effectively avoids removal difficulties caused by the extension buckle 33 slipping or loosening, improving the stability and reliability of the removal process. In addition, the interlocking action of the two inverted buckles 612 and the extension buckle 33 allows the cover 60 to be more firmly fixed to the mounting hole 11 at the bottom of the housing 10, effectively avoiding the risk of the cover 60 falling off or loosening during use, thereby protecting the internal components of the aircraft, ensuring the normal operation of the aircraft, and preventing equipment failure or battery loosening due to the cover 60 loosening.

[0062] It should be noted that the design of the inverted buckle 612 provides a precise locking point, while the elastic deformation of the elastic element 611 provides a wider range of fit and adaptability. When the free end of the elastic element 611 contacts the extension buckle 33, the inverted buckle 612 can quickly and firmly engage with the edge of the extension buckle 33. The elastic element 611 needs to possess a certain degree of elasticity and durability; therefore, materials with good elastic recovery capabilities are usually chosen, such as spring steel, polyurethane, silicone, or nylon. These materials not only possess good elasticity but also ensure that they are not easily deformed or lose elasticity after prolonged use, adapting to frequent loading and unloading operations.

[0063] like Figure 11 , Figure 12 As shown, in an optional embodiment of the present invention, a positioning member 22 is also provided at the bottom of the base 20, and a positioning hole 13 is provided at the bottom of the housing 10, extending through to the mounting cavity 12, and the positioning member 22 is inserted into the positioning hole 13.

[0064] Specifically, by setting a positioning element 22 at the bottom of the base 20, in conjunction with the positioning hole 13 at the bottom of the mounting cavity 12, the operation process is simplified. The user only needs to align the base 20 with the positioning hole 13 and then insert the positioning element 22 into the hole to quickly complete the fixing, making the installation process much simpler. Similarly, during disassembly, the positioning element 22 makes it easy for the user to easily identify and remove it, avoiding the hassle of complicated operations. At the same time, the positioning element 22 provides additional fixing, ensuring that the base 20 will not shift or loosen due to vibration or external forces during use. This not only improves the stability of the base 20 but also reduces potential malfunctions or safety hazards caused by a loose base 20.

[0065] like Figure 14-17As shown, in an optional embodiment of this utility model, it further includes two symmetrically arranged wings 70 and two servo motors 80 for driving the wings 70 to flap. Two through holes 14 extending to the mounting cavity 12 are symmetrically arranged on both sides of the housing 10. The servo motors 80 are symmetrically arranged on both sides of the base 20 and electrically connected to the connector seat 40. The wings 70 are connected to the servo motors 80 through the through holes 14.

[0066] Specifically, the symmetrical layout of the wings 70 and servos 80 allows the aircraft to maintain better balance and stability during flight, ensuring balanced flapping force of the wings 70 and avoiding yaw or slight tilting caused by asymmetry, thus improving the overall handling performance of the aircraft. By using two servos 80 to drive the flapping of the wings 70, adjustments can be made according to the aircraft's flight requirements, enabling more precise control of the wings 70, providing efficient power output, and ensuring that the vibration amplitude and frequency of the wings 70 match the aircraft's needs, further improving flight performance. The electrical connection between the servos 80 and the connector 40 ensures effective current transmission, thereby stably driving the servos 80. Optimized electrical connections ensure that the servos 80 can efficiently drive the wings 70, guaranteeing energy requirements during takeoff, flight, and landing.

[0067] Meanwhile, to better control the flight of the butterfly-inspired flapping-wing aircraft, the system is also equipped with a flight control board that integrates wireless communication capabilities. This flight control board can connect to a receiver and be operated via a remote controller. This design enables precise remote control of the aircraft during flight, improving its flexibility and responsiveness, and further optimizing the flight experience. Additionally, to ensure that the butterfly-inspired flapping-wing aircraft can be powered off directly upon impact to prevent unnecessary damage from flapping on the ground, a start / stop switch 43 connected to the flight control board can be installed at the bottom of the shell 10. This switch automatically cuts off power upon contact with the ground upon impact, or it can be used by the user to control the operation and shutdown of the servo motor 80.

[0068] It should be noted that the servo motor 80 is an electrically driven device with automatic adjustment function, widely used in aircraft, robots, drones, and other fields. The servo motor 80 can precisely control angle, position, and speed according to control signals, and is typically used to drive a component in a control system to perform precise movements. However, the output shaft of a traditional servo motor 80 usually uses a splined shaft for connection. Due to the precision required of splined shafts, improper handling during disassembly and assembly (such as using hammers or heating) can easily damage the spline teeth, potentially leading to spline tooth breakage, cracks, or other problems. Therefore, the use of splined shafts makes the disassembly and assembly of the wing 70 difficult and inefficient.

[0069] like Figure 14-17As shown, in an optional embodiment of this utility model, the wing 70 includes a connector 71 and a fixing member disposed on the connector 71. The connector 71 has a square groove 711 and a first fixing hole 712 that penetrates the two side walls of the connector 71 to the square groove 711. The servo motor 80 is provided with an output square shaft 81 that matches the square hole, and the output square shaft 81 is provided with a second fixing hole 811 that corresponds to the first fixing hole 712. The fixing member can pass through the first fixing hole 712 and the second fixing hole 811 to fix the servo motor 80 and the connector 71 together.

[0070] Specifically, by cooperating with the square shaft 81 and the square slot 711, when the servo motor 80 and the connector 71 are connected, it is only necessary to insert the square shaft 81 into the square slot 711 and then insert the fixing member into the first fixing hole 712 and the second fixing hole 811 for fixed connection. This assembly process does not require complicated alignment or alignment operations, and can complete the stable connection and fixation of the servo motor 80 and the connector 71, which significantly improves the assembly efficiency. This ensures that the wing 70 can withstand the vibration and load when driven by the servo motor 80 during flight, and improves the stability and reliability of the structure.

[0071] The reinforced design of the fasteners ensures a stable connection between the wings 70 and the servo motor 80. When the servo motor 80 drives the wings 70 to flap, it effectively withstands the resulting vibrations and loads, further enhancing the stability and safety of the aircraft during flight. The selection of fasteners depends on the specific application scenario and structural requirements of the butterfly-inspired flapping-wing aircraft, taking into account material performance, ease of installation, and connection strength. Suitable fasteners include screws, bolts, pins, or snap-fit ​​connectors 71. Disassembly is quick and easy; simply removing the fasteners allows the output square shaft 81 to be pulled out of the square slot 711.

[0072] like Figure 15 and Figure 16 As shown, in an optional embodiment of the present invention, the wing 70 further includes a skin 73, a plurality of skeletons 74 and a plurality of support members 72. The plurality of skeletons 74 are respectively disposed on the connectors 71 and the support members 72. The skin 73 is disposed on the skeletons 74 and connected to the connectors 71. The support members 72 are spaced apart on the side edge of the skin 73 away from the connectors 71.

[0073] Specifically, the support of multiple frames 74 effectively distributes external forces, preventing the skin 73 from deforming or being damaged during flight due to airflow or external forces, thereby improving the stability and durability of the wings 70. The support members 72 are rationally arranged on the side edges of the skin 73 away from the connector 71, with multiple frames 74 forming a cross structure. This creates effective mechanical support between the frames 74, enhancing the rigidity of the wings 70 and ensuring efficient and reliable flight of the aircraft. This design simplifies the overall structure by rationally integrating the skin 73, frames 74, and support members 72, making the assembly of the wings 70 more convenient and faster, and facilitating later maintenance and replacement. This design optimizes the structural strength, aerodynamic performance, and load-bearing capacity of the wings 70, making the butterfly-inspired flapping-wing aircraft more stable and efficient in flight, while reducing weight and improving the aircraft's performance and durability.

[0074] Meanwhile, to further enhance the connection rigidity between the connector 71 and the frame 74, a reinforcing member 75 is designed to cover the connection point. This reinforcing member 75 not only effectively protects the frame 74, reducing damage caused by external impacts or collisions, but also optimizes the structure of the connector 71, improving its overall impact resistance. This design effectively reduces the risk of damage to the wing 70 during flight, extending its service life. The reinforcing member 75 can be made primarily of a lightweight, rigid material, featuring low weight and high strength, ensuring sufficient support without adding extra load. This design not only improves the overall structural stability of the wing 70 but also reduces the manufacturing difficulty of the connector 71 and the frame 74, making the manufacturing process simpler and more efficient, and reducing production costs.

[0075] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this utility model. It should be understood that the above descriptions are merely specific embodiments of this utility model and are not intended to limit the scope of protection of this utility model. In particular, it should be noted that any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model by those skilled in the art should be included within the scope of protection of this utility model.

Claims

1. A butterfly flapping winged aircraft, characterized by, The device includes a base, a push-button latch, a connector socket, and a blade socket-type battery. The blade socket-type battery includes a battery body, blade leads, and an extension clip. The blade leads and the extension clip are disposed opposite each other at both ends of the battery body. The bottom of the base has an opening slot adapted to the battery body. The push-button latch is disposed at the bottom of the base. The connector socket is disposed on the inner wall of the opening slot away from the push-button latch, and the connector socket has a limiting groove adapted to the blade leads. When the battery body is installed in the opening slot, the blade leads are embedded in the limiting groove, and the push-button latch will lock the extension clip, so that the blade socket-type battery is fixedly connected to the base.

2. The butterfly flapping aircraft according to claim 1, wherein, The blade socket-type battery also includes a battery casing with a receiving cavity inside. The battery body is disposed in the receiving cavity. The blade pin includes a first base with an installation notch and a plurality of first conductive plates equally spaced within the installation notch. The first base is disposed at the end of the battery casing, and the first conductive plates are electrically connected to the battery body.

3. The butterfly flapping aircraft according to claim 2, wherein, The connector seat includes a second base disposed on the inner wall of the opening groove and a plurality of second conductive plates disposed at equal intervals on the base. The limiting groove is formed between each of the second conductive plates. The first conductive plate is used to insert into the limiting groove so that the connector seat is electrically connected to the blade socket type battery.

4. The butterfly flapping aircraft according to claim 3, wherein, The first conductive sheet has protrusions on each pair of adjacent sidewalls for clamping the second conductive sheet.

5. The butterfly flapping aircraft according to claim 1, wherein, It also includes a housing with a mounting hole at the bottom and a cover installed in the mounting hole. The housing has a mounting cavity communicating with the mounting hole. The base, the push-button snap, the connector seat and the blade socket battery are located in the mounting cavity. The top of the cover is provided with an elastic claw. The elastic claw can extend into the mounting cavity and clamp the extension buckle so that the top of the cover abuts against the bottom of the push-button snap.

6. The butterfly flapping aircraft according to claim 5, wherein, The elastic gripper includes two elastic elements spaced apart on the top of the compartment cover and two buckles positioned opposite each other at the free ends of the two elastic elements. When the two elastic elements clamp the extension buckle, the two buckles engage with the extension buckle.

7. The butterfly flapping aircraft according to claim 5, wherein, The bottom of the base is also provided with a positioning component, and the bottom of the housing is provided with a positioning hole that extends through to the mounting cavity, and the positioning component is inserted into the positioning hole.

8. The butterfly flapping aircraft according to claim 5, wherein, It also includes two symmetrically arranged wings and two servo motors for driving the wings to flap. Two through holes extending into the mounting cavity are symmetrically arranged on the two side walls of the housing. The servo motors are symmetrically arranged on the two side walls of the base and electrically connected to the connector seat. The wings are connected to the servo motors through the through holes.

9. The butterfly flapping aircraft according to claim 8, wherein, The wing includes a connecting piece and a fixing piece arranged on the connecting piece, a square slot and a first fixing hole penetrating through two side walls of the connecting piece to the square slot are arranged on the connecting piece, an output square shaft matched with the square hole is arranged on the steering engine, and a second fixing hole corresponding to the first fixing hole is arranged on the output square shaft, the fixing piece can be penetrated into the first fixing hole and the second fixing hole to fixedly connect the steering engine and the connecting piece.

10. The butterfly flapping aircraft according to claim 9, wherein, The wing further includes a skin, a plurality of skeletons and a plurality of supporting pieces, the plurality of skeletons are respectively arranged on the connecting piece and the supporting pieces, the skin is arranged on the skeletons and connected with the connecting piece, and the supporting pieces are arranged at intervals on the side edge of the skin away from the connecting piece.

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