Bionic aircraft flank

Abstract

The utility model discloses a bionic aircraft side wing, and belongs to the technical field of bionic equipment. The aircraft mainly comprises an aircraft framework and side wing parts arranged on the two sides of the aircraft framework, a fixing frame and a driving component installed on the fixing frame and used for driving the side wing parts to move are arranged at the front end of the aircraft framework, a battery pack and a microcontroller are arranged on the aircraft framework, and each side wing part comprises a front wing, a rear wing and a connecting block. The bionic aircraft side wing is composed of the front wing body, the rear wing body and the connecting block, the front wing body and the rear wing body are connected through the connecting block and provided with the outer contour frames and the wing faces, and the cross structures are arranged in the outer contour frames, so that the rigidity, stability and overall strength of the side wing can be effectively enhanced, and the excellent performance of an aircraft in high-speed flight or complex airflow is guaranteed; meanwhile, the airfoil is made of a thin film material with high tensile strength and elasticity, so that the structural weight is reduced, the aerodynamic performance is optimized, and the efficiency and reliability of the aircraft are improved.

Description

Technical Field

[0001] This application relates to the field of biomimetic equipment technology, specifically a biomimetic aircraft wing. Background Technology

[0002] Bionic aircraft are aircraft developed by imitating the flight principles and structural designs of living organisms in nature. Their design inspiration comes from the flight patterns of birds, insects, bats, and other creatures, aiming to improve the performance, efficiency, and adaptability of aircraft. The "wings" in bionic aircraft refer to the flight surfaces on both sides of the aircraft's fuselage, typically used to provide lift and stability. The design inspiration for bionic aircraft comes from living organisms in nature, and butterflies, as insects with unique flight capabilities, have become an important reference in bionic aircraft design.

[0003] Although the biomimetic design of butterfly wings brings significant advantages in maneuverability and aerodynamic performance to the flanks of aircraft, the structural strength and weight of biomimetic aircraft flanks remain a major challenge in practical applications. The lightness and flexibility of butterfly wings are key to their efficient flight, but this design places high demands on the structural strength of the aircraft, especially under conditions of large external forces or complex airflow. The flanks need to ensure sufficient rigidity and durability. Therefore, the structural strength of current biomimetic aircraft flanks still needs to be improved while ensuring lightweight design.

[0004] Therefore, it is necessary to provide a biomimetic aircraft wing to solve the above problems.

[0005] It should be noted that the information disclosed in this background section is only for understanding the background technology of this application concept, and therefore may include information that does not constitute prior art. Summary of the Invention

[0006] Based on the aforementioned problems in the existing technology, the problem to be solved by this application is to provide a biomimetic aircraft wing that achieves the effects of lightweighting and improving the overall structural strength.

[0007] The technical solution adopted by this application to solve its technical problem is: a biomimetic aircraft side wing, including an aircraft frame and side wing portions provided on both sides thereon, a fixed frame provided at the front end of the aircraft frame and a drive component mounted on the fixed frame for driving the side wing portions to move, a battery pack and a microcontroller provided on the aircraft frame, and the side wing portions including a forewing, a rearwing and a connecting block, the connecting block being used to connect the forewing and the rearwing;

[0008] The forewing includes a first outer contour frame and a wing surface laid on the first outer contour frame. The first outer contour frame is provided with a first main drive rod and a second main drive rod inside, and one end of the first main drive rod and the second main drive rod are both connected to a connecting block. The first outer contour frame is also provided with a first support rod and a second support rod that are cross-connected to the first main drive rod and the second main drive rod.

[0009] The rear wing includes a second outer contour frame and a wing surface laid on the second outer contour frame, and the interior of the second outer contour frame is provided with a diagonal rod.

[0010] Furthermore, the length of the first main drive rod is greater than that of the second main drive rod, and the first main drive rod is cross-connected with the first support rod and the second support rod respectively. The first support rod is located at the outer part of the middle of the first outer contour frame, and one end of the second main drive rod is connected to the second support rod, and the second support rod is located at the middle part of the first outer contour frame.

[0011] Furthermore, a triangular structure is formed between the first main drive rod, the second main drive rod, and the second support rod.

[0012] Furthermore, one end of the diagonal rod is connected to the connecting block, and the other end is connected to the middle position of the edge of the second outer contour frame.

[0013] Furthermore, the wing surface located on the first outer contour frame is connected to the first main drive rod, the second main drive rod, the first support rod, and the second support rod by adhesive bonding.

[0014] Furthermore, the wing surface located on the second outer contour frame is connected to the diagonal rod by adhesive.

[0015] Furthermore, the wing surface is a thin film made of polyurethane material.

[0016] Furthermore, a gap is formed between the forewing and the hindwing.

[0017] The beneficial effects of this application are as follows: The biomimetic aircraft side wing provided by this application consists of a forewing, a rearwing, and a connecting block. The forewing and rearwing are connected by the connecting block. Both the forewing and rearwing are equipped with an outer contour frame and a wing surface. The wing surface is designed with a cross structure, including a first main drive rod, a second main drive rod, a first support rod, a second support rod, and a diagonal rod. This not only effectively ensures the rigidity and stability of the side wing but also enhances the overall strength of the structure, enabling the aircraft to maintain excellent performance in high-speed flight or complex airflow environments. At the same time, the wing surface is made of a thin film material, which has high tensile strength and elasticity, effectively reducing the overall weight of the structure and providing excellent aerodynamic performance. While ensuring the rigidity and stability of the side wing, a lightweight design is achieved, optimizing the aerodynamic performance and structural strength of the aircraft, and significantly improving the flight efficiency and reliability of the aircraft.

[0018] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings:

[0020] Figure 1 This is an overall schematic diagram of the application;

[0021] Figure 2 for Figure 1 Top view;

[0022] Figure 3 This is a schematic diagram of the side wing structure of this application;

[0023] Figure 4 This is a schematic diagram of the forewing and hindwing structure of this application;

[0024] The following are the labeling elements in the figure:

[0025] 1. Aircraft frame; 2. Mounting frame; 3. Side wings; 31. Forewing; 311. First outer contour frame; 312. First main drive rod; 313. Second main drive rod; 314. First support rod; 315. Second support rod; 316. Triangular structure; 32. Rear wing; 321. Second outer contour frame; 322. Diagonal rod; 33. Connecting block; 34. Wing surface; 35. Gap; 4. Drive components; 5. Battery pack; 6. Microcontroller. Detailed Implementation

[0026] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0028] like Figures 1 to 4 As shown, this application provides a biomimetic aircraft side wing, including an aircraft frame 1 and side wing portions 3 on both sides thereon. The front end of the aircraft frame 1 is provided with a fixed frame 2 and a drive component 4 mounted on the fixed frame 2 for driving the side wing portions 3 to move. The aircraft frame 1 is provided with a battery pack 5 and a microcontroller 6. The side wing portion 3 includes a fore wing 31, a rear wing 32 and a connecting block 33. The connecting block 33 is used to connect the fore wing 31 and the rear wing 32.

[0029] The forewing 31 includes a first outer contour frame 311 and a wing surface 34 laid on the first outer contour frame 311. The first outer contour frame 311 is provided with a first main drive rod 312 and a second main drive rod 313, and one end of the first main drive rod 312 and the second main drive rod 313 are connected to the connecting block 33. The first outer contour frame 311 is also provided with a first support rod 314 and a second support rod 315 that are cross-connected with the first main drive rod 312 and the second main drive rod 313.

[0030] The rear wing 32 includes a second outer contour frame 321 and a wing surface 34 laid on the second outer contour frame 321. The interior of the second outer contour frame 321 is provided with a diagonal rod 322.

[0031] In this embodiment, the aircraft frame 1 provides support, and the mounting bracket 2 is installed at the front end of the frame to fix the drive component 4. The drive component 4 is responsible for controlling the movement of the side wing 3 through the microcontroller 6. The microcontroller 6 controls the movement of the side wing 3 according to the flight status of the aircraft to adapt to different flight environments and requirements. The side wing 3 consists of a forewing 31, a rear wing 32, and a connecting block 33. The forewing 31 and the rear wing 32 are connected by the connecting block 33. The forewing 31 and the rear wing 32 are respectively equipped with a first outer contour frame 311 and a second outer contour frame 321 and a wing surface 34, and the internal structure is arranged with a first main drive rod 312, a second main drive rod 313, a first support rod 314, a second support rod 315, and a diagonal rod 322. These designs ensure the rigidity and stability of the structure while minimizing unnecessary weight. The first main drive rod 312 and the second main drive rod 313 inside the forewing 31 achieve motion control through connection with the connecting block 33. The first support rod 314 and the second support rod 315 provide necessary structural support to ensure uniform force distribution of the forewing 31 and prevent deformation or damage due to external forces. The rear wing 32 enhances the overall structural strength through the diagonal rod 322, ensuring that the side wing 3 can withstand greater wind pressure and airflow pressure during flight while maintaining high stability.

[0032] like Figure 3 As shown, the length of the first main drive rod 312 is greater than that of the second main drive rod 313, and the first main drive rod 312 is cross-connected with the first support rod 314 and the second support rod 315 respectively. The first support rod 314 is located at the outer part of the middle of the first outer contour frame 311, and one end of the second main drive rod 313 is connected to the second support rod 315, and the second support rod 315 is located at the middle part of the first outer contour frame 311.

[0033] In this embodiment, the difference in length between the first main drive rod 312 and the second main drive rod 313 helps optimize the motion control and external force resistance of the side wing. The first main drive rod 312 is cross-connected with the first support rod 314 and the second support rod 315, making the structure more mechanically stable. Through the cross-connection, it can be ensured that when the aircraft is subjected to lateral forces, the motion of the side wing 3 is not easily affected by external airflow or wind pressure, avoiding excessive deformation. The first support rod 314 is located in the outer part of the middle of the first outer contour frame 311. This arrangement helps to better distribute the load when the side wing is subjected to forces. The outer position allows the first support rod 314 to effectively support a wider range of force transmission, preventing side wing deformation or damage caused by mechanical imbalance. The end of the second main drive rod 313 is connected to the second support rod 315, and the second support rod 315 is located in the middle of the first outer contour frame 311. This design allows the second main drive rod 313 to provide stable mechanical support through the second support rod 315, avoiding excessive warping or deformation during flight. Furthermore, because the second support rod 315 is located in the middle, the aircraft's flanks can effectively distribute force through this central support when subjected to airflow or external forces, thereby preventing imbalance and maintaining the aircraft's stability. This cross-connection method also enhances rigidity, prevents vertical or lateral misalignment between support rods, and improves the overall durability of the structure.

[0034] like Figure 3 As shown, a triangular structure 316 is formed between the first main drive rod 312, the second main drive rod 313, and the second support rod 315.

[0035] In this embodiment, the first main drive rod 312, the second main drive rod 313 and the second support rod 315 are combined to form a triangular structure 316, which can disperse and evenly transmit force when the aircraft is subjected to external forces such as airflow and crosswinds, avoid force concentration and reduce the risk of structural deformation, and ensure that the side wing 3 is more stable during flight, which can effectively improve the stability of the overall structure.

[0036] like Figure 3 As shown, one end of the diagonal rod 322 is connected to the connecting block 33, and the other end is connected to the middle position of the edge of the second outer contour frame 321.

[0037] In this embodiment, the positioning of the diagonal rod 322 at the center of the edge of the second outer contour frame 321 ensures that the force is more evenly distributed across the entire frame. Especially when subjected to external force, it can effectively transfer the pressure to other support components, thus avoiding excessive local force or stress concentration and improving the rigidity of the overall structure.

[0038] like Figure 3As shown, the wing surface 34 located on the first outer contour frame 311 is connected to the first main drive rod 312, the second main drive rod 313, the first support rod 314 and the second support rod 315 by adhesive bonding.

[0039] The wing surface 34 located on the second outer contour frame 321 is connected to the diagonal rod 322 by adhesive.

[0040] In this embodiment, by bonding the wing surface 34 to the first main drive rod 312, the second main drive rod 313, the first support rod 314, the second support rod 315 on the first outer contour frame 311 and the diagonal rod 322 on the second outer contour frame 321, an efficient, stable and lightweight design of the connecting components is achieved. This bonding connection technology can not only improve the mechanical properties, sealing performance and vibration resistance of the structure, but also optimize the production process, reduce costs and improve the overall aerodynamic characteristics.

[0041] like Figure 3 As shown, wing surface 34 is a thin film made of polyurethane material.

[0042] In this embodiment, using a thin film made of polyurethane as the wing surface 34 can make it lighter and more durable while also being wear-resistant.

[0043] like Figure 4 As shown, a gap 35 is formed between the forewing 31 and the hindwing 32.

[0044] In this embodiment, the design of the gap 35 helps to divert airflow and reduce the pressure difference between the surfaces of the forewing 31 and the hindwing 32, thereby effectively reducing the drag caused by the pressure difference. In addition, the gap 35 can also help to disperse the structural stress caused by the airflow impact, thereby reducing the structural fatigue damage of the side wing 3.

[0045] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A biomimetic aircraft side wing, comprising an aircraft frame and side wing portions disposed on both sides thereof, wherein a fixed frame is provided at the front end of the aircraft frame and a drive component mounted on the fixed frame for driving the movement of the side wing portions, and a battery pack and a microcontroller are provided on the aircraft frame, characterized in that, The side wing includes a forewing, a hindwing, and a connecting block, the connecting block being used to connect the forewing and the hindwing; The forewing includes a first outer contour frame and a wing surface laid on the first outer contour frame. The first outer contour frame is provided with a first main drive rod and a second main drive rod inside, and one end of the first main drive rod and the second main drive rod are both connected to a connecting block. The first outer contour frame is also provided with a first support rod and a second support rod that are cross-connected to the first main drive rod and the second main drive rod. The rear wing includes a second outer contour frame and a wing surface laid on the second outer contour frame, and the interior of the second outer contour frame is provided with a diagonal rod.

2. The biomimetic aircraft wing according to claim 1, characterized in that: The length of the first main drive rod is greater than that of the second main drive rod, and the first main drive rod is cross-connected with the first support rod and the second support rod respectively. The first support rod is located at the outer part of the middle of the first outer contour frame. One end of the second main drive rod is connected to the second support rod, and the second support rod is located at the middle part of the first outer contour frame.

3. The biomimetic aircraft wing according to claim 2, characterized in that: A triangular structure is formed between the first main drive rod, the second main drive rod, and the second support rod.

4. The biomimetic aircraft wing according to claim 3, characterized in that: One end of the diagonal rod is connected to the connecting block, and the other end is connected to the middle position of the edge of the second outer contour frame.

5. The biomimetic aircraft wing according to claim 4, characterized in that: The wing surface located on the first outer contour frame is connected to the first main drive rod, the second main drive rod, the first support rod, and the second support rod by adhesive bonding.

6. The biomimetic aircraft wing according to claim 5, characterized in that: The wing surface located on the second outer contour frame is connected to the diagonal rod by adhesive.

7. A biomimetic aircraft wing according to claim 6, characterized in that: The wing surface is a thin film made of polyurethane.

8. The biomimetic aircraft wing according to claim 7, characterized in that: A gap is formed between the forewing and hindwing.

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