A flapping-wing aircraft

Abstract

This invention discloses a flapping-wing aircraft, relating to the field of aircraft technology. It includes at least two wing bodies and a transmission mechanism that drives their flapping. The wing bodies can dynamically adjust drag. The wing bodies are either mesh-structured or unidirectional valve-structured: the former includes a lightweight mesh structure and elastic components, which fold to reduce drag during ascent and unfold to increase drag during descent; the latter includes a lightweight frame and unidirectional valve components, which adhere to the wall to reduce drag during ascent and close the grid to increase drag during descent. The transmission mechanism is designed based on the lever principle, including a connecting rod, a drive rod, and an operating lever. The drive rod forms a seesaw structure with the base via a support rod. An elastic thin plate is connected to the rear of the wing to assist propulsion, and a buoyancy assist device can also be added. This aircraft has a high lift-to-drag ratio, low propulsion energy consumption, stable flight, and strong adaptability.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a flapping-wing aircraft. Background Technology

[0002] Ornithopter-wing aircraft, which mimic bird flight patterns and possess advantages such as agility and low noise, have become a research hotspot in the aviation field.

[0003] However, existing technologies have significant drawbacks, the core issue being insufficient wing drag adjustment capabilities: First, excessive energy consumption. Fixed-structure wings exhibit little drag difference during ascent and descent, requiring significant air resistance to be overcome during ascent, necessitating high power output from the drive mechanism and limiting endurance; Second, low flight efficiency. They cannot simulate the dynamic adjustment function of bird wings—"folding up to reduce drag during ascent, unfolding to increase drag during descent"—resulting in an imbalance between lift and drag, making long-duration stable flight difficult; Third, cumbersome transmission mechanisms. Most drive systems directly drive wing flapping, failing to fully utilize leverage principles for effort reduction, further exacerbating energy consumption; Fourth, poor adaptability. A single wing structure cannot simultaneously meet the drag requirements of different flight attitudes, highlighting the performance conflict between low-altitude hovering and rapid propulsion.

[0004] The root of these problems lies in the failure to effectively integrate and structurally optimize the "vacuum lift principle" of bird flight, the "reaction force propulsion principle" of fish swimming, and the lever principle of effort saving. This results in existing flapping-wing aircraft struggling to overcome the bottleneck of "high energy consumption and low efficiency." Therefore, developing a flapping-wing aircraft that can dynamically adjust drag and incorporates multiple biomimetic principles has become a key direction for the industry's development. Summary of the Invention

[0005] The purpose of this invention is to overcome the above-mentioned problems and provide a flapping-wing aircraft. To achieve the above objective, this invention adopts the following technical solution: A flapping-wing aircraft includes at least two wing bodies and a transmission mechanism for driving the wing bodies to flap up and down, wherein the wing bodies reduce drag when ascending and increase drag when descending.

[0006] As an improvement, the main body of the wing is a mesh structure wing, which includes a lightweight mesh structure and several elastic components disposed on the lightweight mesh structure. The elastic components are movably connected to the lightweight mesh structure. The elastic components fold downward as the lightweight mesh structure rises and unfold flat as the lightweight mesh structure descends.

[0007] As an improvement, the lightweight mesh structure includes an outer frame, several horizontal beams, several vertical beams, and connecting wires. The outer frame is made of a lightweight and sturdy material. The horizontal beams and vertical beams are intersected to form a skeleton. The connecting wires pass through uniform small holes on the skeleton to form a lightweight mesh structure. The horizontal beams of the lightweight mesh structure are provided with multiple connecting buckles. The lightweight mesh structure is provided with a folding mechanism or a telescopic mechanism.

[0008] As an improvement, the elastic component is a thin film structure, the thin film structure is rectangular, adjacent thin film structures are in close contact with each other, and the middle area of ​​the thin film structure is fixedly connected to the connecting filaments of a lightweight mesh structure; Alternatively, the elastic component may be a thin plate structure, the thin plate structure being rectangular, adjacent thin plate structures being in close contact with each other, the middle area of ​​the thin plate being connected to the connecting wires of the lightweight mesh structure through a sliding structure, and a torsion spring being provided in the middle of the thin plate structure, the two ends of the torsion spring being in contact with the bottom surfaces of the two sides of the thin plate structure.

[0009] As an improvement, the main body of the wing is a one-way valve structure wing. The one-way valve structure wing includes a lightweight frame and a number of one-way valve components disposed within the lightweight frame. The lightweight frame is divided into a number of grids, and the one-way valve components are disposed in each grid. The one-way valve components attach to the inner wall of the grid as the lightweight frame rises, and the one-way valve components unfold and close the grid as the lightweight frame descends.

[0010] As an improvement, the one-way valve assembly is an arc-shaped valve, which has a fixed end and a free end. The fixed end is connected to the inner wall of the grid, and the free end faces downward. The width of the arc-shaped film in the middle is 1.5 to 2.5 times the radius or side length of the grid. Two adjacent arc-shaped films are closely attached to each other at the grid wall. Alternatively, the unidirectional valve assembly may be a bowl-shaped valve, which is a hemispherical elastic membrane with its back side fixedly connected to the inner wall of the grid and its opening facing downwards.

[0011] As an improvement, the transmission mechanism includes a connecting rod, a driving rod, a base, a support rod, and an operating lever. One end of the connecting rod is movably connected to the wing body, and the other end is connected to the driving rod. The middle part of the driving rod is movably connected to the base via a vertical rod. One end of the support rod is connected to the driving rod via a connecting buckle on a crossbeam, and the other end is fixed to the base. The support rod is provided with a telescopic mechanism. One end of the operating lever is connected to the driving rod, and the other end extends to the middle of the base and is slidably or rotatably connected to the base.

[0012] As an improvement, an elastic plate is connected to the rear side of the wing body, and the elastic plate swings synchronously with the up and down flapping of the wing body to propel it forward.

[0013] As an improvement, a buoyancy aid device is also included, which is a hydrogen balloon or a hot air balloon, connected to the crossbeam or connecting rod of the transmission mechanism via a connector.

[0014] As an improvement, the wing body is configured as four, with two symmetrically distributed on each side, and the connecting rods of the two wings on the same side are slidably connected to the end of the same drive rod.

[0015] The advantages of this invention are: 1. This invention is highly efficient and labor-saving, with significantly reduced energy consumption: The main body of the wings achieves "reduced drag during ascent and increased drag during descent" through the dynamic movement of elastic components or one-way valves, greatly improving the lift-to-drag ratio; combined with a transmission mechanism based on the seesaw principle, the driving energy consumption is lower than that of traditional flapping-wing aircraft, and the endurance is improved.

[0016] 2. This invention is stable and highly adaptable: the two wing bodies can be adapted to different flight scenarios; the design of the buoyancy assist device and the elastic thin plate respectively improves flight stability and forward propulsion efficiency, and can cope with complex airflow environments.

[0017] 3. The invention has a stable structure and a long service life: the main body of the wing is made of lightweight and high-strength materials, and the elastic components and valve structure have good fatigue resistance; the connection points of the transmission mechanism are all designed with wear resistance to reduce mechanical wear and extend the service life of the equipment. Attached Figure Description

[0018] Figure 1 This is a structural diagram of the mesh structure in Example 1.

[0019] Figure 2 This is a structural diagram of the thin film structure in Example 1.

[0020] Figure 3 This is a structural diagram of the thin plate structure in Example 1.

[0021] Figure 4 This is a structural diagram of the unidirectional valve structure wing in Example 2.

[0022] Figure 5 This is a structural diagram of the coronal plane of the lattice and the sagittal plane of the valve in Example 2.

[0023] Figure 6 This is a structural diagram of the coronal plane and the sagittal plane of the valve in Example 2.

[0024] Figure 7 This is a structural diagram of the two wings in Example 3.

[0025] Figure 8 This is a top view of the four wings in Example 4.

[0026] Figure 9These are the rear and side views of the four wings in Example 4.

[0027] The diagram is labeled as follows: 11. Lightweight mesh structure; 111. First front beam; 112. First rear beam; 113. First inner beam; 114. First outer beam; 115. First horizontal beam; 116. First vertical beam; 117. First vertical mesh line; 118. First diagonal mesh line; 119. First horizontal mesh line; 12. Thin film structure; 121. First intermediate fold line; 13. Thin plate structure; 131. Second intermediate fold line; 132. Torsion spring; 141. Second anterior beam; 142. Second posterior beam; 143. Second inner beam; 144. Second outer beam; 145. Second transverse beam; 146. Second vertical beam; 147. Grid; 148. Internal valves in open state; 149. Internal valves in closed state; 1410. Bowl-shaped valve; 151. First left valve; 152. First right valve; 153. Free end of the first valve; 161. Second left valve; 162. Second right valve; 163. Free end of the second valve; 211. Third artificial wing; 212. Third crossbeam; 213. Third connecting rod; 214. Third drive rod; 215. Third connecting buckle; 216. Third upright; 217. Third base; 218. Third elastic sheet; 219. Hydrogen balloon; 2110. Third support rod; 221. Fourth artificial wing; 222. Fourth crossbeam; 223. Fourth connecting rod; 224. Fourth drive rod; 225. Fourth connecting buckle; 226. Seesaw center fulcrum; 227. Fourth base; 228. Fourth elastic plate; 229. Hot air balloon; 2210. Fourth support rod; 2211. Seesaw support column; 2212. Fourth operating lever. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0029] In the description of the embodiments of the present invention, it should be noted that if terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of the invention is in use, they are only for the convenience of describing the present invention 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, and therefore should not be construed as a limitation of the present invention. Furthermore, terms such as "first," "second," and "third" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0030] Furthermore, the use of terms such as "horizontal," "vertical," and "sag" does not imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0031] In the description of the embodiments of the present invention, "multiple" means at least two.

[0032] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and 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 the present invention according to the specific circumstances.

[0033] The present invention will now be described in detail and specifically through specific embodiments to enable a better understanding of the present invention. However, the following embodiments do not limit the scope of protection of the present invention. Example

[0034] This embodiment discloses a flapping-wing aircraft.

[0035] This embodiment includes at least two wing bodies and a transmission mechanism for driving the wing bodies to flap up and down. The wing bodies reduce resistance when they rise and increase resistance when they fall.

[0036] The main body of the wing is a mesh structure wing, which includes a lightweight mesh structure and several elastic components on the lightweight mesh structure. The elastic components are movably connected to the lightweight mesh structure. The elastic components fold downward as the lightweight mesh structure rises and unfold flat as the lightweight mesh structure descends.

[0037] like Figure 1 The lightweight mesh structure 11 shown in this embodiment includes a first outer frame, several first horizontal beams 115, several first vertical beams 116, and first connecting wires. The first outer frame is made of a lightweight and sturdy material. The first horizontal beams 115 and the first vertical beams 116 are intersected to form a skeleton. The first connecting wires pass through uniform small holes in the skeleton to form the lightweight mesh structure 11. The first horizontal beams 115 of the lightweight mesh structure 11 are provided with multiple connecting buckles. The lightweight mesh structure 11 is provided with a folding mechanism or a telescopic mechanism. The first outer frame is composed of a first front beam 111, a first rear beam 112, a first inner beam 113, and a first outer beam 114. The connecting wires are composed of first vertical mesh wires 117, first diagonal mesh wires 118, and first horizontal mesh wires 119.

[0038] like Figure 2 The elastic component shown is a thin film structure 12. The middle region of the thin film structure 12 is provided with a first middle fold line 121. The thin film structure 12 is rectangular. Adjacent thin film structures 12 are in close contact with each other. The middle region of the thin film structure 12 is fixedly connected to the connecting wires of the lightweight mesh structure. like Figure 3 The elastic component shown is a thin plate structure 13. The thin plate structure 13 has a second intermediate fold line 131 in the middle area. The thin plate structure 13 is rectangular. Adjacent thin plate structures 13 are in close contact with each other. The middle area of ​​the thin plate is connected to the connecting wire of the lightweight mesh structure through a sliding structure. A torsion spring 132 is provided in the middle of the thin plate structure 13. The two ends of the torsion spring 132 are in contact with the bottom surfaces of the two sides of the thin plate structure 13.

[0039] The main body of the wings is the core component for achieving "drag reduction during ascent and drag increase during descent." It is designed in two structural forms, which can be selected according to flight requirements, and both have dynamic drag adjustment capabilities. This embodiment features a mesh-structured wing: composed of a lightweight mesh structure and several elastic components, using lightweight, high-strength materials throughout, balancing structural stability with lightweight design requirements. Lightweight mesh structure: Serving as the supporting skeleton for the wings, this structure includes an outer frame, crossbeams, vertical beams, and connecting wires. The outer frame is made of lightweight yet strong materials such as carbon fiber and can be designed in various shapes, including round and square, to suit different flight scenarios. Crossbeams and vertical beams intersect to form a mesh skeleton, enhancing overall structural strength. Small holes are evenly spaced on the skeleton, through which connecting wires (such as high-strength nylon thread or thin steel wire) pass to form a complete mesh structure, reducing weight while ensuring breathability. Multiple connecting buckles are provided on the crossbeams for connection to the transmission mechanism. The mesh structure also incorporates folding or telescopic mechanisms (such as folding hinges or elastic telescopic rods) for easy storage and transportation.

[0040] Elastic components: available in two forms, thin-film structure and thin-plate structure, both installed beneath a lightweight mesh structure to achieve adaptive resistance adjustment. This embodiment can be a thin film structure: rectangular in shape, with adjacent films closely attached to each other, covering the area below the mesh structure. The middle area of ​​the film is fixedly connected to the connecting threads of the mesh structure. Dynamic deformation is achieved by utilizing the elasticity of the film itself. When the wings rise, air resistance acts on the lower surface of the film, causing it to fold downwards along the connection point, exposing the mesh structure and minimizing the upward resistance. When the wings descend, air resistance acts in the opposite direction, pushing the film to unfold and completely cover the mesh structure, significantly increasing the downward resistance and thus generating upward lift.

[0041] This embodiment can also be a thin-plate structure: rectangular in shape, with adjacent thin plates tightly attached to each other. The middle area of ​​the thin plates is connected to the connecting wires via a sliding structure (such as a slider and a groove). A torsion spring is provided in the middle of the thin plate, with both ends of the torsion spring fitting against the bottom surfaces on both sides of the thin plate, keeping the thin plate horizontal in its natural state. When the wings rise, air resistance overcomes the spring force of the torsion spring, causing the thin plate to fold downwards around the sliding structure, reducing resistance. When the wings descend, the torsion spring returns to its original position, pushing the thin plate to unfold, which, together with air resistance, increases resistance. The principle is the same as that of the membrane structure, but the structure has higher strength and is suitable for scenarios with large load capacities. Example

[0042] This embodiment discloses a flapping-wing aircraft.

[0043] This embodiment includes at least two wing bodies and a transmission mechanism for driving the wing bodies to flap up and down. The wing bodies reduce resistance when they rise and increase resistance when they fall.

[0044] like Figure 4 As shown, the wing body is a one-way valve structure wing. The one-way valve structure wing includes a lightweight frame and several one-way valve components disposed within the lightweight frame. The lightweight frame consists of a second front beam 141, a second rear beam 142, a second inner beam 143, a second outer beam 144, a second crossbeam 145, and a second vertical beam 146. The lightweight frame is divided into several grids 147, and the one-way valve components are correspondingly disposed in each grid 147. The one-way valve components attach to the inner wall of the grid 147 as the lightweight frame rises, and unfold and close the grid 147 as the lightweight frame descends. Figure 4 In the open state 148 of the inner lattice 147, the valves are in contact with the inner wall of the lattice 147, and the wings are in an ascending state; in the closed state 149 of the inner lattice 147, the artificial wings are descending.

[0045] The one-way valve assembly is an arc-shaped valve with a fixed end and a free end. The fixed end is connected to the inner wall of the grid 147, and the free end faces downward. The width of the arc-shaped membrane in the middle is 1.5 to 2.5 times the radius or side length of the grid 147. Two adjacent arc-shaped membranes are closely attached to the wall of the grid 147. like Figure 4The unidirectional valve assembly shown can also be a cup-shaped valve 1410. The cup-shaped valve 1410 is a hemispherical elastic membrane with its back side fixedly connected to the inner wall of the grid 147 and its opening facing downward.

[0046] like Figure 5 The diagram shows the coronal plane of grid 147 and the sagittal plane of the valve, with two states: ascending and descending. At this time, the diagram shows the first left valve 151, the first right valve 152, and the free end of the first valve 153. When the wings descend, the left and right valves are attached together, and when they ascend, the left and right valves are separated.

[0047] like Figure 6 The diagram shows the coronal plane of the valve and the sagittal plane of the grid 147. The diagram includes the second left valve 161, the second right valve 162, and the free end of the second valve 163.

[0048] One-way valve structure wings: Composed of a lightweight frame and several one-way valve components, drag is adjusted by the one-way opening and closing of the valves, making the structure more suitable for low-altitude hovering. Lightweight frame: Made of the same material as the outer frame of the mesh structure, the interior is divided into several independent grids (circular or square) by horizontal and vertical beams. Each grid corresponds to a unidirectional valve assembly to ensure uniform resistance adjustment.

[0049] One-way valve assembly: Available in two types, arc-shaped and cup-shaped valves, both made of lightweight elastic membrane with the opening facing downwards, enabling unidirectional movement of "opening on rise and closing on fall". Arc-shaped valves: These valves have a fixed end and a free end. The fixed end connects to the inner wall of the grid, while the free end faces downwards. The width of the arc-shaped membrane in the middle is 1.5–2.5 times the radius or side length of the grid. Adjacent arc-shaped membranes are tightly attached to the grid wall. When the wings rise, air pushes the valves from below, causing them to adhere to the inner wall of the grid, keeping the grid open and reducing drag. When the wings descend, air compresses the valves from above, causing the free ends to adhere to each other, closing the grid and forming a closed surface, increasing descent drag.

[0050] Bowl-shaped valve: This is a hemispherical elastic membrane, fixedly connected to the inner wall of the grid on its dorsal side, with the opening facing downwards. When the wings rise, air enters the interior of the bowl-shaped structure, pushing the valve against the inner wall of the grid to achieve decompression; when the wings descend, air compresses the opening end of the valve, causing it to fully expand and close the grid, generating greater drag. Its structural stability is superior to that of an arc-shaped valve. Example

[0051] This embodiment discloses a flapping-wing aircraft.

[0052] This embodiment includes two wing bodies and a transmission mechanism for driving the wing bodies to flap up and down. The wing bodies reduce resistance when they rise and increase resistance when they descend.

[0053] The main body of the wing is a mesh structure wing, which includes a lightweight mesh structure and several elastic components on the lightweight mesh structure. The elastic components are movably connected to the lightweight mesh structure. The elastic components fold downward as the lightweight mesh structure rises and unfold flat as the lightweight mesh structure descends.

[0054] like Figure 7 As shown, the lightweight mesh structure of the third artificial wing 211 includes an outer frame, several third crossbeams 212, several vertical beams, and connecting threads. The outer frame is made of lightweight and sturdy materials. The crossbeams and vertical beams are connected to form a skeleton. The connecting threads pass through the uniform small holes on the skeleton to form a lightweight mesh structure. The crossbeams of the lightweight mesh structure are provided with multiple connecting buckles. The lightweight mesh structure is provided with a folding mechanism or a telescopic mechanism.

[0055] The elastic component is a thin film structure, which is rectangular in shape. Adjacent thin film structures are closely attached to each other, and the middle area of ​​the thin film structure is fixedly connected to the connecting filaments of the lightweight mesh structure. Alternatively, the elastic component may be a thin plate structure, which is rectangular in shape. Adjacent thin plate structures are in close contact with each other. The middle area of ​​the thin plate is connected to the connecting wires of the lightweight mesh structure through a sliding structure. A torsion spring is provided in the middle of the thin plate structure, and the two ends of the torsion spring are in contact with the bottom surfaces of the two sides of the thin plate structure.

[0056] like Figure 7 As shown, the transmission mechanism includes a third connecting rod 213, a third driving rod 214, a third base 217, a third support rod 2110, and an operating lever. One end of the third connecting rod 213 is movably connected to the wing body, and the other end of the third connecting rod 213 is connected to the third driving rod 214. The middle part of the third driving rod 214 is movably connected to the third base 217 through the third upright rod 216. One end of the third support rod 2110 is connected to the third driving rod 214 through the third connecting buckle 215 on the crossbeam, and the other end of the third support rod 2110 is fixed to the third base 217. The third support rod 2110 is provided with a telescopic mechanism.

[0057] A third elastic plate 218 is connected to the rear side of the wing body. The third elastic plate 218 swings synchronously with the up and down flapping of the wing body to propel it forward.

[0058] It also includes a buoyancy assist device. In this embodiment, the buoyancy assist device is a hydrogen balloon 219, which is connected to the third crossbeam 212 or the third connecting rod 213 of the transmission mechanism via a connector.

[0059] Wing auxiliary structure: Both types of wings have elastic plates attached to the rear side. The elastic plates are made of elastic material with memory properties and swing synchronously with the up and down flapping of the wing body. When the wings rise, the plates tilt upwards and when they fall, the plates swing downwards, simulating the propulsion principle of a fish tail swimming, providing forward driving force for the aircraft and improving flight efficiency.

[0060] The buoyancy assist device is a hydrogen balloon or hot air balloon, connected to the crossbeam or connecting rod of the transmission mechanism via a connector. Its function is to provide additional buoyancy, reduce the weight that the wing body needs to bear, and further reduce propulsion energy consumption; at the same time, it can improve the flight stability of the aircraft and avoid attitude imbalance caused by airflow disturbances, which is especially suitable for personal flight scenarios. Example

[0061] This embodiment discloses a flapping-wing aircraft.

[0062] This embodiment includes four wing bodies and a transmission mechanism for driving the wing bodies to flap up and down. The wing bodies reduce resistance when they rise and increase resistance when they descend.

[0063] The main body of the wing is a one-way valve structure wing, which includes a lightweight frame and several one-way valve components set in the lightweight frame. The lightweight frame is divided into several grids, and the one-way valve components are correspondingly set in each grid. The one-way valve components attach to the inner wall of the grid as the lightweight frame rises, and the one-way valve components unfold and close the grid as the lightweight frame descends.

[0064] The one-way valve assembly is an arc-shaped valve with a fixed end and a free end. The fixed end is connected to the inner wall of the grid, and the free end faces downward. The width of the arc-shaped membrane in the middle is 1.5 to 2.5 times the radius or side length of the grid. Two adjacent arc-shaped membranes are closely attached to the grid wall. Alternatively, the one-way valve assembly may be a cup-shaped valve, which is a hemispherical elastic membrane with its back side fixedly connected to the inner wall of the grid and its opening facing downwards.

[0065] like Figure 8 , Figure 9As shown, the transmission mechanism of the fourth artificial wing 221 includes a fourth connecting rod 223, a fourth driving rod 224, a fourth base 227, a fourth support rod 2210, and a fourth operating lever 2212. One end of the fourth connecting rod 223 is movably connected to the wing body, and the other end of the fourth connecting rod 223 is connected to the fourth driving rod 224. The middle part of the fourth driving rod 224 is slidably connected to both ends of the lever of the seesaw mechanism. The seesaw mechanism is provided with a seesaw middle fulcrum 226 and a seesaw support column 2211. One end of the fourth support rod 2210 is connected to the fourth driving rod 224 through the fourth connecting buckle 225 on the fourth crossbeam 222. The other end of the fourth support rod 2210 is fixed to the fourth base 227. The fourth support rod 2210 is provided with a telescopic mechanism. One end of the fourth operating lever 2212 is connected to the fourth driving rod 224, and the other end of the fourth operating lever 2212 extends to the middle of the base and is slidably or rotatably connected to the base.

[0066] A fourth elastic plate 228 is connected to the rear side of the wing body. The fourth elastic plate 228 swings synchronously with the up and down flapping of the wing body to propel it forward.

[0067] It also includes a buoyancy assist device. In this embodiment, the buoyancy assist device is a hot air balloon 229, which is connected to the crossbeam or connecting rod of the transmission mechanism through a connector.

[0068] The wings are set to four main bodies, with two symmetrically distributed on each side. The connecting rods of the two wings on the same side are slidably connected to the end of the same drive rod.

[0069] The transmission mechanism adopts a lever principle design, which significantly reduces drive energy consumption. It includes a connecting rod, a drive rod, a base, a support rod, and an operating lever, and can achieve manual or mechanical drive. Core Connection and Drive: One end of the connecting rod is movably connected to the wing body (multi-angle rotation can be achieved through a ball joint structure to ensure flexible wing flapping), and the other end is connected to the drive rod; the middle of the drive rod is movably connected to the base through a vertical rod, which acts as a lever fulcrum, forming the core structure of the seesaw. One end of the operating lever is connected to the drive rod, and the other end extends to the middle of the base, where it slides or rotates—in manual drive, the operator manipulates the operating lever to rotate the drive rod around the vertical rod; in mechanical drive, the operating lever can be moved by a motor or hydraulic mechanism.

[0070] Support and Adjustment: One end of the support rod is connected to the drive rod via a connecting buckle on the crossbeam, and the other end is fixed to the base. The support rod is equipped with a telescopic mechanism (such as a hydraulic telescopic rod), which can change the lever arm ratio of the drive rod by adjusting the length, further optimizing the labor-saving effect. When the wing body is set to four (two symmetrically distributed on each side), the connecting rods of the two wings on the same side are slidably connected to the end of the same drive rod, ensuring that the wings on the same side move synchronously and improving flight stability.

[0071] The specific embodiments of the present invention have been described in detail above, but they are merely examples, and the present invention is not equivalent to the specific embodiments described above. For those skilled in the art, any equivalent modifications and substitutions to the present invention are also within the scope of the present invention. Therefore, all equivalent transformations and modifications made without departing from the spirit and scope of the present invention should be covered within the scope of the present invention.

Claims

1. A flapping-wing aircraft, characterized in that, It includes at least two wing bodies and a transmission mechanism for driving the wing bodies to flap up and down, wherein the wing bodies reduce resistance when rising and increase resistance when falling.

2. The flapping-wing aircraft according to claim 1, characterized in that, The main body of the wing is a mesh structure wing, which includes a lightweight mesh structure and several elastic components disposed on the lightweight mesh structure. The elastic components are movably connected to the lightweight mesh structure. The elastic components fold downward as the lightweight mesh structure rises and unfold flat as the lightweight mesh structure descends.

3. A flapping-wing aircraft according to claim 2, characterized in that, The lightweight mesh structure includes an outer frame, several horizontal beams, several vertical beams, and connecting wires. The outer frame is made of lightweight and sturdy materials. The horizontal beams and vertical beams are connected to each other to form a skeleton. The connecting wires pass through uniform small holes in the skeleton to form a lightweight mesh structure. The horizontal beams of the lightweight mesh structure are provided with multiple connecting buckles. The lightweight mesh structure is provided with a folding mechanism or a telescopic mechanism.

4. A flapping-wing aircraft according to claim 3, characterized in that, The elastic component is a thin film structure, which is rectangular in shape. Adjacent thin film structures are in close contact with each other, and the middle area of ​​the thin film structure is fixedly connected to the connecting filaments of a lightweight mesh structure. Alternatively, the elastic component may be a thin plate structure, the thin plate structure being rectangular, adjacent thin plate structures being in close contact with each other, the middle area of ​​the thin plate being connected to the connecting wires of the lightweight mesh structure through a sliding structure, and a torsion spring being provided in the middle of the thin plate structure, the two ends of the torsion spring being in contact with the bottom surfaces of the two sides of the thin plate structure.

5. A flapping-wing aircraft according to claim 1, characterized in that, The wing body is a one-way valve structure wing. The one-way valve structure wing includes a lightweight frame and several one-way valve components disposed within the lightweight frame. The lightweight frame is divided into several grids, and the one-way valve components are disposed in each grid. The one-way valve components attach to the inner wall of the grid as the lightweight frame rises, and the one-way valve components unfold and close the grid as the lightweight frame descends.

6. A flapping-wing aircraft according to claim 5, characterized in that, The unidirectional valve assembly is an arc-shaped valve with a fixed end and a free end. The fixed end is connected to the inner wall of the grid, and the free end faces downward. The width of the arc-shaped film in the middle is 1.5 to 2.5 times the radius or side length of the grid. Two adjacent arc-shaped films are closely attached to the grid wall. Alternatively, the unidirectional valve assembly may be a bowl-shaped valve, which is a hemispherical elastic membrane with its back side fixedly connected to the inner wall of the grid and its opening facing downwards.

7. A flapping-wing aircraft according to claim 1, characterized in that, The transmission mechanism includes a connecting rod, a driving rod, a base, a support rod, and an operating lever. One end of the connecting rod is movably connected to the wing body, and the other end is connected to the driving rod. The middle part of the driving rod is movably connected to the base via a vertical rod. One end of the support rod is connected to the driving rod via a connecting buckle on a crossbeam, and the other end is fixed to the base. The support rod is equipped with a telescopic mechanism. One end of the operating lever is connected to the driving rod, and the other end extends to the middle of the base and is slidably or rotatably connected to the base.

8. A flapping-wing aircraft according to claim 1, characterized in that, An elastic plate is connected to the rear side of the wing body. The elastic plate swings synchronously with the up and down flapping of the wing body to propel it forward.

9. A flapping-wing aircraft according to claim 1, characterized in that, It also includes a buoyancy aid device, which is a hydrogen balloon or a hot air balloon, connected to the crossbeam or connecting rod of the transmission mechanism via a connector.

10. A flapping-wing aircraft according to claim 1, characterized in that, The wing body is configured as four, with two symmetrically distributed on each side, and the connecting rods of the two wings on the same side are slidably connected to the end of the same drive rod.

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