An array wing flight device and its application

Abstract

The present invention discloses an arrayed wing flight device, and the arrayed wing flight device comprises: a carrier; and two or more groups of wing components arrayed on the carrier. The present invention provides an arrayed wing flight device, which combines a plurality of small vibrating wing components into a two-dimensional or three-dimensional grid-shaped carrier to form a new type of adjustable flight power unit. Such a power device can be applied to unmanned or manned aircraft to achieve efficient and highly flexible flight.

Description

Technical Field

[0001] The present invention relates to the technical field of micro bionic flying devices, and particularly relates to an arrayed wing flying device and its application. Background Art

[0002] After hundreds of millions of years of evolution, insects have evolved the most efficient and successful flight mode on the earth. Taking flies as an example, they can generate power more than ten times their own thrust-to-weight ratio with extremely thin wings. Current human aircraft are far from achieving this, and even birds cannot compare. Moreover, many insects such as bees can hover in the air for a long time, and they only carry very little biomass energy, indicating their extremely low flight energy consumption. In addition, the flight of insects such as flies is extremely flexible and can achieve rapid mid-air turning, which is currently incomparable to any artificial aircraft or even birds.

[0003] Currently, artificial aircraft using aerodynamics mainly fall into two categories: fixed wings and rotors. Research shows that the flight principle of flies is different from that of the above artificial aircraft and also different from that of birds. The reason why flies can fly is that they cleverly utilize the micro air vortices generated by the high-frequency vibration of their membranous wings. This is a very efficient flight mode, and the generation of these micro vortices is also closely related to the morphological size of the wing.

[0004] Currently, there are attempts to simulate the flight of a single insect, but their purpose is not to, and it is also impossible to simply expand the size to become a general-purpose flight power engine. Therefore, designing a flight device that can effectively utilize the efficient flight mode of insects and can be replicated and expanded without limit is one of the urgent problems to be solved in the field of flight device design. Summary of the Invention

[0005] In view of this, the present invention provides an arrayed wing flying device, which combines a large number of small vibrating wing components into a two-dimensional or three-dimensional grid-shaped carrier to form a controllable new flight power unit. Such a power device can be applied to unmanned or manned aircraft to achieve efficient and highly flexible flight.

[0006] To achieve the above object, according to one aspect of the present invention, an arrayed wing flying device is provided.

[0007] The arrayed wing flying device described in the present invention includes:

[0008] A carrier;

[0009] Two or more groups of wing components arranged in an array on the carrier.

[0010] In one embodiment, the carrier is a frame structure, and wing components are provided at at least two nodes of the frame structure.

[0011] In one embodiment, the carrier is a planar frame structure.

[0012] In one embodiment, the carrier is a three-dimensional frame structure.

[0013] In one embodiment, the frame structure has a folded state and an unfolded state.

[0014] In one embodiment, the folded state and the unfolded state of the frame structure can be converted into each other.

[0015] In one embodiment, each group of the wing assemblies includes one or more pairs of wings and at least one power device, and the power device provides power for the wings.

[0016] In one embodiment, each pair of the wings is arranged in parallel.

[0017] In one embodiment, each wing includes a wing root and a wing body, the wing root is connected to the power device, and the wing root drives the wing body to move.

[0018] In one embodiment, the wing is a layered structure.

[0019] In one embodiment, the wing is a flexible layered structure.

[0020] In one embodiment, the wing is a rigid layered structure.

[0021] In one embodiment, the wing is composed of rigid wing veins and flexible wing leaves.

[0022] In one embodiment, the wing assembly further includes at least one pair of balance components.

[0023] In one embodiment, the balance components are arranged beside the wings, and the balance components adjust the micro vortices generated by the wings.

[0024] In one embodiment, the arrayed wing flight device further includes a central control component, and the central control component controls the wing assemblies.

[0025] In one embodiment, the arrayed wing flight device further includes a sensor, the sensor measures the flight parameters of the arrayed wing flight device, and sends the measured results to the central control component, and the central control component sends execution commands to the wing assemblies according to preset rules.

[0026] In one embodiment, the power device is an electromagnetic motor.

[0027] In one embodiment, the power device includes:

[0028] A wing flapping power component, which deforms after being stimulated by the outside world, and thus drives the wing to perform up-and-down flapping movements through its deformation;

[0029] A wing direction-changing power component, which deforms after being stimulated by the outside world. The deformation of the wing direction-changing power component applies a force to a part of the wing flapping power component in a direction perpendicular to the plane formed by the up-and-down flapping of the wing, thereby causing the wing flapping power component to twist, and further changing the flapping direction of the wing.

[0030] In one embodiment, the power device is a laminated composite structure. The power device includes a first horizontally extending layer and a second horizontally extending layer, and the first horizontally extending layer and the second horizontally extending layer are laminated together.

[0031] The wing root is located between the first horizontally extending layer and the second horizontally extending layer, and the two wing bodies in each pair of wings are respectively located on opposite sides of the laminated composite structure.

[0032] At least one of the first horizontally extending layer and the second horizontally extending layer will contract / elongate in the lateral direction along the two sides where the wing is located under the stimulation of the outside world, and the contraction rate / elongation rate is different under the same outside stimulation.

[0033] In one embodiment, the power device further includes a first longitudinally extending layer and a second longitudinally extending layer. The first longitudinally extending layer is located outside the first horizontally extending layer and is laminated and fixed to the first horizontally extending layer, and the second longitudinally extending layer is located outside the second horizontally extending layer and is laminated and fixed to the second horizontally extending layer.

[0034] The first longitudinally extending layer is composed of a first fixing part and a first extending part, and the first fixing part and the first extending part are arranged adjacent to each other on the surface of the first horizontally extending layer.

[0035] The second longitudinally extending layer is composed of a second fixing part and a second extending part, and the second fixing part and the second extending part are arranged adjacent to each other on the surface of the second horizontally extending layer.

[0036] Under the stimulation of the outside world, the first extending part and the second extending part will contract / elongate in the longitudinal direction perpendicular to the horizontal direction. Under the same outside stimulation, the contraction rate / elongation rate of the first fixing part is less than that of the first extending part or the contraction rate / elongation rate is zero, and the contraction rate / elongation rate of the second fixing part is less than that of the second extending part or the contraction rate / elongation rate is zero.

[0037] Vertically, the arrangement order of the first extension part and the first fixing part in the first longitudinally extending layer is opposite to the arrangement order of the second extension part and the second fixing part in the second longitudinally extending layer.

[0038] In one embodiment, the power device includes:

[0039] A first housing, the first housing having a curved surface structure, and two opposite side ends of the curved surface structure of the first housing are respectively connected to the ends of the wing root to form a connecting shaft or a shaftless hinge, and the wing can rotate relative to the first housing around the connecting shaft or the shaftless hinge;

[0040] A second housing, the second housing having a curved surface structure, and two opposite side ends of the curved surface structure of the second housing are respectively in contact with at least a part other than the end points of the wing root, and the inner side of the curved surface of the second housing is arranged opposite to the inner side of the curved surface of the first housing to form a power device cavity;

[0041] A wing flapping power component, the wing flapping power component connecting the inner sides of the first housing and the second housing, and the wing flapping power component deforms after being stimulated by the outside world, so as to drive the relative distance between the first housing and the second housing to change through its deformation. Under the action of the force exerted on the wing by the cooperation of the first housing and the second housing, the wing makes an up-and-down flapping motion;

[0042] A wing direction-changing power component, the wing direction-changing power component extending in the direction parallel to the curved surface structures of the first housing and the second housing in the power device cavity, the wing direction-changing power component penetrating through the wing flapping power component or adhering to the surface of the wing flapping power component, and being closely fitted with the wing flapping power component. The wing direction-changing power component deforms after being stimulated by the outside world, and the deformation drives the part of the wing flapping power component that is in contact with it, so as to cause the wing flapping power component to be distorted, and further change the flapping direction of the wing.

[0043] In one embodiment, the power device drives the wing through a lever, wherein one end of the lever is connected to the power device, the other end of the lever is connected to the wing, the fulcrum of the lever is arranged on the carrier, and the lever is connected to the fulcrum in an axial or non-axial manner.

[0044] In one embodiment, the external stimulus is electrification.

[0045] In one embodiment, the first extension part, the first laterally extending layer, the second laterally extending layer, and the second extension part are all connected to a power source through wires, and the central control component controls the expansion and contraction of the first extension part, the first laterally extending layer, the second laterally extending layer, and the second extension part respectively by controlling the power source.

[0046] In one embodiment, each group of the wing assemblies includes one or more pairs of axially symmetric wings. The wings are of a two-layer or multi-layer laminated structure. When the materials of each layer of the wings are energized, they elongate in the direction away from the carrier, and the arrangement order of each layer is such that the elongation lengths in the direction away from the carrier increase after energization.

[0047] The array-type wing flight device described in the present invention is applied to unmanned or manned aircraft, airplanes, or airships. And it can be used in combination with various existing flight power devices.

[0048] The advantages of the array-type wing flight device provided according to the present invention compared with the existing flight power devices (engines) are as follows: First, it is more efficient because the flight mode of insects has been proven to be the most efficient mode at present. Second, it is more flexible in changing directions. The wings of the entire wing array can achieve instantaneous simultaneous turning under the control of the central control component. Third, it is lighter because, compared with traditional engines mainly composed of metal components, the device of the present invention is mainly composed of polymer materials. Fourth, it can be deformed, being deployed when in use or folded when not in use. Fifth, it is more tolerant of local damage / malfunctions. A few damaged components of an existing engine may cause an air crash, while even if a small part of the wing array is damaged / malfunctions, it will not cause the collapse of the overall system.

[0049] The array-type wing flight device provided according to the present invention combines numerous small vibrating wing assemblies into a two-dimensional or three-dimensional grid-shaped carrier to form a new controllable flight power unit. Moreover, the multiple wing assemblies are independent of each other and do not interfere with each other. Even if some wing assemblies are damaged, it will not affect the normal operation of other wing assemblies, with higher safety, thus achieving efficient and highly flexible flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] The drawings are used to better understand the present invention and do not constitute an improper limitation to the present invention. Among them:

[0051] Figure 1 is one of the schematic structural diagrams of the array-type wing flight device according to the present invention;

[0052] Figure 2 is another schematic structural diagram of the array-type wing flight device according to the present invention;

[0053] Figure 3 is the third schematic structural diagram of the array-type wing flight device according to the present invention;

[0054] Figure 4 is the schematic diagram of the power device according to the present invention;

[0055] Figure 5 is one of the schematic diagrams of the wing assembly according to the present invention;

[0056] Figure 6It is the second schematic diagram of the wing component according to the present invention;

[0057] Figure 7 It is the third schematic diagram of the wing component according to the present invention.

[0058] List of reference numerals

[0059] 1 - Carrier, 2 - Wing, 3 - Power device, 4 - Wing root, 5 - First fixing part, 6 - First extension part, 7 - First laterally extending layer, 8 - Second laterally extending layer, 9 - Second fixing part, 10 - Second extension part, 11 - a direction-changing power component, 12 - b direction-changing power component, 13 - c direction-changing power component, 14 - d direction-changing power component, 15 - First outer shell, 16 - Second outer shell, 17 - Wing flapping power component, 18 - Wing direction-changing power component, 19 - First wing, 20 - First wing 20. Detailed implementation manners

[0060] The following describes exemplary embodiments of the present invention with reference to the accompanying drawings. Various details of the embodiments of the present invention are included to facilitate understanding, and they should be considered merely exemplary. Therefore, those of ordinary skill in the art should recognize that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present invention. Similarly, for the sake of clarity and conciseness, descriptions of well-known functions and structures are omitted in the following description.

[0061] The present invention relates to an array-type wing flight device, and the array-type wing flight device includes:

[0062] Carrier 1;

[0063] Two or more groups of wing components arranged in an array on the carrier 1.

[0064] The carrier 1 has the function of balancing and transmitting power to achieve power supply and control, and form an overall structure. The carrier 1 can also achieve direction adjustment (by rotating the carrier 1 rather than the wings).

[0065] The carrier 1 can also be a folding structure, and when the flight device is in a non-flying state, it can be folded to reduce the volume and facilitate storage. Extremely thin wires are also arranged on the carrier 1 to connect the power supply and the power device 3.

[0066] The wing components on the carrier 1 are independent of each other and do not affect each other. Multiple wing components can be arranged in parallel at intervals.

[0067] In an embodiment of the present invention, the carrier 1 is a frame structure, and wing components are provided at at least two nodes of the frame structure.

[0068] The carrier 1 can be a planar frame structure. Further, the carrier 1 can also be a planar net structure, and furthermore, the carrier 1 can be a planar foldable net structure.

[0069] The carrier 1 can be a three-dimensional frame structure. The carrier 1 can be a three-dimensional geometric structure such as a cube net structure or a prism net structure.

[0070] In an embodiment of the present invention, the frame structure has a folded state and an unfolded state. The folded state and the unfolded state of the frame structure can be converted into each other. When the flying device is in a flying state, the frame structure is in an unfolded state, and when the flying device is stopped, the frame structure is in a folded state, so as to facilitate storage and reduce the occupied space.

[0071] In an embodiment of the present invention, each set of the wing components includes one or more pairs of wings 2 and at least one power device 3, and the power device 3 provides power for the wings 2.

[0072] Each pair of the wings 2 is symmetrically arranged with respect to the power device 3. The power device 3 is arranged between each pair of the wings 2, and each pair of the wings 2 is connected to the power device 3.

[0073] As Figure 1 and Figure 2 shown, each of the power devices 3 can be connected to one pair of wings 2 or multiple pairs of wings 2. When the power device 3 is connected to multiple pairs of wings 2, the power device 3 provides power for each pair of wings 2 respectively, so that each pair of wings 2 is independent of each other and does not affect each other.

[0074] The power device 3 can provide power for the wings 2, so that the wings 2 can vibrate, and further the flying device can fly.

[0075] In an embodiment of the present invention, each pair of the wings 2 is arranged parallel to each other, so that when each pair of the wings 2 is flying, the micro-vortices generated do not affect each other.

[0076] In an embodiment of the present invention, each of the wings 2 includes a wing root 4 and a wing body. The wing root 4 is connected to the power device 3, and the wing root 4 drives the movement of the wing body of the wings 2.

[0077] The wing body can be a fan-shaped sheet, an oval sheet, and other arc-shaped and polygonal sheet structures.

[0078] The wing body can also be a feather-shaped structure.

[0079] The wing body and the wing root 4 are integrally formed.

[0080] In one embodiment of the present invention, the wing 2 is a layered structure.

[0081] The wing 2 can be a single-layer structure or a multi-layer structure.

[0082] In one embodiment of the present invention, the wing 2 is a flexible layered structure, and the wing 2 can be composed of one or more materials such as nylon and thermoplastic polyurethane elastomer rubber (TPU).

[0083] In one embodiment of the present invention, the wing 2 is a rigid layered structure, and the wing 2 can be composed of one or more materials such as polyvinyl chloride (PVC) and polypropylene (PP).

[0084] In one embodiment of the present invention, the wing 2 is composed of a rigid wing vein and a flexible wing blade. The wing vein can be composed of one or more materials such as titanium alloy, acrylonitrile-butadiene-styrene copolymer (ABS), and electroactive materials. The wing blade can be composed of one or more materials such as nylon polyethylene, polypropylene, and electroactive materials.

[0085] In one embodiment of the present invention, the wing assembly further includes at least one pair of balance components.

[0086] The balance components are arranged beside the wing, and the micro-vortices generated by the balance components can adjust and balance the wing.

[0087] The balance components can be arranged on the power device 3.

[0088] Each pair of the balance components is symmetrically arranged with respect to the axis of the power device 3.

[0089] Each pair of the wings 2 corresponds to a pair of the balance components.

[0090] The balance components can be rod-shaped, club-shaped, paddle-shaped, etc.

[0091] The balance components can be similar to the halteres of dipteran insects.

[0092] The balance components and the wing 2 are arranged on the power device 3 at intervals, and each pair of the balance components and its corresponding pair of the wings 2 are located on the same side.

[0093] In one embodiment of the present invention, the arrayed-wing flight device further includes a central control component, and the central control component controls the wing assembly.

[0094] The central control component can be arranged on the carrier 1 or not. The central control component can control the vibration of the wing assembly.

[0095] The central control unit is an integrated circuit that sensitively adjusts output voltage and current under computer program control. It includes one or more high-frequency inverters under program control to control individual or multiple circuits. The inverters convert low-voltage DC power from the power supply into high-frequency AC power. Pulse-width modulation (PWM) is a commonly used technique, with a PWM integrated controller at its core. The central control unit can be an inverter controlled by a TL5001 chip.

[0096] In one embodiment of the present invention, the array-type wing-wing flying device further includes a sensor, which measures the flight parameters of the array-type wing-wing flying device and sends the measured results to the central control component, which sends an execution command to the wing assembly according to preset rules.

[0097] The perception device may be a sensor.

[0098] The sensors may include three-axis velocity and three-axis acceleration sensors, vibration sensors, micro voltage and current sensors (used for feedback when local arrays are damaged), temperature sensors, air pressure sensors, etc.

[0099] The sensor can be set at any position of the carrier 1.

[0100] A plurality of sensors may be provided on the carrier 1 to make the parameters detected by the sensors more accurate. The sensors send the detected flight parameters of the flying device to the central control component so that the central control component can make accurate commands to the wing assembly.

[0101] In one embodiment of the present invention, the power device 3 is an electromagnetic motor.

[0102] In one embodiment of the present invention, the power device 3 includes:

[0103] A wing flapping power component, which is deformed when stimulated by external stimuli, thereby driving the wing 2 to flap up and down through its deformation;

[0104] The wing-changing power component deforms after being subjected to external stimulation. The deformation of the wing-changing power component applies force to a part of the wing-flapping power component in a direction perpendicular to the plane formed by the up and down flapping of the wing 2, thereby causing the wing-flapping power component to twist, thereby changing the flapping direction of the wing 2.

[0105] The wing flapping power component is subjected to external stimulation, and the external stimulation here can be electrical stimulation, light stimulation of intelligent photosensitive materials, temperature stimulation of temperature-sensitive materials, etc.

[0106] The wing flapping power component is connected to the wing 2. When the wing flapping power component is deformed by external stimuli, it drives the wing 2 to perform up and down flapping operations.

[0107] The wing direction-changing power component is subjected to external stimuli, where the external stimuli can be electrical stimuli, light stimuli of intelligent photosensitive materials, temperature stimuli of temperature-sensitive materials, etc.

[0108] The deformation direction of the wing direction-changing power component is perpendicular to the deformation direction of the wing flapping power component.

[0109] The wing direction-changing power component is connected to the wing flapping power component. When the wing direction-changing power component is deformed after being subjected to external stimuli, the connection between the wing flapping power component and the wing direction-changing power component will be subjected to the pulling force or pushing force of the wing direction-changing power component, thereby causing the wing flapping power component to be distorted, and further changing the flapping direction of the wing 2.

[0110] In an embodiment of the present invention, the power device 3 is a laminated composite structure. The power device 3 includes a first horizontally extending layer 7 and a second horizontally extending layer 8, and the first horizontally extending layer 7 and the second horizontally extending layer 8 are laminated together.

[0111] The wing root 4 is located between the first horizontally extending layer 7 and the second horizontally extending layer 8, and the two wing bodies in each pair of wings 2 are respectively located on opposite sides of the laminated composite structure.

[0112] At least one of the first horizontally extending layer 7 and the second horizontally extending layer 8 will contract / elongate in the lateral direction along both sides where the wing 2 is located when subjected to external stimuli, and the contraction rate / elongation rate is different under the same external stimuli.

[0113] The first horizontally extending layer 7 is fixedly connected to the second horizontally extending layer 8. The wing root 4 is connected to the first horizontally extending layer 7 and the second horizontally extending layer 8. When the first horizontally extending layer 7 and the second horizontally extending layer 8 are deformed under external stimuli (since the contraction rate / elongation rate of the first horizontally extending layer 7 and the second horizontally extending layer 8 is different, contraction / elongation will occur in the lateral direction along both sides where the wing 2 is located), the wing root 4 drives the wing body to vibrate, so that the device can fly.

[0114] In one embodiment of the present invention, the power device 3 further includes a first longitudinally extending layer and a second longitudinally extending layer. The first longitudinally extending layer is located outside the first laterally extending layer 7 and laminated and fixed to the first laterally extending layer 7. The second longitudinally extending layer is located outside the second laterally extending layer 8 and laminated and fixed to the second laterally extending layer 8.

[0115] The first longitudinally extending layer is composed of a first fixing portion 5 and a first extending portion 6. The first fixing portion 5 and the first extending portion 6 are arranged adjacent to each other on the surface of the first laterally extending layer 7.

[0116] The second longitudinally extending layer is composed of a second fixing portion 9 and a second extending portion 10. The second fixing portion 9 and the second extending portion 10 are arranged adjacent to each other on the surface of the second laterally extending layer 8.

[0117] Under external stimulation, the first extending portion 6 and the second extending portion 10 will contract / elongate in the longitudinal direction perpendicular to the lateral direction. Under the same external stimulation, the shrinkage / elongation rate of the first fixing portion 5 is less than that of the first extending portion 6 or the shrinkage / elongation rate is zero, and the shrinkage / elongation rate of the second fixing portion 9 is less than that of the second extending portion 10 or the shrinkage / elongation rate is zero.

[0118] In the longitudinal direction, the arrangement order of the first extending portion 6 and the first fixing portion 5 in the first longitudinally extending layer is opposite to the arrangement order of the second extending portion 10 and the second fixing portion 9 in the second longitudinally extending layer.

[0119] The first laterally extending layer 7, the second laterally extending layer 8, the first fixing portion 5, the first extending portion 6, the second fixing portion 9, and the second extending portion 10 can all be in a plate-like structure, preferably a cuboid plate-like structure.

[0120] The shrinkage / elongation rate of the first fixing portion 5 is less than the shrinkage / elongation rate of the first extending portion 6.

[0121] The shrinkage / elongation rate of the first fixing portion 5 can be zero.

[0122] The shrinkage / elongation rate of the second fixing portion 9 is less than the shrinkage / elongation rate of the second extending portion 10.

[0123] The shrinkage / elongation rate of the second fixing portion 9 can be zero.

[0124] In one embodiment of the present invention, the power device 3 includes:

[0125] The first housing 15, the first housing 15 is a curved surface structure, and the two opposite side ends of the curved surface structure of the first housing 15 are respectively connected to the ends of the wing root 4 to form a connecting shaft or a shaftless hinge, and the wing 2 can rotate relative to the first housing 15 around the connecting shaft or the shaftless hinge; that is, one end of the wing root 4 is movably connected to the first housing 15.

[0126] The second housing 16, the second housing 16 is a curved surface structure, and the two opposite side ends of the curved surface structure of the second housing 16 are respectively in contact with at least a part other than the end points of the wing root 4, and the inner side of the curved surface of the second housing 16 is arranged opposite to the inner side of the curved surface of the first housing 15 to form a power device cavity;

[0127] The other end of the wing root 4 is connected to the second housing 16.

[0128] Both the first housing 15 and the second housing 16 can be arc-shaped.

[0129] Both the first housing 15 and the second housing 16 can be made of elastic materials.

[0130] The first housing 15 and the second housing 16 can form a sealed or semi-sealed power device cavity.

[0131] The wing flapping power component 17, the wing flapping power component 17 is connected to the inner sides of the first housing 15 and the second housing 16. After being stimulated by the outside world, the wing flapping power component 17 undergoes deformation, so as to change the relative distance between the first housing 15 and the second housing 16 through its deformation. Under the action of the first housing 15 and the second housing 16 cooperating with each other to exert a force on the wing 2, the wing 2 makes an up-and-down flapping motion;

[0132] The wing flapping power component 17 can be made of an elastic material (the elastic material is the prior art, as long as it can realize its function in the present invention). When the wing flapping power component 17 is stimulated by the outside world, the wing flapping power component 17 undergoes deformation along the extension direction of the wing flapping power component 17 (that is, the wing flapping power component 17 expands and contracts along the extension direction of the wing flapping power component 17), so as to change the relative distance between the first housing 15 and the second housing 16, and further make the wing root 4 receive the pulling force or pushing force of the first housing 15 and the second housing 16, so that the wing 2 makes an up-and-down flapping motion.

[0133] The number of the wing flapping power components 17 can be one or more. The wing flapping power components 17 are preferably even in number, and the multiple wing flapping power components 17 are symmetrically arranged with respect to the central axis of the power device cavity.

[0134] The wing direction-changing power component 18 extends in the direction parallel to the curved surface structures of the first housing 15 and the second housing 16 within the power device cavity. The wing direction-changing power component 18 penetrates through the wing flapping power component 17 or adheres to the surface of the wing flapping power component 17 and is in close contact with the wing flapping power component 17. After being stimulated by the outside world, the wing direction-changing power component 18 undergoes deformation, and the deformation drives the part of the wing flapping power component 17 that is in contact with it, thereby causing the wing flapping power component 17 to be distorted, and further changing the flapping direction of the wing 2.

[0135] The wing direction-changing power component 18 can be made of an elastic material. The wing direction-changing power component 18 can be a regular three-dimensional structure or an irregular three-dimensional structure.

[0136] The number of the wing direction-changing power components 18 can be one or more, and the wing direction-changing power components 18 are preferably even in number.

[0137] The wing direction-changing power components 18 are preferably even in number, and multiple wing direction-changing power components 18 are symmetrically arranged with respect to the central axis of the power device cavity.

[0138] In an embodiment of the present invention, the outside stimulation is power-on. The first extension part 6, the first transverse extension layer 7, the second transverse extension layer 8, and the second extension part 10 are all connected to a power source through wires, and the central control component controls the expansion and contraction of the first extension part �, the first transverse extension layer 7, the second transverse extension layer 8, and the second extension part 10 respectively by controlling the power source.

[0139] After the first extension part 6 is powered on, the first extension part 6 can expand and contract in the direction away from / towards the first fixing part 5; after the second extension part 10 is powered on, the second extension part 10 can expand and contract in the direction away from / towards the second fixing part 9; the expansion and contraction direction of the first extension part 6 is opposite to the expansion and contraction direction of the second extension part 10.

[0140] After the first transverse extension layer 7 is powered on, the first transverse extension layer 7 can extend in the direction towards the wing 2; after the second transverse extension layer 8 is powered on, the second transverse extension layer 8 can extend in the direction towards the wing 2; the extension direction of the first transverse extension layer 7 is the same as the extension direction of the second extension part 10.

[0141] In one embodiment, the power device drives the wing through a lever, where one end of the lever is connected to the power device, the other end of the lever is connected to the wing, the fulcrum of the lever is arranged on the carrier, and the lever is connected to the fulcrum axially or non-axially. The power device controls the vibration or flapping of the wing through the lever principle.

[0142] In one embodiment of the present invention, each set of wing assemblies includes one or more pairs of axially symmetric wings 2, the wings 2 are of a two-layer or multi-layer laminated structure, and when the materials of each layer of the wings 2 are energized, they elongate in the direction away from the carrier 1, and the arrangement order of each layer is that the elongation length in the direction away from the carrier 1 increases after being energized.

[0143] The application of the arrayed wing flight device of the present invention in unmanned or manned aircraft, airplanes, or airships.

[0144] Example 1

[0145] As Figures 1-4 shown, the present invention provides an arrayed wing flight device, which includes: a carrier 1, two or more sets of wing assemblies arranged in an array on the carrier 1, a central control component, a sensor, and a power source. The wing assembly includes one or more pairs of wings 2 and at least one power device 3. The power device 3 is of a laminated composite structure, and the power device 3 includes a first longitudinally extending layer, a first laterally extending layer 7, a second laterally extending layer 8, and a second longitudinally extending layer that are stacked and connected in sequence from top to bottom;

[0146] The first longitudinally extending layer includes a first extending portion 6 and a first fixing portion 5, and the first extending portion 6 and the first fixing portion 5 are arranged side by side on the surface of the first laterally extending layer 7.

[0147] The second longitudinally extending layer includes a second extending portion 10 and a second fixing portion 9, and the second extending portion 10 and the second fixing portion 9 are arranged side by side on the surface of the second laterally extending layer 8.

[0148] The first laterally extending layer 7, the second laterally extending layer 8, the first fixing portion 5, the first extending portion 6, the second fixing portion 9, and the second extending portion 10 are all of a cuboid plate-like structure.

[0149] The first laterally extending layer 7 and the second laterally extending layer 8 are both connected to the wing root 4, and the two wing bodies in each pair of wings 2 are respectively located on opposite sides of the laminated composite structure.

[0150] The shrinkage / elongation rates of the first horizontally extending layer 7 and the second horizontally extending layer 8 are different. The shrinkage / elongation rate of the first extending portion 6 is greater than that of the first fixing portion 5, and the shrinkage / elongation rate of the second extending portion 10 is greater than that of the second fixing portion 9.

[0151] The sensor is disposed on the carrier 1 for measuring the flight parameters of the flying device and sending the flight parameters to the central control component, so that the central control component issues a preparation command to the power device 3.

[0152] When the arrayed wing flying device needs to fly, the central control component supplies power to the power device 3 by controlling the power supply. The first horizontally extending layer 7 and the second horizontally extending layer 8 in the power device 3 are subjected to electrical stimulation. The first horizontally extending layer 7 and the second horizontally extending layer 8 expand and contract in the direction close to the wing 2 (that is, due to the different shrinkage / elongation rates between the first horizontally extending layer 7 and the second horizontally extending layer 8, the first horizontally extending layer 7 and the second horizontally extending layer 8 will shrink / elongate in the lateral direction, i.e., on both sides where the wing 2 is located). The wing root 4 drives the wing body to vibrate, so that the device can fly.

[0153] When the flying device needs to turn, the central control component supplies power to the power device 3 by controlling the power supply. The first extending portion 6 is subjected to electrical stimulation, and the first extending portion 6 will expand and contract in the direction away from / towards the first fixing portion 5 (i.e., expand and contract in the longitudinal direction perpendicular to the lateral direction); the second extending portion 10 is subjected to electrical stimulation, and the second extending portion 10 will expand and contract in the direction away from / towards the second fixing portion 9 (i.e., expand and contract in the longitudinal direction perpendicular to the lateral direction); thereby driving the first horizontally extending layer 7 and the second horizontally extending layer 8 to undergo a torsional deformation, and further driving the flapping direction of the wing 2 to change, so as to achieve a change in the flight direction.

[0154] Embodiment 2

[0155] As Figure 5 shown, the present invention provides an arrayed wing flying device, and the difference between the arrayed wing flying device and the flying device in Embodiment 1 lies in the different structures of the power device 3.

[0156] The power device 3 includes two power components arranged in a stacked manner with the same structure. The power components include four steering power components arranged in a cross shape and four flapping power components. The adjacent steering power components are connected by the flapping power components, and a regular octagonal prism plate-like structure is formed between the four steering power components and the four flapping power components (the steering power components are square plate-like structures, and the flapping power components are pentagonal plate-like structures).

[0157] A pair of wing fins 2 are provided at the connection of the two power components, and the two wing fins 2 are respectively provided on the sides of the two relatively arranged power flapping components (that is, each pair of wing fins 2 is symmetrically arranged with respect to the power device 3).

[0158] The four steering power components in the power component are respectively connected to the power supply through wires, so that the four steering power components are independent of each other and do not affect each other. When each steering power component is powered on, it can contract independently. The flapping power component is deformed by the expansion and contraction of the steering power component, so as to drive the wing fin 2 to flap and operate.

[0159] When the flying device needs to fly, the four steering power components on the upper layer can expand and contract simultaneously, and the four steering power components on the lower layer can also expand and contract simultaneously. In this way, the four steering power components on the upper layer and the four steering power components on the lower layer expand and contract alternately, which will cause the upper and lower alternating movements of the roots 4 of the two wing fins.

[0160] Each pair of wing fins 2 includes a first wing fin 19 and a first wing fin 20.

[0161] The four steering power components on the upper layer are respectively the a steering power component 11, the b steering power component 12, the c steering power component 13, and the d steering power component 14 in the clockwise direction. The first wing fin 19 is connected to the flapping power component between the a steering power component 11 and the d steering power component 14, and the first wing fin 20 is connected to the flapping power component between the b steering power component 12 and the c steering power component 13.

[0162] The four variable-direction power components of the lower layer are, in clockwise order, the A variable-direction power component, the B variable-direction power component, the C variable-direction power component, and the D variable-direction power component. The first wing 19 is connected to the flapping power component between the A variable-direction power component and the D variable-direction power component, and the first wing 20 is connected to the flapping power component between the B variable-direction power component and the C variable-direction power component. The a variable-direction power component 11 corresponds to the A variable-direction power component vertically, the b variable-direction power component 12 corresponds to the B variable-direction power component vertically, the c variable-direction power component 13 corresponds to the C variable-direction power component vertically, and the d variable-direction power component 14 corresponds to the D variable-direction power component vertically.

[0163] When the a variable-direction power component 11 and the A variable-direction power component expand and contract simultaneously, it can cause the first wing 19 to move forward; when the d variable-direction power component 14 and the D variable-direction power component expand and contract simultaneously, it can cause the first wing 19 to move backward. When the b variable-direction power component 12 and the B variable-direction power component expand and contract simultaneously, it can cause the first wing 20 to move forward; when the c variable-direction power component 13 and the C variable-direction power component expand and contract simultaneously, it can cause the first wing 20 to move backward.

[0164] When the a variable-direction power component 11 and the D variable-direction power component expand and contract simultaneously, it can cause the first wing 19 to twist in the clockwise direction; when the A variable-direction power component and the d variable-direction power component 14 expand and contract simultaneously, it can cause the first wing 19 to twist in the counterclockwise direction. The same applies to the first wing 20.

[0165] Embodiment 3

[0166] As Figure 6 and Figure 7 shown, the present invention provides an arrayed-wing flight device. The difference between the arrayed-wing flight device and the flight device in Embodiment 1 lies in the structure of the power device 3.

[0167] The power device 3 includes:

[0168] A first housing 15 and a second housing 16. Both the first housing 15 and the second housing 16 are curved surface structures. The two opposite side ends of the curved surface structure of the first housing 15 are respectively movably connected to the ends of the wing root 4, that is, one end of the wing root 4 is movably connected to the first housing 15. The two opposite side ends of the second housing 16 are respectively connected to the other end of the wing root 4. The inner side of the curved surface of the second housing 16 is arranged opposite to the inner side of the curved surface of the first housing 15 to form a closed cavity of the power device 3;

[0169] Inside the power device cavity, there is a wing flapping power component 17, and the wing flapping power component 17 connects the inner sides of the first housing 15 and the second housing 16. After being stimulated by the outside world, the wing flapping power component 17 undergoes deformation, thereby driving a change in the relative distance between the first housing 15 and the second housing 16 through its deformation. Under the action of the first housing 15 and the second housing 16 cooperating with each other to exert a force on the wing 2, the wing 2 makes an up-and-down flapping motion;

[0170] The number of the wing flapping power components 17 is two, and the two wing flapping power components 17 are symmetrically arranged with respect to the central axis of the power device cavity.

[0171] Inside the power device cavity, there is also a wing direction-changing power component 18. The wing direction-changing power component 18 extends in the power device cavity in a direction parallel to the curved surface structures of the first housing 15 and the second housing 16. The wing direction-changing power component 18 penetrates through the wing flapping power component 17 or adheres to the surface of the wing flapping power component 17 and is in close contact with the wing flapping power component 17. After being stimulated by the outside world, the wing direction-changing power component 18 undergoes deformation, and the deformation drives the part of the wing flapping power component 17 that is in contact with it, thereby causing the wing flapping power component 17 to be distorted, and further changing the flapping direction of the wing 2.

[0172] The number of the wing direction-changing power components 18 is two, and the two wing direction-changing power components 18 are symmetrically arranged with respect to the central axis of the power device cavity.

[0173] When the flying device needs to fly, after the wing flapping power component 17 is stimulated by the outside world, the wing flapping power component 17 undergoes deformation along the extension direction of the wing flapping power component 17 (that is, the wing flapping power component 17 expands and contracts along the extension direction of the wing flapping power component 17), thereby driving a change in the relative distance between the first housing 15 and the second housing 16, and further causing the wing root 4 to be subjected to the pulling force or pushing force of the first housing 15 and the second housing 16, so that the wing 2 makes an up-and-down flapping motion. When the flying direction of the flying device needs to be changed, after the wing direction-changing power component 18 is stimulated by the outside world, the wing direction-changing power component 18 undergoes deformation, and the deformation drives the part of the wing flapping power component 17 that is in contact with it, thereby causing the wing flapping power component 17 to be distorted, and further changing the flapping direction of the wing.

[0174] Although the embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the above specific embodiments and application fields. The above specific embodiments are merely illustrative and guiding, rather than restrictive. Those of ordinary skill in the art can also make many forms under the inspiration of this specification and without departing from the scope protected by the claims of the present invention, and these all fall within the scope of protection of the present invention.

Claims

1. An array-type wing-shaped flying device, characterized in that: The array wing-shaped flying device comprises: carrier; Two or more groups of wing assemblies arranged in an array on the carrier; Each set of the wing assemblies comprises one or more pairs of wings and at least one power device, wherein the power device provides power for the wings; Each wing comprises a wing root and a wing body, wherein the wing root is connected to a power device, and the wing root drives the wing body to move; The power device is a layered composite structure, comprising a first transverse extension layer and a second transverse extension layer, wherein the first transverse extension layer and the second transverse extension layer are laminated together. The wing root is located between the first transverse extension layer and the second transverse extension layer, and the two wing bodies in each pair of wings are located on opposite sides of the layered composite structure. At least one of the first transverse extension layer and the second transverse extension layer will shrink / stretch along the two sides of the wing, i.e., in the transverse direction, under external stimulation; The power device further includes a first longitudinal extension layer and a second longitudinal extension layer, wherein the first longitudinal extension layer is located outside the first transverse extension layer and is laminated and fixed to the first transverse extension layer, and the second longitudinal extension layer is located outside the second transverse extension layer and is laminated and fixed to the second transverse extension layer. The first longitudinal extension layer is composed of a first fixing portion and a first extension portion, and the first fixing portion and the first extension portion are arranged adjacent to each other on the surface of the first transverse extension layer. The second longitudinal extension layer is composed of a second fixing portion and a second extension portion, and the second fixing portion and the second extension portion are arranged adjacent to each other on the surface of the second transverse extension layer. Under external stimulation, the first extension portion and the second extension portion will shrink / stretch in the longitudinal direction perpendicular to the transverse direction. In the longitudinal direction, the arrangement order of the first extending portions and the first fixing portions in the first longitudinally extending layer is opposite to the arrangement order of the second extending portions and the second fixing portions in the second longitudinally extending layer.

2. The array wing flying device according to claim 1, characterized in that: The carrier is a frame structure, and wing assemblies are provided on at least two nodes of the frame structure.

3. The array wing flying device according to claim 2, characterized in that: The carrier is a planar frame structure.

4. The array wing flying device according to claim 2, characterized in that: The carrier is a three-dimensional frame structure.

5. The array-type wing-shaped flying device according to any one of claims 2 to 4, characterized in that: The frame structure has a folded state and an unfolded state.

6. The array wing flying device according to claim 5, characterized in that: The folded state and the unfolded state of the frame structure are convertible into each other.

7. The array wing flying device according to claim 1, characterized in that: Each pair of wings is arranged parallel to each other.

8. The array wing flying device according to claim 1, characterized in that: The wings are of layered structure.

9. The array wing flying device according to claim 1, characterized in that: The wings are flexible layered structures.

10. The array wing flying device according to claim 1, characterized in that: The wing is a hard layered structure.

11. The array wing flying device according to claim 1, characterized in that: The wings are composed of hard wing veins and soft wing leaves.

12. The array wing flying device according to claim 1, characterized in that: The wing assembly also includes at least one pair of balancing components.

13. The array wing flying device according to claim 12, characterized in that: The balancing component is arranged beside the wing, and the balancing component adjusts the micro vortex generated by the wing.

14. The array wing flying device according to claim 1, characterized in that: The array-type wing-wing flying device further includes a central control component, which controls the wing-wing assembly.

15. The array wing flying device according to claim 14, characterized in that: The array-type wing-wing flying device also includes a sensor, which measures the flight parameters of the array-type wing-wing flying device and sends the measured results to the central control component. The central control component sends an execution command to the wing assembly according to preset rules.

16. The array-type wing-shaped flying device according to claim 1, characterized in that: The power device is an electromagnetic motor.

17. The array wing flying device according to claim 1, characterized in that: The first extension part, the first lateral extension layer, the second lateral extension layer and the second extension part are all connected to a power source through wires, and the central control component controls the expansion and contraction of the first extension part, the first lateral extension layer, the second lateral extension layer and the second extension part respectively by controlling the power source.

18. The array wing flying device according to claim 1, characterized in that: Each group of wing assemblies includes one or more pairs of axisymmetric wings, and the wings are a two-layer or multi-layered structure. After power is applied to each layer of the wing material, it stretches in the direction away from the carrier, and the order of arrangement of each layer is that the length of the stretching in the direction away from the carrier increases after power is applied.

19. Use of the array-type wing-flying device according to any one of claims 1 to 18 in an unmanned or manned aircraft, airplane, or airship.

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