CN211468771U - Array wing flight device - Google Patents
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- CN211468771U CN211468771U CN201922064156.7U CN201922064156U CN211468771U CN 211468771 U CN211468771 U CN 211468771U CN 201922064156 U CN201922064156 U CN 201922064156U CN 211468771 U CN211468771 U CN 211468771U
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Abstract
The utility model discloses an array wing flight device, array wing flight device includes: a carrier; more than two groups of wing assemblies are arrayed on the carrier. The utility model provides an array wing flying device, with the wing subassembly of numerous small-size vibrations, combine a two-dimentional or three-dimensional latticed carrier in, form a novel flight power pack that can regulate and control. The power device can be applied to unmanned or manned aircrafts, and high-efficiency and high-flexibility flight is realized.
Description
Technical Field
The utility model relates to a miniature bionical flying device technical field, concretely relates to array wing flying device.
Background
Insects have evolved the most efficient and successful flight patterns on earth over hundreds of millions of years of evolution. Taking flies as an example, the power of over ten times of the self-weight-pushing ratio can be generated by extremely thin wings. Human aircrafts are currently also at risk. Even birds are not comparable. And many insects such as bees can hover in the air for a long time, and the insects carry only little biomass energy, so that the flying energy consumption ratio is low. In addition, the flying of insects such as flies is very flexible, rapid air steering can be realized, and no artificial aircraft or even birds can be compared at present.
At present, the artificial aircrafts utilizing aerodynamic force mainly comprise two main types, namely fixed wings and rotary wings. Research shows that the flying principle of the fly is different from the flying principle of the artificial aircraft and the flying principle of birds. The fly can fly, and the micro air vortex generated by the high-frequency vibration of the membrane fin is skillfully utilized. This is a very efficient flight mode, and the generation of these micro-vortices is closely related to the form and size of the wing.
At present, the single insect flying is simulated, but the aim is not to simply expand the size and become a universal flying power engine. Therefore, designing a flying device which can effectively utilize the high-efficiency flying mode of insects and can copy and expand the scale without limit is one of the problems to be solved in the field of flying device design.
SUMMERY OF THE UTILITY MODEL
In view of this, the present invention provides an array type wing flying device, which combines a plurality of small vibrating wing assemblies into a two-dimensional or three-dimensional grid carrier to form a controllable novel flying power unit. The power device can be applied to unmanned or manned aircrafts, and high-efficiency and high-flexibility flight is realized.
To achieve the above object, according to one aspect of the present invention, there is provided an array type wing flight device.
An array wing flight device, array wing flight device include:
a carrier;
more than two groups of wing assemblies are arrayed on the carrier.
In one embodiment, the carrier is a framework structure having wing assemblies disposed on at least two nodes of the framework structure.
In one embodiment, the carrier is a planar frame structure.
In one embodiment, the carrier is a three-dimensional frame structure.
In one embodiment, the frame structure has a collapsed state and an expanded state.
In one embodiment, the collapsed state and the expanded state of the frame structure are transformable into each other.
In one embodiment, each set of said wing assemblies comprises one or more pairs of wings and at least one power plant which powers said wings.
In one embodiment, each pair of said wings are arranged parallel to each other.
In one embodiment, each of the wings comprises a wing root and a wing body, the wing root is connected with a power device, and the wing root drives the wing body to move.
In one embodiment, the wing is a laminated structure.
In one embodiment, the wing is a flexible laminate structure.
In one embodiment, the wing is a rigid laminar structure.
In one embodiment, the winglets are comprised of a rigid wing vein and flexible wing leaves.
In one embodiment, the wing assembly further comprises at least one pair of balancing members.
In one embodiment, the balancing member is disposed adjacent to the wing, and the balancing member adjusts the micro eddy current generated by the wing.
In one embodiment, the arrayed wing flight device further comprises a central control component that controls the wing assembly.
In one embodiment, the array-type wing flight device further comprises a sensor, the sensor measures flight parameters of the array-type wing flight device and sends the measured results to the central control unit, and the central control unit sends execution commands to the wing assemblies according to preset rules.
In one embodiment, the power plant is an electromagnetic motor.
In one embodiment, the power plant comprises:
the wing flapping power component deforms after being stimulated by the outside, so that the wing is driven to flap up and down through the deformation of the wing flapping power component;
the wing turning power component deforms after being stimulated by the outside, and the deformation of the wing turning power component applies force to one part of the wing flapping power component in the direction perpendicular to the plane formed by flapping the wing up and down, so that the wing flapping power component is twisted, and the flapping direction of the wing changes.
In one embodiment, the power plant is a layered composite structure comprising a first laterally extending layer and a second laterally extending layer laminated together,
the wing roots are located between the first laterally extending layer and the second laterally extending layer, the two wing bodies of each pair of wing are located on opposite sides of a laminar composite structure,
at least one of the first transversely extending layer and the second transversely extending layer contracts/elongates in the lateral direction of the wing, i.e. in the transverse direction, when subjected to an external stimulus, and the contraction rates/elongations are different when subjected to the same external stimulus.
In one embodiment, the power plant further comprises a first longitudinally extending layer laminated and secured to the first laterally extending layer outboard of the first laterally extending layer, and a second longitudinally extending layer laminated and secured to the second laterally extending layer outboard of the second laterally extending layer,
the first longitudinal extension layer is composed of a first fixing part and a first extension part which are adjacently arranged on the surface of the first transverse extension layer,
the second longitudinal extension layer is composed of a second fixed part and a second extension part which are adjacently arranged on the surface of the second transverse extension layer,
under the external stimulus, the first extension part and the second extension part can contract/extend in the direction vertical to the transverse direction, namely the longitudinal direction, under the same external stimulus, the shrinkage rate/elongation of the first fixing part is smaller than that of the first extension part or the shrinkage rate/elongation is zero, the shrinkage rate/elongation of the second fixing part is smaller than that of the second extension part or the shrinkage rate/elongation is zero,
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.
In one embodiment, the power plant comprises:
the wing comprises a first shell, a second shell and a wing body, wherein the first shell is of a curved surface structure, two opposite side ends of the curved surface structure of the first shell are respectively connected with the end parts of the roots of the wings to form a connecting shaft or a shaftless hinge, and the wings can rotate around the connecting shaft or the shaftless hinge relative to the first shell;
the two opposite side ends of the curved surface structure of the second shell are respectively contacted with at least one part except the root end points of the wing, and the inner side of the curved surface of the second shell and the inner side of the curved surface of the first shell are oppositely arranged to form a cavity of the power device;
the wing flapping power component is connected with the inner side of the first shell and the inner side of the second shell, and deforms after being stimulated by the outside, so that the relative distance between the first shell and the second shell is driven to change through the deformation of the wing flapping power component, and the wing does up-and-down flapping motion under the action of force exerted on the wing by the mutual matching of the first shell and the second shell;
wing diversion power pack, wing diversion power pack extends in the direction that is on a parallel with first shell curved surface structure and second shell curved surface structure in the power device cavity, wing diversion power pack run through in among the wing patting power pack or be attached to wing patting power pack surface, and with wing patting power pack closely laminates, wing diversion power pack takes place deformation after receiving external stimulus, deformation drives the wing and patts the part rather than the laminating on the power pack, thereby makes wing patting power pack takes place the distortion, and then makes the direction of patting of wing change.
In one embodiment, the power device drives the wing through a lever, wherein one end of the lever is connected with the power device, the other end of the lever is connected with the wing, a fulcrum of the lever is arranged on the carrier, and the lever is axially or non-axially connected with the fulcrum.
In one embodiment, the external stimulus is an electrical stimulus.
In one embodiment, the first extension portion, the first laterally extending layer, the second laterally extending layer and the second extension portion are all connected with a power supply through wires, and the central control component controls the extension and retraction of the first extension portion, the first laterally extending layer, the second laterally extending layer and the second extension portion through the control power supply.
In one embodiment, each said wing assembly comprises one or more pairs of axisymmetric wings, said wings being in a two-or multi-layer laminate structure, the layers of material of said wings extending in a direction away from the carrier upon application of current thereto, the layers being arranged in an order such that the length of extension in the direction away from the carrier increases upon application of current thereto.
The utility model discloses array wing flight device is in unmanned or manned aircraft, or the application of dirigible. And may be used in combination with various other existing flight power devices.
According to the utility model provides an array wing flying device compares existing flight power device (engine)'s advantage and lies in: first, it is more efficient because the way insects fly has proven to be the most efficient mode at present. The second direction change is more flexible, and the wing fins of the whole wing array can realize instantaneous simultaneous steering under the control of the central control component. The third is lighter because compare in traditional engine metal parts and give first place to, the utility model discloses the device uses macromolecular material to give first place to. The fourth can be deformed and unfolded when in use or folded when not in use. The fifth pair of localized damages/failures is more tolerant. Few components of the existing engine are damaged, so that air crash can be caused, and even a small part of the wing array is damaged/failed, the whole system is not crashed.
According to the utility model provides an array wing flight device, with the wing subassembly of numerous small-size vibrations, combine a two-dimentional or three-dimensional latticed carrier in, form a novel flight power pack that can regulate and control. And a plurality of the wing assemblies are independent and do not interfere with each other, so that the normal operation of other wing assemblies cannot be influenced even if part of the wing assemblies are damaged, the safety is higher, and the high-efficiency and high-flexibility flight is realized.
Drawings
The accompanying drawings are included to provide a better understanding of the present invention and are not intended to constitute an undue limitation on the invention. Wherein:
FIG. 1 is one of the schematic structural views of an arrayed wing flight device according to the present invention;
fig. 2 is a second schematic structural diagram of the arrayed wing flying device according to the present invention;
fig. 3 is a third schematic structural diagram of the array-type wing flying device according to the present invention;
FIG. 4 is a schematic view of a power plant according to the present invention;
figure 5 is one of the schematic views of a wing assembly according to the present invention;
figure 6 is a second schematic view of a wing assembly according to the present invention;
figure 7 is a third schematic view of a wing assembly according to the present invention.
List of reference numerals
The wing-flapping-wing power device comprises a carrier 1, a wing 2, a wing 3, a power device 4, a wing root 5, a first fixing part 6, a first extending part 7, a first transverse extending layer 8, a second transverse extending layer 9, a second fixing part 10, a second extending part 11, a direction-changing power part 12, a direction-changing power part 13, a direction-changing power part 14, a first shell 15, a second shell 16, a wing flapping power part 17, a wing direction-changing power part 18, a first wing 19 and a first wing 20.
Detailed Description
Exemplary embodiments of the invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered exemplary only. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.
The utility model relates to an array wing flight device, array wing flight device includes:
a carrier 1;
more than two groups of wing assemblies are arranged in an array on the carrier 1.
The carrier 1 has the functions of power balance and power transmission so as to realize power supply and control and form an integral structure. The carrier 1 may also be provided with directional adjustment (by turning the carrier 1 instead of the wings).
The carrier 1 may also be of a folded configuration, which may be folded to reduce bulk when the heeling apparatus is in the non-heeled condition for storage. The carrier 1 is also provided with extremely fine wires for connecting a power supply and a power device 3.
The wing assemblies on the carrier 1 are mutually independent and do not influence each other. A plurality of said wing assemblies may be arranged in parallel spaced apart relationship.
In one embodiment of the present invention, the carrier 1 is a frame structure, and wing assemblies are disposed on at least two nodes of the frame structure.
The carrier 1 may be a planar frame structure. Further, the carrier 1 may also be a planar net structure, and further, the carrier 1 may be a planar foldable net structure.
The carrier 1 may be a space frame structure. The carrier 1 can be a three-dimensional geometrical structure such as a cubic mesh structure, a polygonal prism mesh structure and the like.
In one embodiment of the present invention, the frame structure has a collapsed state and an expanded state. The folded state and the unfolded state of the frame structure can be mutually converted. When the flying device is in a flying state, the frame structure is in an unfolded state, and when the flying device stops running, the frame structure is in a folded state so as to be convenient to store and reduce the occupied space.
In one embodiment of the present invention, each set of said wing assemblies comprises one or more pairs of wings 2 and at least one power means 3, said power means 3 powering said wings 2.
Each pair of the wings 2 is arranged in an axisymmetric manner by taking the power device 3 as an axis, the power device 3 is arranged between each pair of the wings 2, and each pair of the wings 2 is connected with the power device 3.
As shown in fig. 1 and 2, each of the power units 3 may be connected to a pair of wings 2, or may be connected to a plurality of pairs of wings 2. When the power device 3 is connected with a plurality of pairs of wings 2, the power device 3 respectively provides power for each pair of wings 2, so that each pair of wings 2 are independent and do not influence each other.
The power device 3 can provide power for the wing 2, so that the wing 2 can vibrate, and the flying device flies.
In one embodiment of the present invention, each pair of the wing members 2 are disposed in parallel with each other, so that each pair of the wing members 2 do not affect each other when flying.
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 wing body 2 to move.
The wing body can be in a fan-shaped sheet shape, an oval sheet shape and other arc-shaped and polygonal sheet structures.
The winged fin body can also be of a feather-like structure.
The wing body and the wing root 4 are integrally formed.
In one embodiment of the present invention, the wing 2 is a laminated structure.
The wing 2 may have a single-layer structure or a multi-layer structure.
In one embodiment of the present invention, the wing 2 is a flexible layered structure, and the wing 2 may be made of one or more of nylon, thermoplastic polyurethane elastomer rubber (TPU), and the like.
In one embodiment of the present invention, the wing 2 is a hard layered structure, and the wing 2 may be made of one or more materials such as polyvinyl chloride (PVC), polypropylene (PP), etc.
In one embodiment of the present invention, the wing 2 is composed of a hard wing and a soft wing, the wing may be composed of one or more of titanium alloy, acrylonitrile-butadiene-styrene (ABS) and electro-active material, and the wing may be composed of one or more of nylon polyethylene, polypropylene and electro-active material.
In one embodiment of the invention, the wing assembly further comprises at least one pair of balancing members.
The balance component is arranged beside the wing, and can adjust and balance the micro eddy generated by the wing.
The balance member may be provided on the power unit 3.
Each pair of the balance parts is arranged with the power device 3 as an axis symmetry.
Each pair of the wing members 2 corresponds to a pair of the balance members.
The balance member may be in the form of a bar, a mallet, a paddle, or the like.
The balancing member may be a balancing bar resembling a dipteran insect.
The balance members are arranged on the power device 3 at intervals with the wing fins 2, and each pair of the balance members and the corresponding pair of the wing fins 2 are positioned on the same side.
In one embodiment of the present invention, the array-type wing flight device further comprises a central control unit, and the central control unit controls the wing assembly.
The central control unit may be disposed on the carrier 1 or not disposed on the carrier 1, and the central control unit may control the vibration of the wing assembly.
The central control component is an integrated block which realizes sensitive regulation of output voltage and current under the control of a computer program. The central control component comprises one or more high-frequency inverters under program control to respectively control one or more circuits, and the inverters can convert direct-current low-voltage electricity of the power supply into high-frequency alternating current electricity. The adopted technology is Pulse Width Modulation (PWM), and the core of the technology is a PWM integrated controller. The central control component can be an inverter controlled by a TL5001 chip.
The utility model discloses an in an embodiment, array wing flight device still includes the perceptron, the perceptron measures array wing flight device's flight parameter to with the result send that records to well accuse part, well accuse part is right according to presetting the rule wing subassembly sends the execution command.
The sensor may be a sensor.
The sensors can be triaxial speed and acceleration sensors, vibration sensors, micro voltage and current sensors (used for feedback when the local array is damaged), temperature sensors, air pressure sensors and the like.
The sensor may be arranged at any position of the carrier 1.
A plurality of sensors can be arranged on the carrier 1 so as to enable parameters detected by the sensors to be more accurate, and the sensors send detected flight parameters of the flight device to the central control component so that the central control component can make accurate commands to the wing assembly.
In an embodiment of the present invention, the power device 3 is an electromagnetic motor.
In an embodiment of the present invention, the power unit 3 includes:
the wing flapping power component deforms after being stimulated by the outside, so that the wing 2 is driven to flap up and down through the deformation of the wing flapping power component;
the wing turning power component deforms after being stimulated by the outside, and the deformation of the wing turning power component applies force to one part of the wing flapping power component in the direction perpendicular to the plane formed by flapping the wing 2 up and down, so that the wing flapping power component is twisted, and the flapping direction of the wing 2 is changed.
The wing flapping power component is stimulated by the outside, and the outside stimulation can be electric stimulation, light stimulation of an intelligent photosensitive material, temperature stimulation of a temperature-sensitive material and the like.
The wing flapping power component is connected with the wing 2, and when the wing flapping power component is stimulated by the outside to deform, the wing flapping power component drives the wing 2 to flap up and down.
The wing turning power component is stimulated by the outside, and the outside stimulation can be electric stimulation, light stimulation of an intelligent photosensitive material, temperature stimulation of a temperature-sensitive material and the like.
The deformation direction of the wing turning power component is perpendicular to the deformation direction of the wing flapping power component.
The wing turning power component is connected with the wing flapping power component, and when the wing turning power component deforms after being stimulated by the outside, the connection position of the wing flapping power component and the wing turning power component can be subjected to the pulling force or the pushing force of the wing turning power component, so that the wing flapping power component is twisted, and the flapping direction of the wing 2 is changed.
In one embodiment of the present invention, the power unit 3 is a laminated composite structure, the power unit 3 comprises a first transversely extending layer 7 and a second transversely extending layer 8, the first transversely extending layer 7 and the second transversely extending layer 8 are laminated together,
the wing roots 4 are located between the first and second laterally extending layers 7, 8, the two wing bodies of each pair of wings 2 being located on opposite sides of a laminar composite structure,
at least one of the first laterally extending layer 7 and the second laterally extending layer 8 contracts/elongates in both lateral directions, i.e. in the lateral direction, in which the wing 2 is located, when subjected to an external stimulus, and the contraction/elongation rates are different when subjected to the same external stimulus.
The first transverse extension layer 7 is fixedly connected with the second transverse extension layer 8, the wing root portion 4 is connected with the first transverse extension layer 7 and the second transverse extension layer 8, when the first transverse extension layer 7 and the second transverse extension layer 8 deform under external stimulation (due to different shrinkage/elongation rates of the first transverse extension layer 7 and the second transverse extension layer 8, the wing root portion 4 drives the wing body to vibrate along the directions of two sides where the wing 2 is located, namely, the transverse direction), and therefore the device can fly.
In one embodiment of the present invention, the power unit 3 further comprises a first longitudinally extending layer and a second longitudinally extending layer, the first longitudinally extending layer is located outside the first transversely extending layer 7 and is laminated and fixed with the first transversely extending layer 7, the second longitudinally extending layer is located outside the second transversely extending layer 8 and is laminated and fixed with the second transversely extending layer 8,
the first longitudinal extension layer is composed of a first fixed part 5 and a first extension part 6, the first fixed part 5 and the first extension part 6 are adjacently arranged on the surface of a first transverse extension layer 7,
the second longitudinally extending layer is composed of a second fixed part 9 and a second extending part 10, the second fixed part 9 and the second extending part 10 are adjacently arranged on the surface of the second transversely extending layer 8,
under the external stimulus, the first extending portion 6 and the second extending portion 10 contract/extend in the direction perpendicular to the transverse direction, i.e. the longitudinal direction, under the same external stimulus, the first fixing portion 5 has a shrinkage/extension rate smaller than that of the first extending portion 6 or a shrinkage/extension rate of zero, the second fixing portion 9 has a shrinkage/extension rate smaller than that of the second extending portion 10 or a shrinkage/extension rate of zero,
in the longitudinal direction, the order of arrangement of the first extending portions 6 and the first anchoring portions 5 in the first longitudinally extending layer is opposite to the order of arrangement of the second extending portions 10 and the second anchoring portions 9 in the second longitudinally extending layer.
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 may each be a plate-like structure, preferably a rectangular parallelepiped plate-like structure.
The contraction rate/elongation of the first fixing portion 5 is smaller than that of the first extending portion 6.
The shrinkage/elongation of the first fixing portion 5 may be zero.
The contraction rate/elongation of the second fixing portion 9 is smaller than that of the second extending portion 10.
The shrinkage/elongation of the second fixing portion 9 may be zero.
In an embodiment of the present invention, the power unit 3 includes:
the first shell 15 is of a curved surface structure, two opposite side ends of the curved surface structure of the first shell 15 are respectively connected with the end parts of the wing roots 4 to form a connecting shaft or a shaftless hinge, and the wing 2 can rotate around the connecting shaft or the shaftless hinge relative to the first shell 15; namely, one end of the wing root 4 is movably connected with the first shell 15.
The second shell 16 is a curved surface structure, two opposite side ends of the curved surface structure of the second shell 16 are respectively contacted with at least one part except the endpoint of the wing root 4, and the inner side of the curved surface of the second shell 16 is opposite to the inner side of the curved surface of the first shell 15 to form a power device cavity;
the other end of the wing root 4 is connected with the second housing 16.
The first housing 15 and the second housing 16 may have an arc shape.
The first housing 15 and the second housing 16 may be made of an elastic material.
The first housing 15 and the second housing 16 may form an enclosed or semi-enclosed power plant cavity.
The wing flapping power component 17 is connected with the inner side of the first shell 15 and the inner side of the second shell 16, the wing flapping power component 17 deforms after being stimulated by the outside, so that the relative distance between the first shell 15 and the second shell 16 is driven to change through the deformation of the wing flapping power component 17, and the wing 2 does up-and-down flapping motion under the action of force exerted on the wing 2 by the mutual matching of the first shell 15 and the second shell 16;
wing patting power component 17 can be made by elastic material (elastic material is prior art, as long as can realize that it is in the utility model provides an effect can), work as wing patting power component 17 receives external stimulus after, wing patting power component 17 follows wing patting power component 17's extending direction takes place deformation (promptly wing patting power component 17 follows the extending direction that power component 17 was patted to the wing rises and contracts), thereby drives first shell 15 and second shell 16 relative distance change, and then make wing root 4 receives first shell 15 with the pulling force or the thrust of second shell 16 make wing 2 does the up-and-down motion of patting.
The number of the wing flapping power components 17 can be one or multiple, the wing flapping power components 17 are preferably even, and the wing flapping power components 17 are symmetrically arranged around the central axis of the cavity of the power device.
A wing turning power component 18, the wing turning power component 18 extends in the direction parallel to the curved surface structure of the first shell 15 and the curved surface structure of the second shell 16 in the cavity of the power device, the wing turning power component 18 runs through the wing flapping power component 17 or is attached to the surface of the wing flapping power component 17, and is tightly attached to the wing flapping power component 17, the wing turning power component 18 deforms after being stimulated by the outside, and the deformation drives the part of the wing flapping power component 17 attached to the wing flapping power component 17, so that the wing flapping power component 17 is twisted, and the flapping direction of the wing 2 is changed.
The wing direction-changing power component 18 may be made of an elastic material, and the wing direction-changing power component 18 may have a regular three-dimensional structure or an irregular three-dimensional structure.
The number of the wing direction changing power parts 18 can be one or more, and the wing direction changing power parts 18 are preferably even number.
The number of the wing direction changing power parts 18 is preferably even, and the plurality of wing direction changing power parts 18 are symmetrically arranged on the central axis of the cavity of the power device.
In one embodiment of the present invention, the external stimulus 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 with a power supply through wires, and the central control part controls the extension and retraction of the first extension part 6, the first transverse extension layer 7, the second transverse extension layer 8 and the second extension part 10 through the control power supply.
After the first extending part 6 is powered on, the first extending part 6 can extend and contract along the direction far away from/close to the first fixing part 5; after the second extending portion 10 is powered on, the second extending portion 10 can extend and contract along a direction away from/close to the second fixing portion 9; the first extension 6 is extended and retracted in the opposite direction to the second extension 10.
After the first laterally extending layer 7 is powered on, the first laterally extending layer 7 may extend in a direction close to the wing 2; after the second laterally-extending layer 8 is powered on, the second laterally-extending layer 8 may extend in a direction close to the wing 2; the first laterally extending layer 7 is aligned with the direction in which the second extension 10 extends.
In one embodiment, the power device drives the wing through a lever, wherein one end of the lever is connected with the power device, the other end of the lever is connected with the wing, a fulcrum of the lever is arranged on the carrier, and the lever is axially or non-axially connected with the fulcrum. The power device controls the vibration or beating of the wing through a lever principle.
In one embodiment of the present invention, each of the wing assemblies comprises one or more pairs of axisymmetric wings 2, the wings 2 are two-layer or multi-layer layered structures, each layer of the material of the wings 2 extends in the direction away from the carrier 1 after being electrified, and the extending length of each layer increases in the direction away from the carrier 1 after being electrified.
The utility model discloses array wing flight device is in unmanned or manned aircraft, or the application of dirigible.
Example 1
As shown in fig. 1-4, the utility model provides an array type wing flying device, array type wing flying device includes: the wing assembly comprises a carrier 1, more than two groups of wing assemblies, a central control unit, a sensor and a power supply, wherein the wing assemblies are arranged on the carrier 1 in an array mode, each wing assembly comprises one or more pairs of wings 2 and at least one power device 3, each power device 3 is of a layered composite structure, and each power device 3 comprises a first longitudinally extending layer, a first transversely extending layer 7, a second transversely extending layer 8 and a second longitudinally extending layer which are sequentially connected in a stacked mode from top to bottom;
the first longitudinally extending layer comprises a first extending part 6 and a first fixing part 5, and the first extending part 6 and the first fixing part 5 are arranged on the surface of the first transversely extending layer 7 in parallel.
The second longitudinally extending layer comprises a second extending part 10 and a second fixing part 9, and the second extending part 10 and the second fixing part 9 are arranged on the surface of the second transversely extending layer 8 in parallel.
The first transverse extension layer 7, the second transverse extension layer 8, the first fixing part 5, the first extension part 6, the second fixing part 9 and the second extension part 10 are all rectangular plate-shaped structures.
The first transverse extension layer 7 and the second transverse extension layer 8 are both connected with the wing roots 4, and the two wing bodies in each pair of wings 2 are respectively positioned on two opposite sides of the laminated composite structure.
The first and second laterally extending layers 7 and 8 have different shrinkage/elongation rates, the first extending portion 6 has a shrinkage/elongation rate greater than that of the first fastening portion 5, and the second extending portion 10 has a shrinkage/elongation rate greater than that of the second fastening portion 9.
The sensor is arranged on the carrier 1 and used for measuring the flight parameters of the flight device and sending the flight parameters to the central control component, so that the central control component sends a preparation command to the power device 3.
When the array type wing flying device needs to fly, the central control unit controls the power supply to supply power to the power device 3, the first transverse extension layer 7 and the second transverse extension layer 8 in the power device 3 are electrically stimulated, the first transverse extension layer 7 and the second transverse extension layer 8 stretch and contract in a direction close to the wing 2 (namely, due to the fact that the shrinkage/elongation rates of the first transverse extension layer 7 and the second transverse extension layer 8 are different, the first transverse extension layer 7 and the second transverse extension layer 8 shrink/expand in directions on two sides of the wing 2, namely in a transverse direction), and the wing root 4 drives the wing body to vibrate, so that the device can fly.
When the flying device needs to turn, the central control component controls the power supply to supply power to the power device 3, the first extension part 6 is electrically stimulated, and the first extension part 6 can stretch and contract in a direction far away from/close to the first fixing part 5 (namely, the first extension part can contract/expand in a direction vertical to the transverse direction, namely, the longitudinal direction); the second extending portion 10 is electrically stimulated, and the second extending portion 10 is expanded/contracted in a direction away from/close to the second fixing portion 9 (i.e., contracted/expanded in a direction perpendicular to the transverse direction, i.e., the longitudinal direction); thereby drive first horizontal extension layer 7 and second horizontal extension layer 8 take place distortion, and then drive the flap direction of wing 2 changes to realize the change of direction of flight.
Example 2
As shown in fig. 5, the present invention provides an array type wing flying device, which is different from the flying device in embodiment 1 in the structure of the power device 3.
A pair of wing fins 2 is arranged at the joint of the two power parts, and the two wing fins 2 are respectively arranged on two side surfaces of the power flapping part which are oppositely arranged (namely, each pair of wing fins 2 are arranged in axial symmetry by taking the power device 3 as an axis).
And four turning power parts in the power parts are respectively connected with the power supply through electric wires, so that the four turning power parts are independent from each other and do not influence each other. Each direction-changing power component can be independently contracted when being electrified. The turning power component stretches and retracts to drive the flapping power component to deform, so that the wing 2 is driven to flap.
When the flying device needs to fly, the four turning power components on the upper layer can be stretched out and drawn back simultaneously, the four turning power components on the lower layer also can be stretched out and drawn back simultaneously, so that the four turning power components on the upper layer and the four turning power components on the lower layer are alternately stretched out and drawn back, and the wing roots 4 on the two sides can be caused to move up and down alternately.
Each pair of said wings 2 comprises a first wing 19 and a first wing 20.
The four on upper strata diversion power pack is a diversion power pack 11, b diversion power pack 12, c diversion power pack 13, d diversion power pack 14 along the clockwise respectively, just first wing 19 with the power pack that beats between a diversion power pack 11 and the d diversion power pack 14 is connected, first wing 20 with the power pack that beats between b diversion power pack 12 and the c diversion power pack 13 is connected.
The four of lower floor diversion power unit is A diversion power unit, B diversion power unit, C diversion power unit, D diversion power unit along the clockwise respectively, just first wing 19 with patting power unit between A diversion power unit and the D diversion power unit is connected, first wing 20 with patting power unit between B diversion power unit and the C diversion power unit is connected. The direction-changing power component 11 and the direction-changing power component A are vertically corresponding, the direction-changing power component 12 and the direction-changing power component B are vertically corresponding, the direction-changing power component C13 and the direction-changing power component C are vertically corresponding, and the direction-changing power component D14 and the direction-changing power component D are vertically corresponding.
When the direction-changing power component 11 and the direction-changing power component A are stretched and contracted simultaneously, the first wing 19 can be caused to move forwards; the D direction-changing power component 14 and the D direction-changing power component extend and retract simultaneously, and the first wing 19 can be caused to move backwards. When the B direction-changing power component 12 and the B direction-changing power component are simultaneously telescopic, the first wing 20 can be caused to move forwards; the C direction-changing power component 13 and the C direction-changing power component extend and retract simultaneously, so that the first wing 20 can move backwards.
When the direction-changing power component a 11 and the direction-changing power component D extend and retract simultaneously, the first wing 19 can be twisted clockwise; when the direction-changing power component A and the direction-changing power component d 14 are stretched and contracted simultaneously, the first wing 19 can be twisted in the anticlockwise direction. The first wing 20 works the same.
Example 3
As shown in fig. 6 and 7, the present invention provides an array type wing flying device, which is different from the flying device of embodiment 1 in the structure of the power unit 3.
The power unit 3 includes:
the wing structure comprises a first shell 15 and a second shell 16, wherein the first shell 15 and the second shell 16 are both curved surface structures, two opposite side ends of the curved surface structure of the first shell 15 are movably connected with the end part of the wing root part 4 respectively, namely, one end of the wing root part 4 is movably connected with the first shell 15. Two opposite side ends of the second shell 16 are respectively connected with the other ends of the wing roots 4, and the inner side of the curved surface of the second shell 16 is arranged opposite to the inner side of the curved surface of the first shell 15 to form a closed cavity of the power device 3;
a wing flapping power component 17 is arranged in the cavity of the power device, the wing flapping power component 17 is connected with the inner side of the first shell 15 and the inner side of the second shell 16, the wing flapping power component 17 deforms after being stimulated by the outside, so that the relative distance between the first shell 15 and the second shell 16 is driven to change through the deformation of the wing flapping power component, and the wing 2 performs vertical flapping motion under the action of force exerted on the wing 2 by the mutual matching of the first shell 15 and the second shell 16;
the number of the wing flapping power components 17 is two, and the wing flapping power components 17 are symmetrically arranged on the central axis of the cavity of the power device.
Still be provided with wing diversion power pack 18 in the power device cavity, wing diversion power pack 18 extends in the power device cavity in the direction that is on a parallel with 15 curved surface structures of first shell and the 16 curved surface structures of second shell, wing diversion power pack 18 run through in wing patting power pack 17 or attach to in wing patting power pack 17 surface, and with wing patting power pack 17 closely laminates, wing diversion power pack 18 takes place deformation after receiving external stimulus, deformation drives the part rather than laminating on the wing patting power pack 17, thereby makes wing patting power pack 17 takes place the distortion, and then makes the patting direction change of wing 2.
The number of the wing direction-changing power components 18 is two, and the two wing direction-changing power components 18 are symmetrically arranged around the central axis of the cavity of the power device.
When the flying device needs to fly, the wing flapping power component 17 receives external stimulation back, the wing flapping power component 17 is followed the extending direction of the wing flapping power component 17 takes place to be deformed (namely the wing flapping power component 17 is followed the extending direction of the wing flapping power component 17 is carried out to rise and contract), thereby drives the relative distance of the first shell 15 and the second shell 16 changes, and then makes the wing root 4 receive the first shell 15 with the pulling force or the thrust of the second shell 16, so that the wing 2 does up-and-down flapping motion. When the flight direction of the flight device needs to be changed, the wing turning power component 18 deforms after being stimulated by the outside, and the deformation drives the wing to flap the part, attached to the wing, of the power component 17, so that the wing flapping power component 17 is twisted, and the flapping direction of the wing is changed.
Although the embodiments of the present invention have been described above with reference to the accompanying drawings, the present invention is not limited to the above-described embodiments and application fields, and the above-described embodiments are illustrative, instructive, and not restrictive. Those skilled in the art, having the benefit of this disclosure, may effect numerous modifications thereto without departing from the scope of the invention as defined by the appended claims.
Claims (10)
1. An arrayed wing flight device, comprising:
a carrier;
more than two groups of wing assemblies are arrayed on the carrier.
2. The array winged flying device of claim 1, wherein the carrier is a frame structure having winged components disposed on at least two nodes of the frame structure.
3. The array wing flight device of claim 2, wherein the carrier is a planar frame structure.
4. The array winged flying device of claim 2, wherein the carrier is a space frame structure.
5. The array wing flight device of any one of claims 2 to 4, wherein the frame structure has a collapsed state and an expanded state.
6. The array wing flying device of claim 5, wherein the frame structure is convertible between a collapsed state and an expanded state.
7. The array wing flying device of claim 1, wherein each set of wing assemblies comprises one or more pairs of wings and at least one power device that powers the wings.
8. The arrayed wing flight device of claim 7, wherein each pair of the wings are arranged parallel to each other.
9. The array type wing flying device according to claim 7, wherein each wing comprises a wing root and a wing body, the wing root is connected with a power device, and the wing root drives the wing body to move.
10. The array winged flying device of claim 7, wherein the wings are layered.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110723286A (en) * | 2019-11-26 | 2020-01-24 | 赵小清 | Array wing flight device and application thereof |
| CN113306715A (en) * | 2021-07-06 | 2021-08-27 | 西北农林科技大学 | Novel micro bionic aircraft and simulation analysis method thereof |
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2019
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110723286A (en) * | 2019-11-26 | 2020-01-24 | 赵小清 | Array wing flight device and application thereof |
| CN113306715A (en) * | 2021-07-06 | 2021-08-27 | 西北农林科技大学 | Novel micro bionic aircraft and simulation analysis method thereof |
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