CN210310873U - Flap structure of solar cell panel flapping wing aircraft - Google Patents
Flap structure of solar cell panel flapping wing aircraft Download PDFInfo
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- CN210310873U CN210310873U CN201920846989.6U CN201920846989U CN210310873U CN 210310873 U CN210310873 U CN 210310873U CN 201920846989 U CN201920846989 U CN 201920846989U CN 210310873 U CN210310873 U CN 210310873U
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Abstract
The utility model discloses wing structure of solar cell panel flapping wing aircraft, the alar part skeleton that frame main part bilateral symmetry set up, the radius of alar part skeleton, the humerus, the phalanx, the leg passes through the imitative bat wing face of adhesive fixed connection flexible thin-film solar cell panel material, photoelectric effect based on solar cell panel flexible thin-film, convert the light energy of collecting on the wing face into the electric energy, charge for the battery, the time of flight that continues, wing face and alar part skeleton can fold and can expand, and not only convenient to carry, and can realize that aircraft wing structure expandes to wave the motion of warping with the wing area, satisfy long-time flight requirement on the basis that does not increase aircraft weight, thin-film solar cell panel can bend repeatedly and expand, span area is big, occupation space is few, moreover, the steam generator is simple in structure, long service life.
Description
Technical Field
The invention relates to a flap structure of a solar cell panel flapping wing aircraft, belonging to the technical field of miniature flapping wing aircraft.
Background
The flapping wing aircraft is an aircraft which is reversely and bionically developed according to the biological flight principle, has strong superiority compared with the traditional fixed wing aircraft and rotor aircraft, can realize flight by integrating lifting, hovering and propelling systems on a pair of wings, has better maneuverability and stability, and has wide application in military and civil fields; the flapping wing aircraft in the prior art has limited lift force generated by flapping of the airfoil surface, the self load weight is limited, the battery energy carried by the aircraft cannot meet the requirement of long-time flight, the endurance time is short, and the energy can be supplied only by absorbing and converting solar energy on the basis of not increasing the weight of the aircraft. The flapping wing air vehicle mainly comprises an insect-like type and an insect-like type, the insect-like flapping wing air vehicle is a miniature insect-like type flapping wing air vehicle, the wingspan area is small, the effect of supplying energy by using a solar panel is very small, the wingspan area of the bird-like flapping wing air vehicle is relatively large, the large wingspan area can absorb more solar energy to meet the cruising requirement, but the unfolding size of the bird-like flapping wing air vehicle is correspondingly large, the occupied space is large, and the carrying is inconvenient.
Disclosure of Invention
The invention aims to solve the technical problem of providing the flap structure of the solar cell panel flapping wing aircraft, which can meet the requirement of long-time flight, has a simple structure, is convenient to carry and has a long service life.
The invention relates to a flap structure of a solar cell panel flapping wing aircraft, which is characterized in that: the wing part framework is symmetrically arranged on two sides of the rack main body, and wing surfaces are arranged on the wing part framework; the wing part framework comprises leg bones positioned at two sides of the bottom of the frame main body and wing bones positioned at two sides of the middle part of the frame main body, and each side leg bone comprises a thigh bone hinged at the bottom of the frame main body and a shank bone fixedly connected at the lower end of the thigh bone; each side wing bone comprises a radius bone which is hinged and connected with the side of the main body of the rack and a humerus which is hinged and connected with the radius bone, and the far end of the humerus bone is hinged and connected with a plurality of phalanges; the airfoil surface material is a flexible thin-film solar cell panel, the airfoil surface is fixedly connected to the airfoil part framework through an adhesive, and the airfoil surface is connected to a driving device and a control circuit module in the rack main body through a connecting circuit;
the joints of the two ends of the humerus and the joints of the radius and the phalange in a hinged mode are respectively provided with a micro-electric motor, the humerus and the radius are provided with hollow inner cavities, and the wing surfaces are connected to a driving device and a control circuit module in the rack main body along the hollow inner cavities of the humerus and the radius through leads;
mounting grooves are formed in two sides of the frame main body, the end part of the radius is hinged and connected in the mounting grooves, the rotating angle range between the radius and the humerus is 110-140 degrees, and the rotating angle range between the humerus and the central line of the frame main body is 45-75 degrees;
the distal end of the humerus is simultaneously hinged with a first phalanx, a second phalanx, a third phalanx, a fourth phalanx and a fifth phalanx, and each phalanx can be driven by a micro motor to independently rotate;
the first phalanx and the fifth phalanx are positioned on the same straight line and can be driven by the micro motor to rotate simultaneously; the third phalanx is provided with a three-bending joint, and the fourth phalanx is provided with a two-bending joint; the second phalanx is also linear;
the first phalanx and the fifth phalanx are of a unitary structure;
the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are made of carbon fiber composite materials, and the hinged connection structure materials at the two ends of the humerus are also made of carbon fiber composite materials;
the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are also provided with hollow inner cavities, and the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are also connected to a driving device and a control circuit module inside the machine frame main body along the hollow inner cavities of the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx through leads;
the surface of the flexible thin-film solar cell panel is coated with a graphene coating.
The wing part frameworks are symmetrically arranged on two sides of the rack main body, the radius, the humerus, the phalange and the leg bone of each wing part framework are fixedly connected with a bat-like wing surface of a flexible thin-film solar cell panel material through an adhesive, based on the photoelectric effect of a flexible thin film of the solar cell panel, light energy collected on the wing surface is converted into electric energy to charge a battery, the endurance flight time is long, the wing surface and the wing part frameworks can be folded and unfolded, the wing structure folding and unfolding device is convenient to carry, the wing structure unfolding and wing surface area deformation movement can be realized, long-time flight requirements can be met on the basis of not increasing the weight of the aircraft, the thin-film solar cell panel can be repeatedly bent and unfolded, the wingspan area is large, the occupied space is small, the structure is simple, and.
Drawings
FIG. 1 is a perspective view of a flap structure of a solar panel ornithopter according to an embodiment of the invention;
FIG. 2 is a schematic plan view of a flap structure of a solar panel ornithopter according to an embodiment of the invention.
Detailed Description
As shown in the figure, a flap structure of a solar cell panel flapping wing aircraft, a rack main body 1 adopts a general structure of the flapping wing aircraft known in the prior art, no special design is needed, and a driving device and a control circuit module are arranged in the rack main body 1; the main technical scheme is that wing portion frameworks are symmetrically arranged on two sides of a rack main body 1, airfoils are fixedly installed on the wing portion frameworks, flexible thin-film solar cell panels are selected from airfoil materials, the flexible thin-film solar cell panels are fixedly connected to the wing portion frameworks through adhesives, and are connected to a driving device and a control circuit module inside the rack main body through connecting circuits, based on the photoelectric effect of flexible thin films of the solar cell panels, light energy collected on the airfoils is converted into electric energy, batteries of the driving device and the control circuit module are charged, the endurance flight time is long, long-time flight requirements are met on the basis that the weight of an aircraft is not increased, the flexible thin-film solar cell panels have certain flexibility and ductility, the flexible thin-film solar cell panels can be repeatedly bent and unfolded, the structure is simple.
The wing framework comprises leg bones positioned at two sides of the bottom of the frame main body and wing bones positioned at two sides of the middle part of the frame main body, and each leg bone comprises a thigh bone 9 hinged at the bottom of the frame main body and a shank bone 10 fixedly connected at the lower end of the thigh bone; each side wing bone comprises a radius 2 hinged to the side of the main body of the rack and a humerus 3 hinged to the radius, and the far end of the humerus 3 is hinged with a plurality of phalanges; the radius, the humerus, the phalanges and the leg bones are fixedly connected with the bat-imitated wing surface of the flexible thin-film solar cell panel material through the adhesive, the bat-imitated wing surface can be folded and unfolded, the carrying is convenient, the motion of unfolding and swinging of a wing structure and deformation of the wing surface area can be realized, the wingspan area is large, and the occupied space is small.
Furthermore, the hinge joints of the two ends of the humerus 3 and the radius 2 and the phalange are respectively provided with a micro-electric motor, the humerus and the radius are provided with hollow inner cavities, and the wing surfaces are connected to a driving device and a control circuit module in the rack main body along the hollow inner cavities of the humerus and the radius through leads;
further, mounting grooves are formed in two sides of the frame main body 1, the end portion of the radius 2 is hinged and connected in the mounting grooves, the rotation angle range between the radius 2 and the humerus 3 is 110 degrees to 140 degrees, and the rotation angle range between the humerus 3 and the central line of the frame main body 1 is 45 degrees to 75 degrees; the distal end of the humerus 3 is simultaneously hinged with a first phalanx 4, a second phalanx 5, a third phalanx 6, a fourth phalanx 7 and a fifth phalanx 8, and each phalanx can be driven by a micro motor to independently rotate;
in the practical operation of this embodiment, the rack main body is formed by combining the external rack housing 11 and the internal control main body 12, the control main body 12 is installed inside the rack housing 11 in a position-limited fit manner and can rotate inside the rack housing 11, the rack housing is equivalent to a "tortoise shell", and the control main body is equivalent to "meat" inside the "tortoise shell";
so that the airfoil and the wing skeleton have 8 degrees of freedom, including: the degree of freedom is one, the control main body is arranged in the rack shell in a limiting and matching mode to be similar to joints of a human body, and the back and abdomen movement or rotation of shoulders is provided; the degree of freedom is two, the joints of the main body and the humerus are controlled, and head and tail and front and back movement are provided; degree of freedom three, the joint of the humerus and the elbow radius ulna; four, five, six, seven degrees of freedom, four joints at the phalanges, allowing each phalange to rotate independently relative to the radius; eight degrees of freedom, joints of the legs and the buttocks.
Still further, the first phalanx 4 and the fifth phalanx 8 are positioned on the same straight line and can be driven by the micro motor to rotate simultaneously; the first phalanx 4 and the fifth phalanx 8 can be selected from parts of an integral structure, and can also be formed by fixedly connecting split type parts, the third phalanx 6 is provided with a three-bending joint, the fourth phalanx 7 is provided with a two-bending joint, and the second phalanx 5 is also of a linear type, so that the biological flight principle is simulated as much as possible.
The first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are made of carbon fiber composite materials, the hinged connection structure materials at the two ends of the humerus are also made of carbon fiber composite materials, and the endurance time is increased to the maximum extent on the basis that the weight of the aircraft is not increased.
The first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx also have hollow inner cavities, and the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are also connected to a driving device and a control circuit module inside the machine frame body along the hollow inner cavities of the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx through leads so as to control the uniform rotary motion of the phalanges or the independent rotary motion of the phalanges.
And finally, coating a graphene coating on the surface of the flexible thin film solar cell panel to ensure the photoelectric effect of the flexible thin film of the solar cell panel and convert the light energy collected on the wing surface into electric energy.
The wing part frameworks are symmetrically arranged on two sides of the rack main body, the radius, the humerus, the phalange and the leg bone of each wing part framework are fixedly connected with a bat-like wing surface of a flexible thin-film solar cell panel material through an adhesive, based on the photoelectric effect of a flexible thin film of the solar cell panel, light energy collected on the wing surface is converted into electric energy to charge a battery, the endurance flight time is long, the wing surface and the wing part frameworks can be folded and unfolded, the wing structure folding and unfolding device is convenient to carry, the wing structure unfolding and wing surface area deformation movement can be realized, long-time flight requirements can be met on the basis of not increasing the weight of the aircraft, the thin-film solar cell panel can be repeatedly bent and unfolded, the wingspan area is large, the occupied space is small, the structure is simple, and.
The specific design concept is as follows:
the invention belongs to the technical field of miniature flapping wing aircrafts, and relates to a flapping wing aircraft wing structure which is mainly used for converting light energy collected on a wing surface into electric energy and can be repeatedly folded and unfolded based on the photoelectric effect of a flexible film of a solar cell panel.
The flapping wing aircraft is an aircraft which is reversely and bionically developed according to the biological flight principle, has strong superiority compared with the traditional fixed wing aircraft and rotor aircraft, can realize flight by integrating lifting, hovering and propelling systems on a pair of wings, has better maneuverability and stability, and has wide application in military and civil fields.
At present, the short endurance time of the flapping wing aircraft is a main reason that the flapping wing aircraft cannot be applied and popularized, because the lift force generated by flapping wings of the flapping wing aircraft is limited, the self load weight is strictly limited, the battery energy carried by the aircraft cannot meet the requirement of long-time flight, and the energy can be supplied only by absorbing and converting solar energy on the basis of not increasing the weight of the aircraft at the present stage. The flapping wing air vehicle mainly comprises an insect-like type and an insect-like type, the insect-like flapping wing air vehicle is a miniature insect-like flapping wing air vehicle, the wingspan area is small, the effect of supplying energy by utilizing a solar cell panel is very small, the wingspan area of the bird-like flapping wing air vehicle is relatively large, the large wingspan area can absorb more solar energy to meet the cruising requirement, and the cruising effect of the bird-like flapping wing air vehicle is more remarkable than that of a microminiature flapping wing air vehicle.
Convenient to carry and disguise also are an important performance index of flapping wing aircraft, to large-scale flapping wing aircraft such as imitative bird, the wing span is folded to less space size after transportation and recovery, has very strong practicality, portable in the transportation does benefit to after descending and hides, fully expandes the airfoil at the flight in-process, can provide abundant lift and electric energy.
In order to improve the endurance time of the flapping wing aircraft and simultaneously solve the current situations that the existing flapping wing aircraft is large in space size and difficult to carry, the invention provides the foldable flapping wing aircraft.
The technical scheme of the invention is as follows: the wing framework comprises a rack main body, a hinged connection mechanism, a leg bone and a wing bone, wherein the rack main body is of an arc-shaped hollow cavity structure, a driving device and a control circuit module are arranged in the rack main body, and the wing bone and the leg bone are connected with the wing surface; the airfoil is made of a flexible thin film solar cell panel, the flexible thin film solar cell panel is fixed on an airfoil rib through an adhesive, and a graphene layer is coated on the surface of the flexible thin film solar cell panel.
The angle between the humerus and the radius after the humerus is unfolded is 110-140 degrees, and the angle between the humerus and the central line of the frame main body is 45-75 degrees;
the airfoil structure contains 8 degrees of freedom, including: the first degree of freedom, the control main body 12 and the frame shell 11 simulate joints of a human body and provide the back and abdomen movement or rotation of shoulders; the degree of freedom is two, the joints of the main body and the humerus are controlled, and head and tail and front and back movement are provided; degree of freedom three, the joint of the humerus and the elbow radius ulna; four, five, six, seven degrees of freedom, four joints at the phalanges, allowing each phalange to rotate independently relative to the radius; eight degrees of freedom, joints of the legs and the buttocks.
The first micro motor is arranged at the first hinge for connecting the humerus and the radius, the second micro motor is arranged at the second hinge for connecting the humerus and the phalange, the interiors of the humerus and the radius are of hollow structures, and the guide lines are arranged to connect the airfoil power generation part with the micro motor and the control circuit module;
the phalanx I and the phalanx V are of an integral structure and are linear, the phalanx II is also linear, the phalanx III is provided with three bending joints, and the phalanx IV is provided with two bending joints.
The airfoil is made of a flexible thin-film solar cell panel, has certain flexibility and extensibility, can be repeatedly folded and unfolded, is fixed on an airfoil rib through an adhesive, and the surface of the flexible thin-film solar cell panel is coated with a graphene layer.
The wing surface ribs and bones are made of carbon fiber composite materials, the inner parts of the ribs and bones penetrate through leads, and parts at the connecting parts are also made of the carbon fiber composite materials.
The invention has the advantages that:
(1) the mechanical structure is simple and practical;
(2) the thin-film solar cell panel is directly used as a wing airfoil of the flapping-wing aircraft, so that the self weight of the flapping-wing aircraft is reduced, and meanwhile, the thin-film solar cell panel can be repeatedly bent and unfolded;
(3) based on the photoelectric effect of the flexible film of the solar cell panel, the light energy collected on the wing surface is converted into electric energy, and then the battery is charged, so that the endurance flight capability of the aircraft is improved, meanwhile, the wing surface ribs can be folded and unfolded, the carrying is convenient, and the unfolding and swinging movement of the wing surface wing structure and the wing surface area deformation movement can be realized.
The invention provides a wing structure of a flapping wing aircraft with a foldable solar cell panel, and belongs to the technical field of miniature flapping wing aircraft. The wing comprises a wing surface and a wing framework, wherein the wing surface is similar to a bat in shape, the wing framework is symmetrically distributed along a central line, the wing framework comprises a machine body frame, a connecting body, a hinge structure and wing surface bones and muscles, the machine body frame is of an arc-shaped hollow cavity structure, a driving device and a control circuit module are arranged in the machine body frame, the connecting body comprises a humerus and a radius, the humerus and the radius are connected through a hinge I, the connecting body is connected with the wing surface bones and muscles through a hinge II, and the wing surface bones and muscles comprise a phalanx I, a phalanx II, a phalanx III, a phalanx IV, a phalanx V, a thigh. The airfoil is made of a flexible thin film solar cell panel, the flexible thin film solar cell panel is fixed on an airfoil rib through an adhesive, and a graphene layer is coated on the surface of the flexible thin film solar cell panel. The solar cell panel based wing surface folding and unfolding device converts light energy collected on the wing surface into electric energy based on the photoelectric effect of the flexible film of the solar cell panel, and then charges the battery, so that the endurance flight capability of the aircraft is improved, meanwhile, the wing surface ribs can be folded and unfolded, the carrying is convenient, and the unfolding and swinging movement of a wing surface structure and the wing surface area deformation movement of the aircraft can be realized.
Claims (9)
1. The utility model provides a flap structure of solar cell panel flapping wing aircraft which characterized in that: the wing part framework is symmetrically arranged on two sides of the rack main body, and wing surfaces are arranged on the wing part framework; the wing part framework comprises leg bones positioned at two sides of the bottom of the frame main body and wing bones positioned at two sides of the middle part of the frame main body, and each side leg bone comprises a thigh bone hinged at the bottom of the frame main body and a shank bone fixedly connected at the lower end of the thigh bone; each side wing bone comprises a radius bone which is hinged and connected with the side of the main body of the rack and a humerus which is hinged and connected with the radius bone, and the far end of the humerus bone is hinged and connected with a plurality of phalanges; the airfoil material is a flexible thin-film solar cell panel, the airfoil is fixedly connected to the airfoil framework through an adhesive, and the airfoil is connected to the driving device and the control circuit module in the rack main body through a connecting circuit.
2. The flap structure of a solar panel ornithopter of claim 1, wherein: the articulated junction of humerus both ends and radius, phalanx is provided with little type motor respectively, and humerus, radius have hollow inner chamber, and the airfoil passes through the wire and is connected to inside drive arrangement and the control circuit module of frame main part along the hollow inner chamber of humerus, radius.
3. The flap structure of a solar panel ornithopter of claim 1, wherein: the two sides of the frame main body are provided with mounting grooves, the end part of the radius is hinged and connected in the mounting grooves, the rotating angle range between the radius and the humerus is 110 degrees to 140 degrees, and the rotating angle range between the humerus and the central line of the frame main body is 45 degrees to 75 degrees.
4. The flap structure of a solar panel ornithopter of claim 2, wherein: the distal end of the humerus is simultaneously hinged with a first phalanx, a second phalanx, a third phalanx, a fourth phalanx and a fifth phalanx, and each phalanx can be driven by a micro motor to independently rotate.
5. The flap structure of a solar panel ornithopter of claim 4, wherein: the first phalanx and the fifth phalanx are positioned on the same straight line and can be driven by the micro motor to rotate simultaneously; the third phalanx is provided with a three-bending joint, and the fourth phalanx is provided with a two-bending joint; the second phalanx is also linear.
6. The flap structure of a solar panel ornithopter of claim 5, wherein: the first phalanx and the fifth phalanx are of unitary construction.
7. The flap structure of a solar panel ornithopter of claim 4, wherein: the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are made of carbon fiber composite materials, and the hinged connection structure materials at the two ends of the humerus are also made of carbon fiber composite materials.
8. The flap structure of a solar panel ornithopter of claim 5, wherein: the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx also have hollow inner cavities, and the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx are also connected to the driving device and the control circuit module inside the machine frame main body along the hollow inner cavities of the first phalanx, the second phalanx, the third phalanx, the fourth phalanx and the fifth phalanx through leads.
9. The flap structure of a solar panel ornithopter of claim 1, wherein: the surface of the flexible thin-film solar cell panel is coated with a graphene coating.
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| CN201920846989.6U CN210310873U (en) | 2019-06-06 | 2019-06-06 | Flap structure of solar cell panel flapping wing aircraft |
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| CN201920846989.6U CN210310873U (en) | 2019-06-06 | 2019-06-06 | Flap structure of solar cell panel flapping wing aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182362A (en) * | 2019-06-06 | 2019-08-30 | 江苏航空职业技术学院 | A kind of flap structure of solar panel flapping wing aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182362A (en) * | 2019-06-06 | 2019-08-30 | 江苏航空职业技术学院 | A kind of flap structure of solar panel flapping wing aircraft |
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