CN109760833B - Foldable elastic wing - Google Patents
Foldable elastic wing Download PDFInfo
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- CN109760833B CN109760833B CN201910081715.7A CN201910081715A CN109760833B CN 109760833 B CN109760833 B CN 109760833B CN 201910081715 A CN201910081715 A CN 201910081715A CN 109760833 B CN109760833 B CN 109760833B
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Abstract
The invention relates to a foldable elastic wing in the field of aircrafts, which comprises a wing connecting plate, a wing short plate, a wing long plate, a wing connecting rod, a wing rib, a thin wing panel, an upper covering wing panel and a lower covering wing panel, wherein the wing connecting plate is fixedly connected with the wing short plate; the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod, the wing rib, the thin wing panel, the upper covering wing panel and the lower covering wing panel are connected through shaft holes; the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod and the wing rib are combined in a plane four-bar mechanism mode, the wing connecting plate is connected with the airplane body and the wing driving mechanism, reciprocating thrust is input into the wing driving mechanism to push the wing short plate to swing around a shaft, and the wing short plate is provided with a plurality of plane four-bar mechanisms consisting of the wing long plate, the wing connecting rod and the wing rib to finish the folding and unfolding actions of the wing. The invention can reduce the resistance of the wings during the flying process of the flapping wings to the maximum extent, and can save the wing storage space to the maximum extent when the aircraft is parked.
Description
Technical Field
The invention relates to the field of flapping wing and fixed wing aircraft equipment, in particular to a foldable elastic wing.
Background
The flapping wing aircraft is an aircraft capable of flying through wings flapping up and down, and in the existing aircraft, the problem that downward reaction force is brought when the wings are raised up cannot be solved, so that the fuselage floats up and down in the flying process, and the fuselage vibrates. Cannot fly smoothly and flexibly as a bird. To solve the problem, the wings need to be folded and unfolded in the flying process like bird wings. The great reason why the flapping wing air vehicle cannot eliminate the up-and-down floating and the fuselage fluttering in flight is a great factor which hinders the development and progress of the flapping wing air vehicle in the practical and aviation industries is that no practical wing can be folded and unfolded at present.
Meanwhile, because the wings of the existing flapping wing aircraft can not be unfolded and folded flexibly like bird wings, the flying speed is generally relatively low.
One SmartBird developed by Festo technologies is a robotic bird that can simulate bird flight as well as flap wings realistically. Smartbird's wings can be flapped up and down and also can be twisted at a specific angle, so that extraordinary aerodynamic performance and agility are given to the ultralight robot bird. However, the wings of the robot bird can not be folded and unfolded like bird wings, and when the wings are raised in the flying process, the downward force acts on the fuselage, so that the fuselage sinks greatly, the fuselage shakes seriously, and the stable flying can not be realized like birds.
Through the search of the prior art, the invention name of Chinese invention patent CN201610692704.9 is a kind of this invention discloses an ornithopter, which belongs to the technical scheme of the aerocraft field, including rotating crankshaft assembly, two gangbars, two transmission modules and mounting shaft; the rotating crankshaft component is provided with two crankshafts which are respectively arranged on two opposite side surfaces of the rotating crankshaft component; one end of each linkage rod is connected with a crankshaft shaft, and the other end of each linkage rod is connected with a transmission module shaft; the two transmission modules are connected with the mounting shaft, and each transmission module is provided with a flapping wing; the rotating crankshaft assembly is used for driving the linkage rod to perform curved swing motion, the linkage rod is used for driving the two transmission modules to perform separation and opposite motion around the mounting shaft, and the transmission modules are used for driving the flapping wings to perform flapping wing motion. Compared with the prior art which needs gears to realize multiple transmissions, the invention reduces the transmission times, so that the transmission of power is more direct and rapid, thereby improving the transmission efficiency and realizing the long-time flight of the flapping wing aircraft. However, the invention cannot reduce the resistance of the flapping wings during the flying process to the maximum extent and can also save the wing storage space to the maximum extent when the aircraft is parked.
Disclosure of Invention
In view of the deficiencies of the prior art, it is an object of the present invention to provide a deployable elastic wing. The invention can reduce the resistance of the wings during the flying process of the flapping wings to the maximum extent, and can save the wing storage space to the maximum extent when the aircraft is parked.
The present invention relates to a deployable elastic wing comprising: the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod, the wing rib, the thin wing panel, the upper covering wing panel and the lower covering wing panel;
the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod, the wing rib, the thin wing panel, the upper covering wing panel and the lower covering wing panel are connected through shaft holes; the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod and the wing rib are combined in a planar four-bar linkage manner;
the wing connecting plate is connected with the body and the wing driving mechanism, the wing driving mechanism inputs reciprocating thrust to push the wing short plate to swing around a shaft, and the wing short plate drives the wing long plate, the wing connecting rods and a plurality of plane four-bar mechanisms formed by the wing ribs to finish the folding and unfolding actions of the wings.
Preferably, the four-bar linkage mechanism C and the four-bar linkage mechanism D formed by the wing ribs and the wing links are parallelogram.
Preferably, the four-bar linkage E, F, G, H, I, L, J, K, L formed by the wing ribs and the wing links is a trapezoid.
Preferably, adjacent sides of two adjacent quadrangles of the four-bar linkage E, F, G, H, I, L, J, K, L share one line, and the shared line is a long side and a short side on the two adjacent quadrangles respectively.
Preferably, the wing connecting plate, the wing link and the wing short plate form a four-bar linkage mechanism a and a four-bar linkage mechanism B, and the total length of two edges of the four-bar linkage mechanism E, F, G, H, I, L, J, K, L with two opposite angles being increased is equal after the two edges are added together.
Preferably, the wing ribs and the thin wing pieces are made of elastic materials, the front ends of the wing ribs are provided with rotating shaft connecting holes, the rotating shaft connecting holes gradually narrow from width to width, the side edges of the rotating shaft connecting holes are in a convex semicircular shape, and the rotating shaft connecting holes and the thin wing pieces are fixedly connected to form a wing rib piece combination.
Preferably, the rib and the thin fin are combined in a winding and fixing mode.
Preferably, the wing rib and the thin wing piece are integrated, the wing rib serves as a main body, the thin wing piece extends from two sides of the wing rib, and the thin wing piece is formed by cold extrusion molding or plastic injection molding of a metal material.
Preferably, the upper covering wing panel and the lower covering wing panel are provided with a plurality of wing panels covering the wing connecting rods, and the whole wing is connected into an integral wing surface when the wing connecting rods are unfolded.
Preferably, the wing connecting plate is fixedly connected with the wing connecting plate covering sheet, the wing short plate is fixedly connected with the wing short plate covering sheet, and the wing long plate is fixedly connected with the wing long plate covering sheet.
Compared with the prior art, the invention has the following beneficial effects:
1. the structure of the foldable elastic wing utilizes the principle of plane four-bar linkage to drive the wing short plate, the wing connecting rod, the wing long plate and the elastic wing rib to finally achieve the folding and unfolding actions through the swinging angle of the rotating shaft. Therefore, the whole wing surface can be divided into a plurality of wing pieces, and then an overlapping combination of movable sheets is formed, so that the wing surface changes the wing folding and unfolding degree according to the actual situation in flight, and the flight resistance can be reduced to the maximum extent. Meanwhile, when the wings are raised, the reaction force during raising is reduced by folding the wings, the up-and-down fluctuation during flying is reduced, and the flying is more stable. Because the wings can be folded and unfolded, the aircraft occupies smaller parking space.
2. The invention relates to an elastic thin wing panel of a foldable elastic wing, which is fixed on an elastic wing rib to form a rib panel combination, the front end of the elastic thin wing panel is fixed through a hole shaft, the rear end of the elastic thin wing panel is in a free state, the rib panel combination is made of elastic materials, and the wing panel formed by the rib panel combination has flexible deformation capability and can change the state of the wing panel in a self-adaptive manner. The front end of the wing rib plate combination is high in strength and is connected with the wing connecting rod, the wing ribs are narrower towards the rear end and are weakened in strength and in a free state, the front end of each wing rib always bends with the rear end due to stress when the flapping frequency is accelerated, the front end and the rear end of each wing rib form a fall when flapping is carried out, the whole wing surface generates a twisting action, and finally the force of flapping the upper flapping wing and the lower flapping wing is converted into backward thrust.
3. The wing rib groups of the foldable elastic wing are longitudinally arranged, and the boss at the front end of the elastic wing rib has a torsion characteristic, so that the wing rib surface with the boss is inclined, the wing rib groups and the upper and lower surfaces of the adjacent wing rib groups are staggered, when the wing is shot downwards, the left wing rib group presses the wing panel of the right wing rib group to seal airflow, and then the wing rib transmits the force to the body to generate lift force, and meanwhile, backward thrust can be generated more efficiently. When the wing is raised, the wing panel is just freely bent, so that air can be filtered, and the raising resistance is maximally reduced. The elastic wing surface formed by the wing rib sheet group can be self-adaptively twisted, and meanwhile, the elastic wing surface can also greatly slow down the force acted on the wing surface by external airflow and transferred to the aircraft body. The excellence of the foldable elastic wings enables the flapping wing aircraft to fly flexibly as close to birds.
4. The foldable elastic wing is a thin sheet in a large area, is lighter than a traditional skin structure, and meanwhile, because the rear end of the elastic wing is in a free state, the problem of tearing caused by insufficient strength is solved, the wing is scattered, and the rear end is in a free state. The wing panels can be made to be very thin and light, the weight of the wing is greatly reduced, the wing is lighter and thinner, the center of gravity is concentrated on the fuselage, and the wing is more stable and convenient to fly and control.
5. The foldable elastic wing is safe and better, the elastic wing rib is made of elastic materials and has good toughness, and the wing rib groups are mutually independent, so that the influence of fatigue fracture on the whole is small. If the airfoil is inadvertently bumped, it is only partially damaged or deformed, and not as a monolithic wing, with the risk of total fracture. The foldable elastic wing is more flexible to respond to airflow changes in flight. When the control of the side wind, the cross wind, the turbulence, the selection, the folding and the unfolding degrees is dealt with, the flight becomes more free and flexible.
6. The foldable elastic wing can also be suitable for a fixed wing aircraft, is different from the traditional variable sweepback wing, the variable sweepback wing only changes the sweepback angle of the wing but can not change the wingspan area of the wing, the foldable elastic wing selects different wingspan degrees according to different flight modes (take-off, landing, flat flight and acceleration) and changes the wingspan area of the wing, and the formed elastic wing surface has strong safety and practicability and is more advantageous than the traditional wing.
7. The foldable elastic wing has the advantages of simple structure, more hole-shaft connection, low requirement on machining and manufacturing precision, strong practicability and convenient machining, and can meet the precision requirement by using common machining to realize structural assembly. The processing cost is low, and the later maintenance and replacement are convenient.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic assembly view of the practice of the present invention;
FIG. 2 is a schematic view of an upper and lower cover tab assembly embodying the present invention;
FIG. 3 is a schematic view of a thin tab assembly embodying the present invention;
FIG. 4 is an assembly view of an embodiment of the present invention;
FIG. 5 is a schematic diagram of the linkage mechanism components used in the practice of the present invention;
FIG. 6 is an isometric view of an embodiment of the present invention;
FIG. 7 is a schematic view of a twisted portion of a rib according to an embodiment of the present invention;
FIG. 8 is a view of a collapsed condition of an airfoil embodying the present invention;
FIG. 9 is a view showing the winding and fastening of a rib and a thin tab according to the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
Examples
In view of the above requirements, the present invention relates to a foldable elastic wing, which comprises a wing connecting plate, a wing short plate, a wing long plate, a plurality of wing connecting rods, a wing rib, a thin wing panel, and upper and lower covering wing panels, which are connected and combined through a shaft hole. The wing connecting plate, the wing short plate, the wing long plate, the plurality of wing connecting rods and the wing ribs are combined with each other in a planar four-bar linkage mode and are constrained in a mutual correlation mode. Regarding all the mechanisms forming the four-bar linkage as quadrangles, the closing action of the quadrangles with two opposite angles being opened and enlarged and the vertex distance being reduced and the other two opposite angles being contracted and the vertex distance being enlarged is satisfied: the condition that the two edges making up the two diagonal corners, whose angles become larger, each add up to the total length is equal. For example, if a front end hole of the wing connecting plate 1 is connected with a left end hole of the wing short plate 2, a second hole of the wing connecting plate 1 is connected with a left end hole of the wing connecting rod 4, the front end of the wing connecting rod 5 is connected with a middle hole of the wing short plate 2, and the rear end of the wing connecting rod 5 is connected with a right end hole of the wing connecting rod 4, a four-bar mechanism a is formed. In the four-bar mechanism A, the distance between the left end hole and the middle hole of the wing short plate 2 is set as a first connecting bar; a second connecting rod is arranged between the front end hole of the wing connecting plate 1 and a second hole; the wing link 4 is set as a third link; the wing link 5 is set as a fourth link; in the four-link a mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added. Therefore, the four-link A mechanism can be ensured, the angle formed by connecting the first link and the second link is enlarged, the angle formed by connecting the third link and the fourth link is also enlarged during the folding action, and the distance between the connecting vertexes of the first link and the second link can be minimized. Finally, the four-bar mechanism consisting of all the associated wing connecting rods, the elastic wings and the ribs can flexibly complete the folding action.
The wing comprises a wing connecting plate 1, a wing short plate 2, a wing long plate 3, 13 wing connecting rods 4-16, 15 wing ribs 17-31, a plurality of thin wings and a plurality of groups of upper and lower covering wings. The wing connecting plate 1, the wing short plate 2, the wing long plate 3, the wing connecting rod, the wing rib and the upper and lower covering wing plates are connected and combined through shaft holes. Each connecting part is a joint which can freely swing. The wing connecting plate 1, the wing short plate 2, the wing long plate 3, the wing connecting rods, the wing ribs and the wing connecting plates are combined in a planar four-bar linkage mode and are constrained in a mutual correlation mode. The wing connecting plate 1 is connected with the fuselage, the fuselage provides power to drive the wing short plate 2 to swing forwards at a certain angle around the shaft, and the wing short plate 2 drives the wing long plate 3 to complete the folding action of the four-bar mechanism together with all the wing connecting rods and the wing ribs.
The upper surface and the lower surface of the wing connecting plate 1 and the wing long plate 3 are respectively provided with three layers, the middle layer is provided with a wing connecting rod, a wing rib and a wing short plate 2 which are four-connecting-rod moving areas for realizing main actions, the second layer is provided with an upper covering wing and a lower covering wing, and a plurality of pieces cover a space area when the wing connecting rods are unfolded, so that the whole wing surface is connected into an integral wing surface. The wing connecting plate 1 is provided with upper and lower first layer wing connecting plate covering pieces 47, the wing long plate 3 is provided with upper and lower first layer wing long plate covering pieces 49, and the wing short plate covering pieces 48 are arranged on the upper and lower surfaces of the wing short plate 2 and are in the same plane and used for covering the vacancy area of the upper and lower covering wing joint of the second layer.
The middle hole of the wing short plate 2 is connected with the front end of a wing connecting rod 5, the right end hole of the wing short plate 2 is connected with the first hole at the left end of a wing long plate 3, the second hole at the left end of the wing long plate 3 is connected with the right end of a wing connecting rod 6, the rear end of the wing connecting rod 5 is connected with the left end of the wing connecting rod 6 to form a four-connecting-rod B mechanism, and the distance between the middle hole and the right end hole of the wing short plate 2 in the four-connecting-rod B mechanism is set as a first connecting rod; the wing link 5 is set as a second link; the wing link 6 is set as a third link; a fourth connecting rod is arranged between the left end hole of the wing long plate 3 and the second hole; in the four-link B mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The left end hole of the wing connecting rod 4 is connected with the second hole of the wing connecting plate 1, the left end hole of the wing connecting rod 7 is connected with the rear end hole of the wing connecting plate 1, the right end hole of the wing connecting rod 4 is connected with the front end hole of the wing rib 19, the right end hole of the wing connecting rod 7 is connected with the second hole of the front end of the wing rib 19 to form a four-link C mechanism, and the length of each connecting rod is set to be two sets of parallelograms with the same opposite sides. The wing rib 17 and the wing rib 18 are additionally arranged to be connected under the condition that the middle of the wing connecting rod 4 and the wing connecting rod 7 are divided into two equal holes, the front end holes of the two wing ribs are connected with the middle hole of the wing connecting rod 4, the second front end holes of the two wing ribs are connected with the middle hole of the wing connecting rod 7, and due to the characteristic of the four-connecting-rod C mechanism with two opposite sides equal, the four-connecting-rod mechanism can ensure that the wing ribs 19 of the wing rib 17 and the wing rib 18 are always parallel to the wing connecting plate 1 in the swinging process, and the wing ribs cannot interfere with each other in the wing surface folding.
The left end hole of the wing connecting rod 6 is connected with the front end hole of the wing rib 19, the left end hole of the wing connecting rod 8 is connected with the second front end hole of the wing rib 19, the right end hole of the wing connecting rod 6 is connected with the front end hole of the wing rib 23, the right end hole of the wing connecting rod 8 is connected with the second front end hole of the wing rib 23, a four-connecting-rod D mechanism is formed, and the length of each connecting rod is set to be a parallelogram with two groups of opposite sides equal. The wing rib 20, the wing rib 21 and the wing rib 22 are additionally arranged to be connected under the condition that three holes are evenly divided in the middle of the wing connecting rod 6 and the wing connecting rod 8, a front end hole of the three wing ribs is connected with a middle hole of the wing connecting rod 6, a second hole in the front end of the three wing ribs is connected with a middle hole of the wing connecting rod 8, and due to the characteristic of a four-connecting-rod D mechanism with two equal pairs of edges, the four-connecting-rod mechanism can swing, so that the wing connecting rod 6 and the wing connecting rod 8 are always parallel, the wing rib 19, the wing rib 20, the wing rib 21, the wing rib 22 and the wing rib 23 are always parallel to the wing connecting plate 1, and the wing ribs.
A first hole at the front end of the wing rib 23 is connected with a second hole at the left end of the wing long plate 3, a third hole at the front end of the wing rib 23 is connected with a hole at the left end of the wing connecting rod 9, a first hole at the front end of the wing rib 24 is connected with a third hole at the left end of the wing long plate 3, a third hole at the front end of the wing rib 24 is connected with a hole at the right end of the wing connecting rod 9, a four-connecting-rod E mechanism is formed, and in the four-connecting-rod E mechanism, the distance between the first hole and the third hole at the front end of the wing; the wing link 9 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 24; a fourth connecting rod is arranged between the second hole and the third hole at the left end of the wing long plate 3; in the four-link E mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
A first hole at the front end of the wing rib 24 is connected with a third hole at the left end of the wing long plate 3, a second hole at the front end of the wing rib 24 is connected with a hole at the left end of the wing connecting rod 10, a first hole at the front end of the wing rib 25 is connected with a fourth hole at the left end of the wing long plate 3, a third hole at the front end of the wing rib 25 is connected with a hole at the right end of the wing connecting rod 10 to form a four-connecting-rod F mechanism, and in the four-connecting-rod F mechanism, the distance between the first hole and the second hole at the front end of the wing rib 24 is; the wing link 10 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 25; a fourth connecting rod is arranged between the third hole and the fourth hole at the left end of the wing long plate 3; in the four-link F mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The first hole at the front end of the wing rib 25 is connected with the fourth hole at the left end of the wing long plate 3, the second hole at the front end of the wing rib 25 is connected with the hole at the left end of the wing connecting rod 11, the first hole at the front end of the wing rib 26 is connected with the fifth hole at the left end of the wing long plate 3, the third hole at the front end of the wing rib 26 is connected with the hole at the right end of the wing connecting rod 11, a four-connecting-rod G mechanism is formed, and the distance between the first hole and the second hole at the front end of the wing rib 25 is set as a first connecting rod in the four-; the wing link 11 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 26; a fourth connecting rod is arranged between a fourth hole and a fifth hole at the left end of the wing length plate 3; in the four-link G mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
A first hole at the front end of the wing rib 26 is connected with a fifth hole at the left end of the wing long plate 3, a second hole at the front end of the wing rib 26 is connected with a hole at the left end of the wing connecting rod 12, a first hole at the front end of the wing rib 27 is connected with a sixth hole at the left end of the wing long plate 3, a third hole at the front end of the wing rib 27 is connected with a hole at the right end of the wing connecting rod 12 to form a four-connecting-rod H mechanism, and in the four-connecting-rod H mechanism, the distance between the first hole and the second hole at the front end of the wing rib 26 is set; the wing link 12 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 27; a fourth connecting rod is arranged between a fifth hole and a sixth hole at the left end of the wing length plate 3; in the four-link H mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The first hole at the front end of the wing rib 27 is connected with the sixth hole at the left end of the wing long plate 3, the second hole at the front end of the wing rib 27 is connected with the hole at the left end of the wing connecting rod 13, the first hole at the front end of the wing rib 28 is connected with the seventh hole at the left end of the wing long plate 3, the third hole at the front end of the wing rib 28 is connected with the hole at the right end of the wing connecting rod 13 to form a four-connecting-rod I mechanism, and in the four-connecting-rod I mechanism, the distance between the first hole and the second hole at the front end of the wing rib 27 is set; the wing link 13 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 28; a fourth connecting rod is arranged between a sixth hole and a seventh hole at the left end of the wing long plate 3; in the four-link I mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The first hole at the front end of the wing rib 28 is connected with the seventh hole at the left end of the wing long plate 3, the second hole at the front end of the wing rib 28 is connected with the left end hole of the wing connecting rod 14, the first hole at the front end of the wing rib 29 is connected with the eighth hole at the left end of the wing long plate 3, the third hole at the front end of the wing rib 29 is connected with the right end hole of the wing connecting rod 14, a four-connecting-rod J mechanism is formed, and in the four-connecting-rod J mechanism, the distance between the first hole at the front end of the wing rib 28 and the second hole is set as a first; the wing link 14 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 29; a fourth connecting rod is arranged between a seventh hole and an eighth hole at the left end of the wing length plate 3; in the four-link J mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The first hole at the front end of the wing rib 29 is connected with the eighth hole at the left end of the wing long plate 3, the second hole at the front end of the wing rib 29 is connected with the left end hole of the wing connecting rod 15, the first hole at the front end of the wing rib 30 is connected with the ninth hole at the left end of the wing long plate 3, the third hole at the front end of the wing rib 30 is connected with the right end hole of the wing connecting rod 15, a four-connecting-rod K mechanism is formed, and in the four-connecting-rod K mechanism, the distance between the first hole and the second hole at the front end of the wing rib 29 is set as a first; the wing link 15 is set as a second link; a third connecting rod is arranged at the distance between the first hole and the third hole at the front end of the wing rib 30; a fourth connecting rod is arranged between the eighth hole and the ninth hole at the left end of the wing long plate 3; in the four-link K mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
A first hole at the front end of the wing rib 30 is connected with a ninth hole at the left end of the wing long plate 3, a second hole at the front end of the wing rib 30 is connected with a hole at the left end of the wing connecting rod 16, a first hole at the front end of the wing rib 31 is connected with a tenth hole at the left end of the wing long plate 3, a second hole at the front end of the wing rib 31 is connected with a hole at the right end of the wing connecting rod 16, a four-connecting-rod L mechanism is formed, and in the four-connecting-rod L mechanism, the distance between the first hole at the front end of the wing rib 30 and the second hole is set; the wing link 16 is set as a second link; a third connecting rod is arranged between the first hole and the second hole at the front end of the wing rib 33; a fourth connecting rod is arranged between a ninth hole and a tenth hole at the left end of the wing long plate 3; in the four-link L mechanism, the total length of the first link and the second link added is equal to the total length of the third link and the fourth link added.
The wing muscle falls into the multiunit with thin fin fixed connection, and thin fin front end adopts drilling riveting or butt-joint, fixes on wing muscle side boss, and the rear portion is free state, and when the wing muscle of being convenient for is crooked, follows the wing muscle and moves, and can not produce the hindrance. The front part and the rear part of the front thin fin cover the front part of the rear thin fin, so that the steam flows more smoothly on the surface. The thin wing fixing parts can be bent because of the wing ribs and are more attached to the wing ribs without deformation.
The rib and the thin fin are combined and are also considered to be fixed by adopting another winding mode. The wing rib is taken as a main body, the strip-shaped thin sheet 50 is spirally wound along one direction, the thin wing sheet 32 is inserted into the overlapped gap of each layer of winding and is fixed by a buckling mode, meanwhile, the front end on the wing rib is provided with a twisting part, the side edge protrudes and is drilled, the rear end part is also drilled and riveted to fix the front end and the rear end of the strip-shaped thin sheet 50, and the thin wing sheet 32, the strip-shaped thin sheet 50 and the wing rib are firmly fixed and cannot shift. The strip-shaped sheet 50 can be wound on the wing ribs in multiple layers, so that the thin wing panel is fixed, and the whole strength of the wing ribs is enhanced, so that the wing ribs can be made of materials with a slightly thinner thickness, and the weight of the wing ribs is properly reduced.
The four-bar linkage C, D composed of the wing ribs and the wing links is parallelogram, wherein the four-bar linkage E, F, G, H, I, L, J, K, L composed of the wing ribs and the wing links is trapezoid. The characteristics are two groups of adjacent quadrangles, wherein adjacent sides share one line, the quadrangle sharing line on the left side is a long section, and the quadrangle sharing line on the right side is a short section. Because the four-bar linkage mechanism formed by the wing ribs and the wing connecting rods meets the condition that the total lengths of two edges forming two opposite angles are equal. Therefore, in the quadrangle formed by the four-bar linkage E, F, G, H, I, J, K, L, because the length difference of the common line is adopted, the angle formed by the side of the wing rib connected with the wing long plate 3 and the wing connecting plate 1 from left to right gradually increases, and the distance between the vertexes of the quadrangle to be folded, where the angle of the two opposite angles increases, also gradually decreases.
The wing ribs and the thin wing pieces are made of elastic materials. The wing rib is characterized in that the front end of the wing rib is provided with a rotating shaft connecting hole, and the fixed wing rib simultaneously plays a role of a connecting rod. The rear part of the wing rib hole gradually becomes narrower from wide, the side edge of the wing rib hole is provided with a convex semicircular shape and is used for butt welding or drilling and riveting with a plurality of thin wing pieces to form a wing rib piece combination. Thus, the strength of the rib main body cannot be influenced by butt welding or drilling. The weight is reduced as much as possible. The front end boss of each wing rib has a torsion characteristic, so that the wing rib surface with the boss is inclined, the wing rib groups are longitudinally arranged and staggered with the upper surface and the lower surface of the adjacent wing rib group, the left wing rib group presses the wing of the right wing rib group, and each wing rib can be correspondingly overlapped after being folded, and interference can be avoided.
The rib and the thin fin are combined, and a winding and fixing mode can also be adopted. The wing rib is taken as a main body, the strip-shaped thin sheet is spirally wound along one direction, the thin wing sheet is inserted into the overlapped gap of each layer of winding and is fixed in a buckling mode, and the thin wing sheet, the strip-shaped thin sheet and the wing rib are firmly fixed and cannot shift. The strip-shaped sheet can be wound on the wing ribs in multiple layers, so that the thin wing panel is fixed, and the overall strength of the wing ribs is enhanced.
Meanwhile, the wing ribs and the thin wing pieces can be combined into a whole, the wing ribs are taken as main bodies, the thin pieces extend from two sides of the wing ribs, the appearance of the wing ribs is similar to that of bird feathers, and the wing ribs and the thin wing pieces are formed by cold extrusion of metal materials or injection molding of plastics.
The upper covering wing panel and the lower covering wing panel cover the space area of the wing connecting rod when the wing connecting rod is unfolded, so that the whole wing is connected into an integral wing surface. Wherein two sheets are in one group, seven groups are respectively arranged on the upper surface and the lower surface, and the shapes and the sizes of the corresponding positions of the upper covering fin and the lower covering fin are the same. The upper covering fins 33, 35, 37, 39, 41, 43 and 45 are first connecting rod fins, the lower covering fins 34, 36, 38, 40, 42, 44 and 46 are second connecting rod fins, the left end of each first connecting rod fin is connected with the wing connecting plate 1, the right end of each first connecting rod fin is connected with the left end of each second connecting rod fin through a hole, and the right end of each second connecting rod fin is connected with the wing long plate 3. The first connecting rod wing piece and the second connecting rod wing piece form a length and a mounting position, and each piece of the wing piece in the first connecting rod is guaranteed to be parallel to each other.
The wing connecting plate covering piece is fixed with the wing connecting plate, the wing short plate covering piece is fixed with the wing short plate, and the wing long plate covering piece is fixed with the wing long plate.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. A deployable flexible wing, comprising: the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod, the wing rib, the thin wing panel, the upper covering wing panel and the lower covering wing panel;
the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod, the wing rib, the thin wing panel, the upper covering wing panel and the lower covering wing panel are connected through shaft holes; the wing connecting plate, the wing short plate, the wing long plate, the wing connecting rod and the wing rib are combined in a planar four-bar linkage manner;
the wing connecting plate is connected with the body and the wing driving mechanism, the wing driving mechanism inputs reciprocating thrust to push the wing short plate to swing around a shaft, and the wing short plate drives a plurality of plane four-bar mechanisms consisting of the wing long plate, the wing connecting rods and the wing ribs to finish the folding and unfolding actions of the wings;
the adjacent sides of two adjacent quadrangles of the four-bar linkage E, F, G, H, I, L, J, K, L share one line, and the shared line is a long side and a short side on the two adjacent quadrangles respectively.
2. The deployable flexible wing of claim 1, wherein the four-bar linkage C and four-bar linkage D of the rib and the wing link are parallelogram shaped.
3. The deployable flexible wing of claim 1, wherein the four bar linkage E, F, G, H, I, L, J, K, L formed by the rib and the wing link is a trapezoid.
4. The deployable flexible wing of claim 1, wherein the wing attachment panel, the wing links, and the wing stub panel form a four-bar linkage a and a four-bar linkage B, and the two edges of the four-bar linkage A, B, E, F, G, H, I, L, J, K, L with two opposite corners having larger angles have equal total lengths after being added together.
5. The flexible wing as claimed in claim 1, wherein the rib and the thin wing are made of flexible material, the front end of the rib has a shaft connecting hole, the shaft connecting hole gradually narrows from width to width, and the side edge has a convex semi-circular shape, and is fixedly connected with the thin wing to form a rib combination.
6. The deployable flexible wing of claim 5, wherein the rib and the thin panel are combined in a wound fastening arrangement.
7. The deployable flexible wing of claim 5, wherein the rib and the thin flaps are integral, the rib being the main body and the thin flaps extending from both sides of the rib and being formed by cold extrusion or injection molding of a metal material.
8. The deployable flexible wing of claim 1, wherein the upper cover flap and the lower cover flap have a plurality of flaps covering the wing links to allow the entire wing to be connected as a unitary wing when deployed.
9. The deployable flexible wing of claim 1, wherein the wing attachment panel is fixedly attached to the wing attachment panel overlay, the tab panel is fixedly attached to the tab panel overlay, and the tab panel is fixedly attached to the tab panel overlay.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910081715.7A CN109760833B (en) | 2019-01-28 | 2019-01-28 | Foldable elastic wing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910081715.7A CN109760833B (en) | 2019-01-28 | 2019-01-28 | Foldable elastic wing |
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| CN109760833A CN109760833A (en) | 2019-05-17 |
| CN109760833B true CN109760833B (en) | 2020-10-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP7254347B2 (en) * | 2019-08-27 | 2023-04-10 | 国立研究開発法人宇宙航空研究開発機構 | Morphing wing, flight control device, flight control method, and program |
| JP2023009836A (en) * | 2021-07-08 | 2023-01-20 | 国立研究開発法人宇宙航空研究開発機構 | Morphing wing, flight control apparatus, flight control method, and program |
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| GB289829A (en) * | 1927-05-03 | 1928-10-25 | Heinrich Grunewald | Flying apparatus |
| FR2991665B1 (en) * | 2012-06-08 | 2014-10-24 | Guy Roger Leroy | ORNITHOPTERE INTENDED TO EXPERIMENT BATTU FLIGHT AND ADAPT IT TO MAN |
| CN106364672A (en) * | 2016-10-21 | 2017-02-01 | 沈小沉 | Ornithopter with elastic wings |
| CN206255193U (en) * | 2016-10-21 | 2017-06-16 | 胡高 | Elastic wing |
| CN107719633A (en) * | 2017-09-06 | 2018-02-23 | 徐国祥 | The wing and collapsible suspension formula aircraft of collapsible suspension formula aircraft |
| CN108945431A (en) * | 2018-07-23 | 2018-12-07 | 西北工业大学 | The imitative birds of flapping-wing aircraft and the folding wing of bat |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB289829A (en) * | 1927-05-03 | 1928-10-25 | Heinrich Grunewald | Flying apparatus |
| FR2991665B1 (en) * | 2012-06-08 | 2014-10-24 | Guy Roger Leroy | ORNITHOPTERE INTENDED TO EXPERIMENT BATTU FLIGHT AND ADAPT IT TO MAN |
| CN106364672A (en) * | 2016-10-21 | 2017-02-01 | 沈小沉 | Ornithopter with elastic wings |
| CN206255193U (en) * | 2016-10-21 | 2017-06-16 | 胡高 | Elastic wing |
| CN107719633A (en) * | 2017-09-06 | 2018-02-23 | 徐国祥 | The wing and collapsible suspension formula aircraft of collapsible suspension formula aircraft |
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| CN109760833A (en) | 2019-05-17 |
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