CN109760833A - Can take down the exhibits resilient wing - Google Patents
Can take down the exhibits resilient wing Download PDFInfo
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- CN109760833A CN109760833A CN201910081715.7A CN201910081715A CN109760833A CN 109760833 A CN109760833 A CN 109760833A CN 201910081715 A CN201910081715 A CN 201910081715A CN 109760833 A CN109760833 A CN 109760833A
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Abstract
The present invention relates to be used for can take down the exhibits resilient wing, including wing connecting plate, wing short slab, chord plate, wing connecting rod, wing muscle, thin wing piece, upper covering fin, lower covering fin in aircraft field；The wing connecting plate, the wing short slab, the chord plate, the wing connecting rod, the wing muscle, the thin wing piece, the upper covering fin, the lower covering fin are connected by axis hole；The wing connecting plate, the wing short slab, the chord plate, the wing connecting rod, the wing muscle are combined in the form of lanar four rod mechanism between each other, wing connecting plate is connect with fuselage and wing driving mechanism, wing driving mechanism inputs reciprocating thrust force, it pushes wing short slab to do to swing around axis, wing short slab drives multiple lanar four rod mechanisms of chord plate, wing connecting rod and wing muscle composition, completes the movement that wing collapses and is unfolded.The present invention can minimize the resistance that wing during flapping flight raises up when acting, while wing parking space can be maximumlly saved when aircraft is parked.
Description
Technical field
The present invention relates to one kind to be suitable for flapping wing and Fixed Wing AirVehicle apparatus field, specifically, being related to one kind can take down the exhibits
Resilient wing.
Background technique
Flapping wing aircraft is a kind of a kind of aircraft that flight can be realized by the wing fluttered up and down, existing at present
Aircraft in, not can solve wing generally when raising up, downward reaction force brought, so that fuselage is in flight course
There is the phenomenon to float up and down, and fuselage is caused to tremble.It cannot the steady flexible flight completely as bird.This is solved to ask
Topic, it is necessary to which wing also can accomplish the movement collapsed and be unfolded as pinion in flight course.Flight can not be eliminated
When float up and down that tremble this with fuselage be the big factors for hindering flapping wing aircraft progress in practical and aircraft industry,
Very greatly the reason is that since there is presently no the movements that the wing of a functionization can accomplish gathering and expansion.
Simultaneously because existing bat rotor aircraft wing flexibly cannot be unfolded and collapse as pinion, so that flight speed
Degree is universal all relatively slow.
A SmartBird that Festo scientific & technical corporation develops is can either to simulate Bird Flight also can realistically flutter
The Bird robot of wing.The wing of SmartBird can be patted up and down, while can also twist by special angle, be this ultralight machine
Device bird assigns outstanding aerodynamic quality and agility.But the wing of this Bird robot cannot be collapsed and be opened up as pinion
It opens, when wing raises up in flight course, acts on the downward power of fuselage, reaction is big so that fuselage sinks, and causes machine
Body trembling is more severe, can not accomplish smooth flight as birds.
Through the retrieval to the prior art, Chinese invention patent CN201610692704.9, a kind of entitled present invention
A kind of flapping wing aircraft is disclosed, the technical solution in aircraft field, including rotation crankshaft group, two interlocking bar, two are belonged to
A transmission module and installation axle；Rotation crankshaft group is set there are two crankshaft, and it is opposite that two crankshafts are respectively arranged on rotation crankshaft group
Two sides on；One end of two interlocking bar couples with a crankshaft axis respectively, the other end of two interlocking bar respectively with one
The connection of transmission module axis；Two transmission modules couple with installation axle axis, are equipped with flapping wing on each transmission module；Rotate crankshaft
Component for driving interlocking bar march pendular motion, interlocking bar for drive two transmission modules around installation axle carry out mutually from and phase
To movement, transmission module is for driving flapping wing to carry out flapping motion.Gear is needed to realize repeatedly transmission compared with the existing technology, this
Invention reduces transmission number, so that the transmitting of power is more directly rapidly, so that transmission efficiency is improved, so that flapping wing aircraft
Flying for long time be achieved.But the invention cannot minimize the resistance that wing during flapping flight raises up when acting
Power can not maximumlly save wing parking space when aircraft is parked.
Summary of the invention
In view of the drawbacks of the prior art, it can take down the exhibits resilient wing the object of the present invention is to provide one kind.The present invention can be maximum
Wing raises up resistance when acting during limit reduces flapping flight, while can maximumlly save when aircraft is parked
Wing parking space.
Can take down the exhibits resilient wing the present invention relates to one kind, comprising: wing connecting plate, wing short slab, chord plate, wing connecting rod, wing muscle,
Thin wing piece, upper covering fin, lower covering fin；
The wing connecting plate, the wing short slab, the chord plate, the wing connecting rod, the wing muscle, the thin wing piece,
The upper covering fin, the lower covering fin are connected by axis hole；The wing connecting plate, the wing short slab, the chord plate,
The wing connecting rod, the wing muscle are combined in the form of lanar four rod mechanism between each other；
The wing connecting plate is connect with fuselage and wing driving mechanism, and wing driving mechanism inputs reciprocating thrust force, is pushed
The wing short slab is done to be swung around axis, and the wing short slab drives the more of the chord plate, the wing connecting rod and wing muscle composition
A lanar four rod mechanism completes the movement that wing collapses and is unfolded.
Preferably, the wing muscle is parallel four side with four-bar mechanism C composed by the wing connecting rod with four-bar mechanism D
Shape.
Preferably, the wing muscle is not advise with four-bar mechanism E, F, G, H, I, L, J, K, L composed by the wing connecting rod
Then quadrangle.
Preferably, two groups of described four-bar mechanism E, F, G, H, I, L, J, K, L adjacent quadrangle adjacent side share one lines,
Its bridging line is respectively long side and short side on adjacent two quadrangle.
Preferably, the wing connecting plate, the wing connecting rod and the wing short slab form four-bar mechanism A, four-bar mechanism
Total length after two sides that two diagonal angles become larger in B, described four-bar mechanism E, F, G, H, I, L, J, K, L are respectively added
It is equal.
Preferably, the wing muscle and the thin wing piece are made of elastic material, and there is shaft connecting hole in wing muscle front end,
The shaft connecting hole is become narrow gradually by width, and there is raised semi-circular shape in side, is fixedly connected to form a wing with the thin wing piece
The combination of muscle piece.
Preferably, the wing muscle and the thin wing piece are combined using the mode of being fastened.
Preferably, the wing muscle and the thin wing piece are integral type, and based on the wing muscle, the thin wing piece is from described
Wing muscle two sides extend, and are shaped with metal material cold-extrusion shaping or plastic injection.
Preferably, the upper covering fin, the lower covering fin fin that there is multi-disc to cover wing connecting rod, when expansion
Entire wing is allowed to be linked to be whole aerofoil.
Preferably, the wing connecting plate is fixedly connected with wing connecting plate emulsion sheet, and it is short that the wing short slab is fixedly connected with the wing
Plate emulsion sheet, the chord plate are fixedly connected with chord plate emulsion sheet.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, can take down the exhibits resilient wing its structure of the present invention is to utilize plane double leval jib principle, drive wing short slab, wing connecting rod, chord
Plate and resilient wing muscle, the movement of gathering and expansion is finally reached by shaft swing angle.It thus can be entire aerofoil point
At multiple fins, the overlapping combinations of a movable thin slice are then re-formed, aerofoil is allowed to change machine according to actual conditions when flight
The degree that the wing is taken down the exhibits can maximumlly reduce flight resistance.Simultaneously when wing raises up, collapses wing and reduce when raising up
Reaction force, dipping and heaving when mitigating flight make flight more steady.Since wing can collapse expansion, also aircraft is allowed to account for
Become smaller with parking space.
2, the Thin Elastic fin of the resilient wing of the invention that can take down the exhibits is fixed on resilient wing muscle and forms the combination of wing muscle piece, front end
It is fixed by hole axle, at free state, the combination of wing muscle is all made of elastic material for rear end, and wing muscle piece can be allowed to combine to be formed
Aerofoil has plastic deformation ability, can be with the change aerofoil state of adaptivity.Wing muscle piece combines front end intensity height and and the wing
Connecting rod connection, wing muscle more narrower weakened and at free state to the back-end, is clapped when wing frequency is accelerated because of stress, wing muscle front end
Bending always is generated with rear end, front and back end when clapping the wing forms drop, and entire aerofoil is allowed to generate twisting action, finally claps upper and lower
The power of the wing is transformed into thrust backward.
3, the wing muscle piece group longitudinal arrangement of the resilient wing of the invention that can take down the exhibits, due to having one at the boss of resilient wing muscle front end
Torsional characteristics, allow have boss wing muscle face generate inclination, so that wing muscle piece group is staggered with adjacent foil muscle piece group top and bottom, when wing to
When lower bat, left winger muscle piece group pushes down outside right forward muscle piece group tab closure air-flow, then generates lift by wing muscle power transmission to fuselage, together
When can also higher efficiency generation backward thrust.And allow fin free bend just when wing raises up, air filtering can be crossed, most
The mitigation changed greatly raises up resistance.The elastic aerofoil that wing muscle piece group is formed, can adaptively distort, while elastic aerofoil also can be very big
Slow down in degree since power of the external airflow function on aerofoil is transmitted on aircraft fuselage.The superiority for the resilient wing that can take down the exhibits
So that flapping wing aircraft can in-flight be accomplished, equally flexibly fly closer to birds.
4, the present invention can take down the exhibits resilient wing large area using thin slice, lighter than traditional stressed-skin construction, simultaneously as resilient wing
Piece rear end is free state, does not have to worry that intensity not enough leads to the problem of tearing, the dispersion of fin, rear end is at free state.
It is not linked to be entirety, has also dispersed the stress of aerofoil, so that every fin all will not be too big because of stress, it is more than fin intensity itself
It loading and tears, fin can be made very thin very light, greatly mitigate wing weight, and the wing the light thin, and center of gravity concentrates fuselage,
It is more stable, convenient for flight control.
5, the present invention can take down the exhibits, and resilient wing is more preferable safely, and resilient wing muscle uses elastic material good toughness, because of wing muscle piece group
It is independent from each other, a piece of entire effect of fatigue fracture is little.If accidentally bumping against aerofoil, only situation damage or deformation,
Without having the danger being entirely broken as the monoblock type wing.It is more flexible that the resilient wing that can take down the exhibits awing copes with air-flow variation.When
Crosswind, beam wind, sinuous flow, selection and the control for collapsing and being unfolded degree are coped with, flight is allowed to become more freedom and flexibility.
6, the present invention resilient wing that can take down the exhibits is readily applicable to Fixed Wing AirVehicle, different from traditional variable swept back wing, can be changed
Swept-back wing only changes wing setting, but cannot change wing span area, and the resilient wing that can take down the exhibits is according to different flight moulds
Formula (take off, land, put down and fly, and accelerate) selects different span degree, changes wing span area, the elastic aerofoil peace of composition
Full property and practicability are very strong, advantageously than traditional wing.
7, the present invention elastic wing structure that can take down the exhibits is simple, is mostly that hole axle mode connects, not to the required precision of processing and manufacturing
Height, practical, easy to process, required precision can both be met by being able to use standard machinery processing, realize structure assembling.It is processed
At low cost, later period maintenance replacement is convenient.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is that the present invention implements assembling schematic diagram；
Fig. 2 is that the present invention implements to cover fin assembling schematic diagram up and down；
Fig. 3 is that the present invention implements thin wing piece assembling schematic diagram；
Fig. 4 is that the present invention implements Standard schematic diagram；
Fig. 5 is that the present invention implements link mechanism composition schematic diagram；
Fig. 6 is that the present invention implements axonometric drawing；
Fig. 7 is that the present invention implements schematic diagram at wing sprain of muscle and tendon turn；
Fig. 8 is that the present invention implements wing rounding state figure；
Fig. 9 is the mode figure that is fastened that the present invention implements wing muscle and thin wing piece.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
Embodiment
In view of the above demand, can take down the exhibits resilient wing the present invention relates to one kind, including wing connecting plate, wing short slab, chord plate,
Multiple wing connecting rods, thin wing piece, cover fin at wing muscle up and down, are composed by axis hole connection.Its wing centre section connecting plate, wing short slab,
Chord plate, wing muscle, is combined in the form of lanar four rod mechanism between each other at multiple wing connecting rods, and interrelated constraint.
The mechanisms of all composition double leval jibs are regarded as quadrangle, to complete two diagonal angles is to open to become larger and vertex distance
Become smaller, the diagonal angle of another two is to reduce and the quadrangle closing action that becomes larger of vertex distance is it is necessary to meeting: composition two
Two sides that diagonal angle becomes larger, being respectively added total length is equal condition.For example, such as 1 front end of wing connecting plate
The connection of 2 left end hole of Kong Yuyi short slab, the connection of 1 second Kong Yuyi connecting rod of wing connecting plate, 4 left end hole, 5 front end of wing connecting rod and the wing are short
The connection of 2 interstitial hole of plate, 5 rear end of wing connecting rod are connect with 4 right end hole of wing connecting rod, form double leval jib A mechanism.In composition double leval jib A machine
In structure, 2 left end hole of wing short slab and interstitial hole are away from being set as first connecting rod；1 front aperture of wing connecting plate and the second pitch-row are set as second
Connecting rod；Wing connecting rod 4 is set as third connecting rod；Wing connecting rod 5 is set as fourth link；In double leval jib A mechanism, first connecting rod and second connects
The overall length that bar is added is equal to the overall length that third connecting rod is added with fourth link.It just can guarantee double leval jib A mechanism in this way, it is dynamic closing up
First connecting rod connect the angle to be formed with second connecting rod and becomes larger when making, and third connecting rod connect the angle to be formed with fourth link and also becomes
Greatly, minimum can be brought together by vertex distance being connected between them.Final all wing connecting rods associated therewith and resilient wing, muscle group
At four-bar mechanism, can flexibly complete closing action.
To achieve the above object, including wing connecting plate 1, wing short slab 2,3,13 wing connecting rod 4-16 of chord plate, 15 wings
Muscle 17-31, multiple thin wing pieces and array cover fin up and down.Wing connecting plate 1, wing short slab 2, chord plate 3, wing connecting rod, the wing
Muscle, up and down covering fin are composed by axis hole connection.Each connecting portion is the pass that can freely swing
Section.Its wing centre section connecting plate 1, chord plate 3, wing connecting rod, wing muscle, is all between each other in the form of lanar four rod mechanism at wing short slab 2
In conjunction with, and interrelated constraint.Wing connecting plate 1 is connect with fuselage, provides power drive wing short slab 2 before axial direction by fuselage
Certain angle is swung, wing short slab 2 drives chord plate 3 and all wing connecting rods, wing muscle to complete four-bar mechanism closing action.
The wing connecting plate 1 respectively has three layers with 3 upper and lower surface of chord plate, and intermediate one layer of installation wing connecting rod, wing muscle and the wing are short
Plate 2 is the double leval jib zone of action for realizing main actions, and the second layer installs lower covering fin, covers wing by multi-disc and connects
Space region when bar is unfolded, allows entire airfoil to be linked to be whole aerofoil.About 1 first layer of wing connecting plate installation wing connecting plate covers
Cover plate 47, about 3 first layer of chord plate install chord plate emulsion sheet 49, and wing short slab emulsion sheet 48 is mounted on 2 top and bottom of wing short slab,
It and is all same plane, for covering the null region for covering fin junction up and down of the second layer.
2 interstitial hole of wing short slab is connect with 5 front end of wing connecting rod, and 2 right end hole of wing short slab and chord plate the first hole of 3 left end connect
It connects, wherein 3 left end the second Kong Yuyi connecting rod of chord plate, 6 right end connects, and 5 rear end of wing connecting rod is connect with 6 left end of wing connecting rod, forms
Double leval jib B mechanism is set as first connecting rod in 2 interstitial hole of double leval jib B mechanism wing centre section short slab and right end pitch-row；Wing connecting rod 5 is set as
Two connecting rods；Wing connecting rod 6 is set as third connecting rod；3 left end hole of chord plate and the second pitch-row are set as fourth link；In double leval jib B mechanism
In, the overall length that first connecting rod is added with second connecting rod is equal to the overall length that third connecting rod is added with fourth link.
4 left end Kong Yuyi connecting plate of wing connecting rod, 1 second hole connects, after the 7 left end Kong Yuyi connecting plate 1 of wing connecting rod
Stomidium connection, the connection of 4 right end Kong Yuyi muscle of wing connecting rod, 19 front aperture, the connection of 7 right end Kong Yuyi muscle of wing connecting rod the second hole of 19 front end
A double leval jib C mechanism is formed, each length of connecting rod is set as two groups of equal parallelogram of opposite side.Wherein wing connecting rod 4 with
The connection of 17 wing muscle 18 of wing muscle, both wings muscle front aperture and 4 interstitial hole of wing connecting rod are further added by the case where intermediate two hole of equal part of wing connecting rod 7
Connection, 7 interstitial hole of both wings muscle front end the second Kong Yuyi connecting rod connection, due to the equal double leval jib C mechanism characteristics of two opposite side, can allow
In four-bar mechanism swing process, guarantees that 17 wing muscle of wing muscle, 18 wing muscle 19 is parallel with wing connecting plate 1 always, reach aerofoil and took down the exhibits
Each wing muscle will not interfere in journey.
6 left end Kong Yuyi muscle of wing connecting rod, the 19 front aperture connection, 8 left end Kong Yuyi muscle of wing connecting rod the second hole of 19 front end connects
It connects, the connection of 6 right end Kong Yuyi muscle of wing connecting rod, 23 front aperture, the connection of 8 right end Kong Yuyi muscle of wing connecting rod the second hole of 23 front end forms one
A double leval jib D mechanism, each length of connecting rod are set as two groups of equal parallelogram of opposite side.Wherein in wing connecting rod 6 and wing connecting rod 8
The connection of 20 wing muscle of wing muscle, 21 wing muscle 22, three wings muscle front aperture and 6 interstitial hole of wing connecting rod are further added by the case where intermediate three hole of equal part
Connection, 8 interstitial hole of three wings muscle front end the second Kong Yuyi connecting rod connection, due to the equal double leval jib D mechanism characteristics of two opposite side, can allow
In four-bar mechanism swing process, it is parallel always with wing connecting rod 8 not only to have guaranteed wing connecting rod 6, but also can guarantee 19 wing muscle of wing muscle, 20 wing muscle
21 wing muscle, 22 wing muscle 23 is parallel with wing connecting plate 1 always, and reaching each wing muscle during aerofoil is taken down the exhibits will not interfere.
Wing muscle 23 front end, first hole is connect with the second hole of 3 left end of chord plate, 23 front end third Kong Yuyi connecting rod 9 of wing muscle
The connection of left end hole, wing muscle the first hole of 24 front end are connect with 3 left end third hole of chord plate, 24 front end third Kong Yuyi connecting rod 9 of wing muscle
The connection of right end hole, forms a double leval jib E mechanism, in double leval jib E mechanism, wing muscle the first hole of 23 front end is set as with third pitch-row
First connecting rod；Wing connecting rod 9 is set as second connecting rod；Wing muscle the first hole of 24 front end and third pitch-row are set as third connecting rod；Chord plate 3 is left
The second hole and third pitch-row is held to be set as fourth link；In double leval jib E mechanism, overall length etc. that first connecting rod is added with second connecting rod
In the overall length that third connecting rod is added with fourth link.
Wing muscle 24 front end, first hole is connect with 3 left end third hole of chord plate, 24 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 10 left ends hole, wing muscle the first hole of 25 front end are connect with the 4th hole of 3 left end of chord plate, 25 front end third Kong Yuyi connecting rod of wing muscle
The connection of 10 right end holes, forms a double leval jib F mechanism, in double leval jib F mechanism, wing muscle the first hole of 24 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 10 is set as second connecting rod；Wing muscle the first hole of 25 front end and third pitch-row are set as third connecting rod；Chord plate
3 left ends third hole and the 4th pitch-row are set as fourth link；In double leval jib F mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 25 front end, first hole is connect with the 4th hole of 3 left end of chord plate, 25 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 11 left ends hole, wing muscle the first hole of 26 front end are connect with the 5th hole of 3 left end of chord plate, 26 front end third Kong Yuyi connecting rod of wing muscle
The connection of 11 right end holes, forms a double leval jib G mechanism, in double leval jib G mechanism, wing muscle the first hole of 25 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 11 is set as second connecting rod；Wing muscle the first hole of 26 front end and third pitch-row are set as third connecting rod；Chord plate
3 the 4th Kong Yu of left end, five pitch-row is set as fourth link；In double leval jib G mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 26 front end, first hole is connect with the 5th hole of 3 left end of chord plate, 26 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 12 left ends hole, wing muscle the first hole of 27 front end are connect with the 6th hole of 3 left end of chord plate, 27 front end third Kong Yuyi connecting rod of wing muscle
The connection of 12 right end holes, forms a double leval jib H mechanism, in double leval jib H mechanism, wing muscle the first hole of 26 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 12 is set as second connecting rod；Wing muscle the first hole of 27 front end and third pitch-row are set as third connecting rod；Chord plate
3 the 5th Kong Yu of left end, six pitch-row is set as fourth link；In double leval jib H mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 27 front end, first hole is connect with the 6th hole of 3 left end of chord plate, 27 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 13 left ends hole, wing muscle the first hole of 28 front end are connect with 3 left end seven apertures in the human head of chord plate, 28 front end third Kong Yuyi connecting rod of wing muscle
The connection of 13 right end holes, forms a double leval jib I mechanism, in double leval jib I mechanism, wing muscle the first hole of 27 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 13 is set as second connecting rod；Wing muscle the first hole of 28 front end and third pitch-row are set as third connecting rod；Chord plate
The 6th Kong Yu seven apertures in the human head of 3 left end is away from being set as fourth link；In double leval jib I mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 28 front end, first hole is connect with 3 left end seven apertures in the human head of chord plate, 28 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 14 left ends hole, wing muscle the first hole of 29 front end are connect with 3 left end octal of chord plate, 29 front end third Kong Yuyi connecting rod of wing muscle
The connection of 14 right end holes, forms a double leval jib J mechanism, in double leval jib J mechanism, wing muscle the first hole of 28 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 14 is set as second connecting rod；Wing muscle the first hole of 29 front end and third pitch-row are set as third connecting rod；Chord plate
3 left end seven apertures in the human heads and octal are away from being set as fourth link；In double leval jib J mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 29 front end, first hole is connect with 3 left end octal of chord plate, 29 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 15 left ends hole, wing muscle the first hole of 30 front end are connect with the 9th hole of 3 left end of chord plate, 30 front end third Kong Yuyi connecting rod of wing muscle
The connection of 15 right end holes, forms a double leval jib K mechanism, in double leval jib K mechanism, wing muscle the first hole of 29 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 15 is set as second connecting rod；Wing muscle the first hole of 30 front end and third pitch-row are set as third connecting rod；Chord plate
3 left end octals and the 9th pitch-row are set as fourth link；In double leval jib K mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
Wing muscle 30 front end, first hole is connect with the 9th hole of 3 left end of chord plate, 30 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 16 left ends hole, wing muscle the first hole of 31 front end are connect with the tenth hole of 3 left end of chord plate, 31 front end the second Kong Yuyi connecting rod of wing muscle
The connection of 16 right end holes, forms a double leval jib L mechanism, in double leval jib L mechanism, wing muscle the first hole of 30 front end is set with the second pitch-row
For first connecting rod；Wing connecting rod 16 is set as second connecting rod；Wing muscle the first hole of 33 front end and the second pitch-row are set as third connecting rod；Chord plate
3 the 9th Kong Yu of left end, ten pitch-row is set as fourth link；In double leval jib L mechanism, first connecting rod is added total with second connecting rod
The long overall length for being equal to third connecting rod and being added with fourth link.
The wing muscle is fixedly connected with thin wing piece is divided into multiple groups, and thin wing piece front end is fixed on using drilling riveting or butt-joint
On the boss of wing muscle side, rear portion is free state, and when convenient for the bending of wing muscle, and then wing muscle is moved, without generating obstruction.Thin wing
A piece of rear portion point overlapping covers the preceding part of a piece of thin wing piece below before piece, allows steam flow to flow through on surface more smoothly.Thin wing piece
It can be bent because of wing muscle between fixed part, more be bonded with wing muscle without being deformed.
The wing muscle and thin sail combination, it is also considered that fixed by the way of another kind winding.Based on wing muscle, utilize
Strip thin slice 50, along a direction at screw type winding, thin wing piece 32 is inserted at each layer of lap clearance of winding, and
It is fixed using snap, while the front end on wing muscle has side at torsion to protrude and drill, rearward end also drills riveting
It connects and fixes 50 rear and front end of strip thin slice, allow thin wing piece 32, strip thin slice 50 and wing muscle is fixed will not generate shifting
Position.Strip thin slice 50 can enwind wing muscle with multilayer, not only fix thin wing piece and also act as strengthening wing muscle integral strength
Effect, the material for allowing wing muscle thickness slightly thinner make, with the weight appropriate for mitigating wing muscle.
The wing muscle is parallel four side row, wing centre section muscle and wing connecting rod institute with four-bar mechanism C, D composed by wing connecting rod
Four-bar mechanism E, F, G, H, I, L, J, K, L of composition are irregular quadrilateral.Its characteristic is two groups of adjacent quadrangles, in phase
Adjacent side is share one line, and the quadrangle bridging line on the left side takes long one section, and the quadrangle bridging line on the right takes short one
Section.Because of four-bar mechanism composed by wing muscle and wing connecting rod, to meet two sides that two diagonal angles of composition become larger, respectively
It is equal condition from total length is added.So in quadrangle composed by four-bar mechanism E, F, G, H, I, J, K, L, because sharing
Line takes length difference, that a line of wing muscle connecting with chord plate 3 can be gradually by the left-to-right angle formed with wing connecting plate 1
Become larger, the quadrangle to be closed up, the vertex distance that two diagonal angles become larger also gradually becomes smaller.
The wing muscle, thin wing piece are made of elastic material.Wing muscle feature is that front end has shaft connecting hole, and fixed-wing muscle is same
When play the role of connecting rod.Part gradually narrows from the width behind wing muscle hole, and there is raised semi-circular shape in side, is used to and multiple thin wing pieces
Butt-joint or drilling riveting form a wing muscle piece combination.Ensure that in this way will not because of butt-joint or drilling to influence wing muscle main body strong
Degree.Mitigate weight as far as possible.A torsional characteristics are had at the boss of each wing muscle front end, the wing muscle face for having boss is allowed to generate
Inclination, makes wing muscle piece group longitudinal arrangement and is staggered with adjacent foil muscle piece group top and bottom, left winger muscle piece group pushes down right flank muscle piece
The fin of group, so that each wing muscle can correspond to overlapping after gathering, without interfering.
The wing muscle and thin sail combination, can also be using the mode that is fastened.It is thin using strip based on wing muscle
Piece, along a direction at screw type winding, thin wing piece is inserted at each layer of lap clearance of winding, and utilizes snap
It fixes, allows thin wing piece, strip thin slice and wing muscle is fixed will not generate displacement.Strip thin slice can be with the winding of multilayer
Firmly wing muscle not only fixes the effect that thin wing piece also acts as strengthening wing muscle integral strength.
Wing muscle and thin sail combination also can be made integral type simultaneously, and based on wing muscle, thin slice extends from wing muscle two sides
It comes, shape is similar to birds remex, is shaped with metal material cold-extrusion shaping or plastic injection.
The covering fin up and down is covered the space region when expansion of wing connecting rod by multi-disc, and entire wing is allowed to be linked to be entirety
Aerofoil.Wherein two panels is one group, and each seven groups of upper and lower surface, the geomery for covering fin corresponding position up and down is identical.With more
The connection type of connecting rod connects, and upper covering fin 33,35,37,39,41,43,45 is first connecting rod fin, lower covering fin 34,
36,38,40,42,44,46 be second connecting rod fin, and first connecting rod fin left end connects wing connecting plate 1, and right end and second connect
The connection of bar fin left end through hole, second connecting rod fin right end are connect with chord plate 3.First connecting rod fin and second connecting rod fin
Length and installation site are formed, guarantees the fin in first connecting rod per a piece of all parallel to each other.
The wing connecting plate emulsion sheet is fixed with wing connecting plate, and wing short slab emulsion sheet is fixed with wing short slab, chord plate
Emulsion sheet is fixed with chord plate.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
- The resilient wing 1. one kind can take down the exhibits characterized by comprising wing connecting plate, wing short slab, chord plate, wing connecting rod, wing muscle, Thin wing piece, upper covering fin, lower covering fin；It is the wing connecting plate, the wing short slab, the chord plate, the wing connecting rod, the wing muscle, the thin wing piece, described Upper covering fin, the lower covering fin are connected by axis hole；It is the wing connecting plate, the wing short slab, the chord plate, described Wing connecting rod, the wing muscle are combined in the form of lanar four rod mechanism between each other；The wing connecting plate is connect with fuselage and wing driving mechanism, wing driving mechanism input reciprocating thrust force, described in promotion Wing short slab is done to be swung around axis, and the wing short slab drives the multiple flat of the chord plate, the wing connecting rod and wing muscle composition Face four-bar mechanism completes the movement that wing collapses and is unfolded.
- 2. resilient wing according to claim 1 of taking down the exhibits, characterized in that four companies of the wing muscle and wing connecting rod composition Linkage C and four-bar mechanism D is parallelogram.
- 3. resilient wing according to claim 1 of taking down the exhibits, characterized in that four composed by the wing muscle and the wing connecting rod Link mechanism E, F, G, H, I, L, J, K, L are irregular quadrilateral.
- 4. resilient wing according to claim 3 of taking down the exhibits, characterized in that the four-bar mechanism E, F, G, H, I, L, J, K, Two groups of L adjacent quadrangle adjacent side share one lines, bridging line are respectively long side and short side on adjacent two quadrangle.
- 5. resilient wing according to claim 4 of taking down the exhibits, characterized in that the wing connecting plate, the wing connecting rod with it is described Wing short slab form four-bar mechanism A, in four-bar mechanism B, described four-bar mechanism A, B, E, F, G, H, I, L, J, K, L two it is right Total length is equal after two sides that the angle at angle becomes larger respectively are added.
- 6. resilient wing according to claim 1 of taking down the exhibits, characterized in that the wing muscle and the thin wing piece are using elastic material There are shaft connecting hole in material production, wing muscle front end, and the shaft connecting hole is become narrow gradually by width, and there is raised semicircle in side Shape is fixedly connected to form a wing muscle piece with the thin wing piece and combines.
- 7. resilient wing according to claim 6 of taking down the exhibits, characterized in that the wing muscle and the thin wing piece are solid using winding Determine mode to combine.
- 8. resilient wing according to claim 6 of taking down the exhibits, characterized in that the wing muscle and the thin wing piece are integral type, Based on the wing muscle, the thin wing piece extends from wing muscle two sides, with metal material cold-extrusion shaping or plastic injection Forming.
- 9. resilient wing according to claim 1 of taking down the exhibits, characterized in that the upper covering fin, the lower covering fin There is multi-disc to cover the fin of wing connecting rod, when expansion allows entire wing to be linked to be whole aerofoil.
- 10. resilient wing according to claim 1 of taking down the exhibits, characterized in that the wing connecting plate is fixedly connected with wing company Fishplate bar emulsion sheet, the wing short slab are fixedly connected with wing short slab emulsion sheet, and the chord plate is fixedly connected with chord plate emulsion sheet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081715.7A CN109760833B (en) | 2019-01-28 | 2019-01-28 | Foldable elastic wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910081715.7A CN109760833B (en) | 2019-01-28 | 2019-01-28 | Foldable elastic wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109760833A true CN109760833A (en) | 2019-05-17 |
| CN109760833B CN109760833B (en) | 2020-10-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910081715.7A Active CN109760833B (en) | 2019-01-28 | 2019-01-28 | Foldable elastic wing |
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| JP2021030950A (en) * | 2019-08-27 | 2021-03-01 | 国立研究開発法人宇宙航空研究開発機構 | Morphing wing, flight controller, flight control method, and program |
| WO2023282278A1 (en) * | 2021-07-08 | 2023-01-12 | 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 |
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| JP2021030950A (en) * | 2019-08-27 | 2021-03-01 | 国立研究開発法人宇宙航空研究開発機構 | Morphing wing, flight controller, flight control method, and program |
| WO2021039209A1 (en) * | 2019-08-27 | 2021-03-04 | 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 |
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| GB2601088B (en) * | 2019-08-27 | 2023-10-04 | Japan Aerospace Exploration | Morphing wing, flight control device, flight control method, and program |
| US11993372B2 (en) | 2019-08-27 | 2024-05-28 | Japan Aerospace Exploration Agency | Morphing wing, flight control device, flight control method, and storage medium |
| WO2023282278A1 (en) * | 2021-07-08 | 2023-01-12 | 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 |
| GB2623227A (en) * | 2021-07-08 | 2024-04-10 | Japan Aerospace Exploration | Morphing wing, flight control device, flight control method, and program |
| GB2623227B (en) * | 2021-07-08 | 2025-02-12 | Japan Aerospace Exploration | Morphing wing, flight control device, flight control method, and program |
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| Publication number | Publication date |
|---|---|
| CN109760833B (en) | 2020-10-09 |
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