CN206255193U - Elastic wing - Google Patents
Elastic wing Download PDFInfo
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- CN206255193U CN206255193U CN201621146865.XU CN201621146865U CN206255193U CN 206255193 U CN206255193 U CN 206255193U CN 201621146865 U CN201621146865 U CN 201621146865U CN 206255193 U CN206255193 U CN 206255193U
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- elastic
- wing
- body frame
- rib
- aerofoil
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Abstract
The utility model provides a kind of elastic wing, including upper limb body frame, bottom wing body frame, rib and fin, wherein, the fin combines to form elastic aerofoil with rib, the upper limb body frame and bottom wing body frame coordinate the forward edge for clamping elastic aerofoil, and the rear portion of elastic aerofoil is in free state.The elastic wing that the utility model is provided, the elastic aerofoil of shaping one is combined together mainly by rib and fin produce elastic deformation, the elastic wing has the characteristics of arranging toughness, strong crooking ability and good fatigue resistance, also there is lightweight, simple structure, maintenance is easily assembled and reduce the advantage of production cost, Fixed Wing AirVehicle and flapping wing aircraft can be effectively applicable to, can maximize can also minimize, and apply to a kind of manned or unmanned vehicle elastic wing.
Description
Technical field
The utility model is related to a kind of aircraft wing of bionic flapping-wing flying vehicle technical field, specifically one kind to be applied to
The deformable elastic wing of fixed-wing, flapping wing aircraft.
Background technology
Wing is that modern fixed-wing or the big aircraft of flapping wing two produce one of critical piece of lift.Its function plays winged
Row control, loads fuel oil, installs the effects such as engine, collection undercarriage.As a kind of important composition part of aircraft, for
The security of whole machine also it is critical that.Existing aircraft wing shape and structure also develop many types, typically all
It is to be made up of skin and inner frame.Fixed wing aircraft wing in flight course can produce elastic deformation in itself, and covering
With inner frame constitute common wing due to structure, its wing overall flexibility, crooked deformability and fatigue resistance
It is limited.And the wing weight that constitutes of covering and inner frame account for fuselage gross weight ratio it is very big, complex structure will cause that wing is every
Individual part and connection can have strong elastoresistance to deform, and fatigue resistance is highly difficult.
Found by being retrieved to present technology, there is presently no the bullet used suitable for large-scale fixed and flapping wing aircraft
Property wing.Only fraction elastic wing is used on small-sized flapping-wing aircraft, and generally using the material of cloth, film or plastics
Material, it is difficult to maximize, its intensity, service life and mechanical property are limited.
Utility model content
The utility model is for above shortcomings in the prior art, there is provided a kind of elastic wing.
The elastic wing that the utility model is provided, an elasticity is constituted by high-quality Elastic Steel rib and high-quality stainless steel fin
Aerofoil, with arranging toughness, strong crooking ability and the characteristics of good fatigue resistance.Traditional wing deflection can effectively be solved small, it is whole
Body toughness, crooked deformability and the limited problem of fatigue resistance.Aircraft can be avoided in flight course with maximum simultaneously
Middle wing is easy to the problem of fracture because of the factors such as outer gas stream mutation, wing.
The elastic wing that the utility model is provided, only can be formed by upper and lower wing body frame, rib and sail combination, be tied
Structure advantages of simple, it is easily assembled maintenance.Compared to traditional wing at least hundreds of, at most thousands of zero wings for constituting, bullet
Property wing part want much less, and each part is directly perceived visible, solves that traditional wing structure is complicated, weight is too heavy, maintenance
Difficult the problems such as.
The utility model provide elastic wing, part shape is simple, processing technology is good, with short production cycle, can batch
Property production.Solve the problems such as traditional wing processing assembling is complicated, the production cycle is long, production cost is high.
To achieve the above object, the utility model is achieved through the following technical solutions.
A kind of elastic wing, including upper limb body frame, bottom wing body frame, rib and fin, wherein, the fin and rib knot
Close and form elastic aerofoil, the upper limb body frame and bottom wing body frame coordinate the forward edge for clamping elastic aerofoil, elastic aerofoil
Rear portion is in free state.
Preferably, the rib is many, and thin seam is provided with each of which root rib, and fin is multi-disc, wherein often
Two sides of a piece of fin are each passed through the thin seam of adjacent two ribs, and are fixed on adjacent two ribs.
Preferably, adjacent two ribs are one group, and separate between other group of rib.
Preferably, the curved strip of the rib, two width of rib on elastic aerofoil transverse direction ragged edge and
Thickness is all higher than the width and thickness of other ribs；The fin is flake structure.
Preferably, the domed convex globoidal in upper surface of the elastic aerofoil, the lower surface of elastic aerofoil is in cancave cambered surface, described
Fin is covered and is fixed on the upper surface of rib, and the rib of the elastic aerofoil lower surface protrudes flap surface and is hidden in concave arc
In face.
Preferably, the forward edge of the elastic aerofoil, the edge a that its root extends between A points to end direction is linear
Inclination angle forward, A points form obtuse angle alpha to the edge b linear inclination angles backward between end between edge a and edge b；The resilient wing
The transverse rear edge in face, its root extends to the linear inclination angles forward of edge c between B points to end direction, and B points are between end
The linear inclination angles backward of edge d, obtuse angles beta is formed between edge c and edge d.
Preferably, the upper limb body frame and bottom wing body frame are adapted with the forward edge of elastic aerofoil.
Preferably, the obtuse angle alpha≤obtuse angles beta.
Preferably, the upper limb body frame and bottom wing body frame are rigid hollow structural member, using aluminum alloy material, the rib
Using Elastic Steel material, the fin uses stainless steel.
Preferably, the elastic wing can also include upper flow deflector and/or lower flow deflector, the upper flow deflector-before
End is fixed on the rear upper surface of upper limb body frame, and connects flat with the cambered surface of upper limb body frame, and the rear end of upper flow deflector is free state,
For guiding elastic wing upper surface airflow smooth to flow through, the front end of the lower flow deflector is fixed on the rear portion following table of bottom wing body frame
Face, and connect flat with the cambered surface of bottom wing body frame, the rear end of lower flow deflector is free state, for guiding elastic wing lower surface air-flow
It is smooth to flow through.
Preferably, the upper flow deflector and/or lower flow deflector use spring flake structure.
Compared with prior art, the utility model has following beneficial effect：
The elastic wing that the utility model is provided, its structure is more simple and reliable, because rib uses Elastic Steel knot with fin
It is combined, relative to traditional stressed-skin construction wing, the utility model can be resisted must live much bigger deflection without breaking
Split, this causes to install the aircraft of this wing when the factor such as being mutated by air-flow and acting on wing, keeps away to greatest extent
Exempt from wing fracture and cause major accident.
Different from stressed-skin construction wing, the utility model critical piece is all visible in outside, convenient to each main of wing
Part inspection, can easily find potential fatigue fracture lines and surface damage breach that each critical piece of wing is present very much, with
Just change in time.
The utility model is made up of multiple ribs and fin, and each fin plays the role of rib and plays support flap, one
Individual fin forms one and combine with two ribs, and with the respective independence of other fins and rib, even wherein have a rib or
Fin is broken in outer masterpiece with unexpected, and the one-level fin combined with it can fail without influencing whether whole wing, still may be used
To allow aircraft safety to land.
Relative to complicated traditional covering wing structure, the main structural components that the utility model only has minority are constituted, nothing
By be from processing cost, processing technology and assembling, it is all more cheap for replacing maintenance cost.
Relative to complicated traditional covering wing structure, the utility model weight is lighter so that aircraft rate of loading is higher,
So as to obtain significant economic benefit.
Brief description of the drawings
The detailed description made to non-limiting example with reference to the following drawings by reading, other spies of the present utility model
Levy, objects and advantages will become more apparent upon：
Fig. 1 is the utility model embodiment wing axonometric drawing；
Fig. 2 is the utility model embodiment wing top view；
Fig. 3 is the utility model embodiment wing sectional view；
Fig. 4 is the utility model embodiment wing upward view；
Fig. 5 is the utility model embodiment wing rearview；
Fig. 6 is the wing axonometric drawing for being provided with flow deflector and/or lower flow deflector；
Fig. 7 is the wing top view for being provided with flow deflector and/or lower flow deflector；
Fig. 8 is the wing sectional view for being provided with flow deflector and/or lower flow deflector；
Fig. 9 is the wing upward view for being provided with flow deflector and/or lower flow deflector；
In figure：1 is upper limb body frame, and 2 is bottom wing body frame, and 3 is the first rib, and 4 is the second rib, and 5 is the 3rd rib, and 6 are
4th rib, 7 is the 5th rib, and 8 is the 6th rib, and 9 is the 7th rib, and 10 is the first fin, and 11 is the second fin, and 12 is the
Three fins, 13 is the 4th fin, and 14 is the 5th fin, and 15 is the 6th fin, and 16 is upper flow deflector, and 17 is lower flow deflector.
Specific embodiment
Embodiment of the present utility model is elaborated below：The present embodiment is with technical solutions of the utility model as preceding
Put and implemented, give detailed implementation method and specific operating process.It should be pointed out that to the common of this area
For technical staff, without departing from the concept of the premise utility, various modifications and improvements can be made, these all belong to
In protection domain of the present utility model.
Embodiment 1
The technical solution of the utility model is described in further detail below in conjunction with the accompanying drawings.
As shown in Figure 1 to Figure 3, the elastic wing that the present embodiment is provided, including upper limb body frame 1, bottom wing body frame 2, rib 3-
9th, fin 10-15.Wherein, upper limb body frame 1 and bottom wing body frame 2 are combined into elastic wing main body, before fixing rib 3-9
Portion, while also clamping the forward edge part of each fins of fin 10-15.
Rib 3-9 longitudinal directions front end is fixed in upper limb body frame 1 and bottom wing body frame 2, and the upper surface of rib is covered by fin 10-15
Lid, rib longitudinally aft end part is in free state, and rib can be allowed to produce elastic free to become with the surface stress of elastic wing
Shape.
Fin 10-15 longitudinal directions forward edge part is clamped and fixed by upper limb body frame 1 and bottom wing body frame 2, horizontal both sides point
Not Chuan Guo adjacent two ribs each in the middle of thin seam, and be fixed on rib inner side (on i.e. adjacent two ribs), fin longitudinal direction
Rim portion is in free state afterwards, and fin can be allowed to produce elastic free to deform with the surface stress of elastic wing.
The upper limb body frame 1 and bottom wing body frame 2 are made using high-strength aluminum alloy material, are processed using CNC milling machine finish-milling
Appearance profile is obtained, inside is except fixed and coupling part, remaining non-stress part milling lightening grooves, to mitigate upper bottom wing body frame weight.
After upper and lower wing body frame is finished through milling machine, surface grinding, finishing polish process the cutter track and residual stress that leave to remove milling machine,
Reduce the dark line in surface, the risk of fracture microscopic nicks.Then anodized surface again, forms smooth surface to reduce during flight
Gas-flow resistance.
The rib makes of high-quality Elastic Steel, to ensure that rib has enough elasticity and service life.Each elastic machine
The rib of the wing has several, and wherein length width is different.The first rib of wing transverse direction outermost direction 3 and the design of the 7th rib 9 will
It is wider than other ribs and thick.So that the 7th rib 9 and the first rib 3 are more stronger than other rib stress-bearing capabilities, in service life more
It is long.If wherein one rib of unexpected fracture in flight course, can also allow aircraft safety to be landed, will not produce very serious
Aircraft accident.Rib obtains appearance profile using the processing of CNC milling machine finish-milling, and middle thin seam is formed using linear cutter.Surface
Grinding, finishing polish are machined into cutter track and residual stress that rib surface leaves to remove, and reduce the dark line in surface, be broken small lacking
The risk of mouth.Then electroplating surface treatment again, forms smooth surface to reduce gas-flow resistance during flight.
The fin 10-15 is made using high-quality stainless steel thin slice.Profile laser cutting is obtained, the longitudinal direction front portion side of fin
Edge is fixed in upper limb body frame 1 and bottom wing body frame 2, and horizontal both sides are fixed between upper and lower wing body frame and rib.Play it is upper,
An effect for entirety is connected between bottom wing body frame and rib, the part shape for finally allowing elastic wing to be connected with fin in rib
Into a deformed region that can be freely elastically deformed.
The elastic wing that the present embodiment is provided, thereon, bottom wing body frame be elastic wing main body, root plane is connected to fixation
On the body of rotor aircraft or flapping wing aircraft.Rib plays auxiliary fixed tab and supports the function of fin, upper lower wing master
Frame fixes rib and fin, forms an entirety.
The elastic wing is main to combine shaping by upper limb body frame and bottom wing body frame and multiple ribs with multiple fins.
Upper and lower wing body frame is rigid member, does not play metamorphosis.Elastic wing is combined together shaping one mainly by rib and fin
Individual elastic aerofoil, produces elastic deformation.
Upper and lower wing body frame uses the hollow Lightened structure of high-strength aluminum alloy, appearance profile CNC milling machine Precision Machining, surface
Grinding and polishing and anodized.Rib is processed using high-quality Elastic Steel CNC milling machine, and then surface grinding finishing polish electroplates
Treatment.Fin uses high-quality stainless steel thin slice.
This elastic wing simple structure, can effectively mitigate aircraft gross weight amount.Easily can be installed on fuselage, also side
Just replace and repair.
This elastic wing longitudinal direction upper part is arch convex globoidal, re-forms middle imploded arcs by fraction plane below
Face.The air velocity for flowing through wing upper and lower surface can be thus allowed to differ, so as to form lift.Fin is covered and is fixed on the wing
Rib upper surface, guiding airflow smooth flows through.Because into cancave cambered surface below wing, rib protrudes finned surface and is hidden in cancave cambered surface
Interior, air-flow blows from longitudinal front main wing frame facet and will not produce resistance because of the rib for protruding.This elastic wing is laterally
Slight arch is formed, left and right elastic wing is symmetrically installed pneumatic outer with regard to forming one one of upper inverted diherdral on board the aircraft
Shape, air-flow from flow longitudinally through aircraft it is overall when so that the pneumatic property of aircraft is more reliable and more stable.
The present embodiment provide elastic wing, thereon, the mode of bottom wing body frame combination grip fix rib and fin, rib
Play a part of to support fin, rib and sail combination form an elastic aerofoil for elastically deformable.
The upper limb body frame is a kind structure of longitudinal convex globoidal and horizontal arcuate surface.Bottom wing body frame is longitudinal concave arc
Face and a kind of structure of horizontal arcuate surface.Upper and lower wing body frame is the main body of elastic wing, and upper and lower wing body frame combination is fixed, and is risen
It is the main components of elastic wing stress and generation lift to the effect for gripping rib and fin.
Rib is a strip for arc, is made using high-quality Elastic Steel, and centre is provided with thin seam for auxiliary fixed-wing
The structure of piece, is to support elastic wing, produces the main element of elastic deformation.Elastic wing is by several this species shape rib group
Into.
Fin is made by thin slice, is fixed on rib upper surface, and guiding elastic wing upper surface airflow smooth flows through, and is machine
The wing extends aerofoil and mitigates the main element of wing weight, by combining the generation elastic deformation that is fixed together with rib, elasticity
By several pieces, this species shape fin is constituted wing.
The present embodiment provide elastic wing, it is adaptable to fixed-wing and flapping wing aircraft, thereon, bottom wing body frame combination fix
Rib and fin, upper and lower wing body frame are wing-body, and root plane is connected to the body of Fixed Wing AirVehicle or flapping wing aircraft
On.Rib plays the function of auxiliary fixed tab and support flap, and upper and lower wing body frame fixes rib and fin, forms one
It is overall.Upper and lower wing body frame is rigid member, does not play metamorphosis.Rib is made by high-quality Elastic Steel, and elastic wing is mainly by the wing
Rib and fin are combined together the elastic aerofoil of shaping one and produce elastic deformation.The wing has arrangement toughness, crooking ability strong
The characteristics of good with fatigue resistance.Also there is lightweight, simple structure, maintenance is easily assembled and reduce the advantage of production cost,
Fixed Wing AirVehicle and flapping wing aircraft can be effectively applicable to.Can maximize can also minimize, it is adaptable to manned or unmanned flight
A kind of elastic wing of device.
The elastic wing that the present embodiment is provided, its simple structure is practical, does not have to making material and processing technology
In harsh requirement.Versatility, interchangeability are good.Lightweight, security is good, it is easy to assembles, safeguard.It is capable of achieving to produce in enormous quantities,
Drop bottom production cost.
Embodiment 2
Embodiment 2 is the change case of embodiment 1, is carried out on the basis of embodiment 1, and with same as Example 1
Function, while beneficial effect same as Example 1 can be reached.
The present embodiment provide elastic wing, on the architecture basics of embodiment 1, can also include upper flow deflector and/or
Lower flow deflector, the upper flow deflector-front end be fixed on the rear upper surface of upper limb body frame, and connect with the cambered surface of upper limb body frame
Flat, the rear end of upper flow deflector is free state, for guiding elastic wing upper surface airflow smooth to flow through, the lower flow deflector
Front end is fixed on the rear lower surface of bottom wing body frame, and connects flat with the cambered surface of bottom wing body frame, and the rear end of lower flow deflector is free shape
State, for guiding elastic wing lower surface airflow smooth to flow through.
Upper flow deflector, lower flow deflector use high-quality spring thin slice.
Specific embodiment of the utility model is described above.It is to be appreciated that the utility model not office
It is limited to above-mentioned particular implementation, those skilled in the art can within the scope of the claims make various deformations or amendments,
This has no effect on substance of the present utility model.
Claims (9)
1. a kind of elastic wing, it is characterised in that including upper limb body frame, bottom wing body frame, rib and fin, wherein, the wing
Piece combines to form elastic aerofoil with rib, and the upper limb body frame and bottom wing body frame coordinate the forward edge for clamping elastic aerofoil,
The rear portion of elastic aerofoil is in free state.
2. elastic wing according to claim 1, it is characterised in that the rib is many, on each of which root rib
Thin seam is provided with, the fin is multi-disc, and two sides of each of which piece fin are each passed through the thin seam of adjacent two ribs,
And be fixed on adjacent two ribs.
3. elastic wing according to claim 2, it is characterised in that adjacent two ribs are a group, and with other group of wing
It is separate between rib.
4. elastic wing according to claim 2, it is characterised in that the curved strip of the rib, elastic aerofoil
The width and thickness of two ribs on horizontal ragged edge are all higher than the width and thickness of other ribs；The fin is thin slice knot
Structure.
5. elastic wing according to claim 1, it is characterised in that the domed convex arc in upper surface of the elastic aerofoil
Face, the lower surface of elastic aerofoil is in cancave cambered surface, and the fin is covered and is fixed on the upper surface of rib, the elastic aerofoil following table
The rib in face protrudes flap surface and is hidden in cancave cambered surface；And/or
The forward edge of the elastic aerofoil, its root extends to edge a linear inclination angle, A points forward between A points to end direction
To the linear inclination angles backward of edge b between end, obtuse angle alpha is formed between edge a and edge b；The transverse rear of the elastic aerofoil
Edge, its root extends to the linear inclination angle forward of edge c between B points to end direction, B points to the edge d between end it is linear to
Back rake angle, obtuse angles beta is formed between edge c and edge d；The forward edge phase of the upper limb body frame and bottom wing body frame and elastic aerofoil
Adaptation.
6. elastic wing according to claim 5, it is characterised in that the obtuse angle alpha≤obtuse angles beta.
7. elastic wing according to claim 1, it is characterised in that the upper limb body frame and bottom wing body frame are rigid hollow
Structural member, using aluminum alloy material；The rib uses Elastic Steel material；The fin uses stainless steel.
8. elastic wing according to any one of claim 1 to 7, it is characterised in that also including upper flow deflector and/or under
Flow deflector, the upper flow deflector-front end be fixed on the rear upper surface of upper limb body frame, and connect flat with the cambered surface of upper limb body frame,
The rear end of upper flow deflector is free state, the lower flow deflector-front end be fixed on the rear lower surface of bottom wing body frame, and with
The cambered surface of wing body frame connects flat, and the rear end of lower flow deflector is free state.
9. elastic wing according to claim 8, it is characterised in that the upper flow deflector and/or lower flow deflector use bullet
Spring flake structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621146865.XU CN206255193U (en) | 2016-10-21 | 2016-10-21 | Elastic wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621146865.XU CN206255193U (en) | 2016-10-21 | 2016-10-21 | Elastic wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206255193U true CN206255193U (en) | 2017-06-16 |
Family
ID=59024124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621146865.XU Active CN206255193U (en) | 2016-10-21 | 2016-10-21 | Elastic wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206255193U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757916A (en) * | 2017-10-10 | 2018-03-06 | 山东大学 | A kind of flapping wing aircraft open-close type wing structure based on combination drive |
| CN109760833A (en) * | 2019-01-28 | 2019-05-17 | 胡高 | Can take down the exhibits resilient wing |
-
2016
- 2016-10-21 CN CN201621146865.XU patent/CN206255193U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107757916A (en) * | 2017-10-10 | 2018-03-06 | 山东大学 | A kind of flapping wing aircraft open-close type wing structure based on combination drive |
| CN107757916B (en) * | 2017-10-10 | 2020-09-08 | 山东大学 | Flapping wing aircraft open-close type wing structure based on hybrid drive |
| CN109760833A (en) * | 2019-01-28 | 2019-05-17 | 胡高 | Can take down the exhibits resilient wing |
| CN109760833B (en) * | 2019-01-28 | 2020-10-09 | 胡高 | Foldable elastic wing |
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