CN207157531U - Flapping-wing aircraft fixed-wing and flapping-wing aircraft - Google Patents
Flapping-wing aircraft fixed-wing and flapping-wing aircraft Download PDFInfo
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- CN207157531U CN207157531U CN201721059013.1U CN201721059013U CN207157531U CN 207157531 U CN207157531 U CN 207157531U CN 201721059013 U CN201721059013 U CN 201721059013U CN 207157531 U CN207157531 U CN 207157531U
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- spar
- wing aircraft
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Abstract
Vehicle technology field is the utility model is related to, more particularly, to a kind of flapping-wing aircraft fixed-wing and flapping-wing aircraft.The flapping-wing aircraft fixed-wing, including covering, spar and rib；The quantity of spar is more, and more spar parallel intervals are set；The quantity of rib is multiple, and multiple rib parallel intervals are set；Spar passes through rib, and spar is fixedly connected with rib；Spar is hollow pipe, chordwise, is gradually reduced by fixed nose of wing to fixed-wing trailing edge, the caliber of more spars.The flapping-wing aircraft, including described flapping-wing aircraft fixed-wing.The utility model is advantageous to the raising of the flying quality of take-off and landing.
Description
Technical field
Vehicle technology field is the utility model is related to, more particularly, to a kind of flapping-wing aircraft fixed-wing and flapping-wing aircraft.
Background technology
Flapping-wing aircraft is also known as ornithopter, refers to the aviation for overweighting air that wing can flutter up and down as bird and insect wing
Device, the wing fluttered (also referred to as flapping wing) not only produce lift, also produce motive force forward.Existing flapping-wing aircraft is shaken by flapping wing
Movable property is given birth in lift and thrust flight course, can also carry out gliding row using the fixed-wing on fuselage, but its fixed-wing
Structure design is unreasonable and heavier-weight, is unfavorable for the raising of the flying quality of the take-off and landing of flapping-wing aircraft.
Utility model content
The purpose of this utility model is to provide a kind of flapping-wing aircraft fixed-wing and flapping-wing aircraft, to solve to exist in the prior art
Flapping-wing aircraft fixed-wing structure design is unreasonable and heavier-weight, be unfavorable for the flight of the take-off and landing of flapping-wing aircraft
The technical problem of the raising of performance.
The utility model provides a kind of flapping-wing aircraft fixed-wing, including covering, spar and rib, and the covering is by the wing
Beam and the rib are supported；The quantity of the spar is more, and the more spar parallel intervals are set；The rib
Quantity is multiple, and multiple rib parallel intervals are set；The spar passes through the rib, and the spar and the wing
Rib is fixedly connected；The spar is hollow pipe, chordwise, by fixed nose of wing to fixed-wing trailing edge, the more spars
Caliber be gradually reduced.
Further, the rib includes upper edge strip, lower edge strip and corbeling；The upper edge strip is located at the lower edge strip
Top, and the upper edge strip is fixedly connected with the lower edge strip, the corbeling be installed on the upper edge strip with it is described under
Between edge strip.
Further, the corbeling includes more inclined struts, and the inclined strut is set with chordwise in angle, and
One end of the inclined strut is fixedly connected with the upper edge strip, and the other end of the inclined strut is fixedly connected with the lower edge strip.
Further, in addition to leading edge supporting member, for supporting the covering；The leading edge supporting member is installed on position
In on the spar of fixed nose of wing
Further, the upper edge strip is structure as a whole with the lower edge strip.
Further, the aerofoil profile of the flapping-wing aircraft fixed-wing is plano-convex aerofoil profile.
Further, the material of the spar is aluminium alloy.
Further, the material aluminium alloy of the rib.
Further, the material of the covering is nylon cloth.
The utility model additionally provides a kind of flapping-wing aircraft, including described flapping-wing aircraft fixed-wing.
Compared with prior art, the beneficial effects of the utility model are：
Flapping-wing aircraft fixed-wing provided by the utility model, including covering, spar and rib, covering are propped up by spar and rib
Support；The quantity of spar is more, and more spar parallel intervals are set；The quantity of rib is multiple, and parallel of multiple ribs
Every setting；Spar passes through rib, and spar is fixedly connected with rib；Spar is hollow pipe, chordwise, by fixed nose of wing
To fixed-wing trailing edge, the caliber of more spars is gradually reduced.By carrying out rearranging simplification to the structure of fixed-wing, using sky
Heart pipe is used as spar to mitigate weight, and in the chordwise of fixed-wing, the caliber of more spars is gradually reduced, solid to optimize
Determine the distribution situation of more spars of the wing, and preferably highly can mitigate weight using wing structure, it is ensured that hold
By the moment of flexure of wing and the performance of shearing, so that fixed-wing is advantageous to the flying quality of the take-off and landing of flapping-wing aircraft
Improve.
The flapping-wing aircraft that the utility model also provides, including described flapping-wing aircraft fixed-wing.Understand that this is flutterred based on above-mentioned analysis
Wing machine is advantageous to the raising of the flying quality of take-off and landing.
Brief description of the drawings
, below will be right in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
The required accompanying drawing used is briefly described in embodiment or description of the prior art, it should be apparent that, describe below
In accompanying drawing be some embodiments of the present utility model, for those of ordinary skill in the art, do not paying creativeness
On the premise of work, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation for the flapping-wing aircraft fixed-wing that the utility model embodiment one provides；
Fig. 2 does not install structural representation during covering for flapping-wing aircraft fixed-wing in the utility model embodiment one；
Fig. 3 is the close-up schematic view at A in Fig. 2；
Fig. 4 is the close-up schematic view at B in Fig. 2；
Fig. 5 is the close-up schematic view at C in Fig. 2；
Fig. 6 is the structural representation of rib in the utility model embodiment one；
Fig. 7 is the schematic diagram at another visual angle of rib in the utility model embodiment one；
Fig. 8 is the structural representation for the flapping-wing aircraft fixed-wing that the utility model embodiment two provides；
Fig. 9 is the structural representation for the flapping-wing aircraft that the utility model embodiment three provides.
Figure 10 is the close-up schematic view at D in Fig. 9.
In figure：
300- fuselage rings；401- coverings；402- spars；
403- ribs；The upper edge strips of 404-；Edge strip under 405-；
406- inclined struts；407- leading edge supporting members；408- leading edge arc tips；
The stable necks of 409-；410- rear edge support components；411- stringers.
Embodiment
The technical solution of the utility model is clearly and completely described below in conjunction with accompanying drawing, it is clear that described
Embodiment is the utility model part of the embodiment, rather than whole embodiments.
Component generally here described in accompanying drawing with the utility model embodiment shown can be with a variety of
Configure to arrange and design.Therefore, the detailed description of the embodiment of the present utility model to providing in the accompanying drawings is not purport below
In the claimed the scope of the utility model of limitation, but it is merely representative of selected embodiment of the present utility model.
Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belong to the scope of the utility model protection.
, it is necessary to explanation in description of the present utility model, term " " center ", " on ", " under ", it is "left", "right", " perpendicular
Directly ", the orientation of the instruction such as " level ", " interior ", " outer " or position relationship are based on orientation shown in the drawings or position relationship, are only
Described for the ease of description the utility model and simplifying, rather than instruction or imply signified device or element must have it is specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.In addition, term " the
One ", " second ", " the 3rd " are only used for describing purpose, and it is not intended that instruction or hint relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.
Embodiment one
Referring to shown in Fig. 1 to Fig. 7, the utility model embodiment one provides a kind of flapping-wing aircraft fixed-wing, including covering
401st, spar 402 and rib 403；The quantity of spar 402 is more, and the more parallel intervals of spar 402 are set；Rib 403
Quantity is multiple, and the parallel interval of multiple ribs 403 is set；Spar 402 passes through rib 403, and spar 402 and rib 403 are solid
Fixed connection；Spar 402 is hollow pipe, chordwise, by fixed nose of wing to fixed-wing trailing edge, the caliber of more spars 402
It is gradually reduced, that is to say, that the caliber of more spars 402 differs, and be located at the spar 402 of the leading edge of flapping-wing aircraft fixed-wing
Caliber is maximum, and the caliber of the spar 402 positioned at the leading edge of flapping-wing aircraft fixed-wing is minimum.It should be noted that caliber refers to
Pipe external diameter.
Specifically, covering is supported jointly by spar and rib, and covering is fixedly connected with spar and rib respectively；It is more
Tangential parallel interval arrangement of the root spar 402 along flapping-wing aircraft fixed-wing, that is to say, that the length direction and flapping-wing aircraft of spar 402
The exhibition of fixed-wing is to parallel；Exhibition of multiple ribs 403 along flapping-wing aircraft fixed-wing is set to parallel interval, that is to say, that rib 403
Length direction it is tangential parallel with flapping-wing aircraft fixed-wing.In the embodiment, the quantity of spar is 3.
Flapping-wing aircraft fixed-wing provided by the utility model, by carrying out rearranging simplification to the structure of fixed-wing, use
Hollow pipe is used as spar 402 to mitigate weight, and in the chordwise of fixed-wing, the caliber of more spars 402 is gradually reduced,
To optimize the distribution situation of more spars 402 of fixed-wing, and preferably highly it can mitigate weight using wing structure,
The moment of flexure for bearing wing and the performance of shearing are also assures that, so that fixed-wing is advantageous to the take-off and landing of flapping-wing aircraft
The raising of flying quality.
In the optional scheme of the embodiment, rib 403 includes upper edge strip 404, lower edge strip 405 and corbeling；Upper edge strip
404 are located at the top of lower edge strip 405, and upper edge strip 404 is fixedly connected with lower edge strip 405, and corbeling is installed on edge strip 404
Between lower edge strip 405.
Specifically, the aerofoil profile of flapping-wing aircraft fixed-wing is plano-convex aerofoil profile；That is, upper edge strip 404 is curved, and lower edge
Bar 405 is linear；One end of upper edge strip 404 is fixedly connected with one end of lower edge strip 405, and the other end of upper edge strip 404 is with
The other end of edge strip is fixedly connected.In the space that corbeling is formed between upper edge strip 404 and upper edge strip 404.
In the optional scheme of the embodiment, upper edge strip 404 is structure as a whole with lower edge strip 405.
Specifically, upper edge strip 404 is made with lower edge strip 405 of integrally formed technique, is so advantageous to improve the wing
The steadiness of rib 403.
In the optional scheme of the embodiment, corbeling includes more inclined struts 406, and inclined strut 406 is fixed with flapping-wing aircraft
The chordwise of the wing is set in angle, and one end of inclined strut 406 is fixedly connected with upper edge strip 404, the other end of inclined strut 406
It is fixedly connected with lower edge strip 405.
Specifically, more inclined struts 406 are in the distribution of line shape is torn open, are so advantageous to upper edge strip 404 and lower edge strip 405
Supporting role, enhance the steadiness of rib 403.
In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes leading edge supporting member 407, for supporting covering
401；Leading edge supporting member 407 is installed on the spar 402 of fixed nose of wing, is also with regard to saying, leading edge supporting member 407 is solid
Due on the maximum spar 402 of the caliber of the leading edge of flapping-wing aircraft fixed-wing.
Specifically, the quantity of leading edge supporting member 407 is multiple, length of multiple leading edge supporting members 407 along spar 402
Direction uniform intervals are spent to set.Leading edge supporting member 407 has leading edge arc tips 408, the leading edge arc tips 408 and flapping-wing aircraft
The shape of the leading edge of fixed-wing is identical.
In the optional scheme of the embodiment, stable card is also each had on the top of leading edge supporting member 407 and upper edge strip 404
Groove 409；Flapping-wing aircraft fixed-wing also includes the stable beam of leading edge；The stable beam of leading edge is sticked in stable neck 409, and leading edge is supported into structure
Part 407 and upper edge strip 404 connect, to ensure the steadiness of leading edge supporting member 407.
In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes rear edge support component 410, for supporting covering
401；Rear edge support component 410 is installed on the spar 402 of fixed-wing trailing edge, is also with regard to saying, rear edge support component 410 is solid
Due on the minimum spar 402 of the caliber of the trailing edge of flapping-wing aircraft fixed-wing.
Specifically, the quantity of rear edge support component 410 is multiple, length of multiple rear edge support components 410 along spar 402
Direction uniform intervals are spent to set.
It should be noted that in the embodiment, can also be opened up on the top of rear edge support component and upper edge strip steady
Determine neck；Flapping-wing aircraft fixed-wing can also include the stable beam of trailing edge；The stable beam of trailing edge is sticked in stable neck, by rear edge support
Component and upper edge strip connect, to ensure the steadiness of rear edge support component.
In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes a stringer 411, the length direction of the stringer 411
It is parallel with the length direction of spar, and the stringer is also fixedly connected with rib.Also rear edge support component is fixed with the stringer
410。
In the optional scheme of the embodiment, the material of spar 402 is aluminium alloy.It should be noted that in the embodiment, the wing
The material of beam 402 is not only limited to aluminium alloy, and the light-weight metal of other forms can also be freely chosen according to actual condition, to
Realize the function of mitigating fixed-wing；No longer specifically repeated one by one for light-weight metal the present embodiment of other forms.
In the optional scheme of the embodiment, the material of rib 403 is aluminium alloy.It should be noted that in the embodiment, the wing
The material of rib 403 is not only limited to aluminium alloy, and the light-weight metal of other forms can also be freely chosen according to actual condition, to
Realize the function of mitigating fixed-wing；Do not repeated specifically further for light-weight metal the present embodiment of other forms.
In the optional scheme of the embodiment, the material of covering 401 is nylon cloth.It should be noted that in the embodiment, cover
The material of skin 401 is not only limited to nylon cloth, and the covering 401 of other forms can also be freely chosen according to actual condition, to
Realize waterproof and mitigate the function of fixed-wing；Do not repeated specifically further for the present embodiment of covering 401 of other forms.
Embodiment two
Shown in Figure 8, the embodiment two also provides a kind of flapping-wing aircraft fixed-wing, and the flapping-wing aircraft of the embodiment two is fixed
The wing describes another implementation of the aspect ratio of flapping-wing aircraft fixed-wing, and the technical scheme of embodiment one in addition also belongs to
In the embodiment two, it is not repeated to describe.
In the embodiment, the aspect ratio of flapping-wing aircraft fixed-wing is 7.69.
Embodiment three
The embodiment three also provides a kind of flapping-wing aircraft fixed-wing, and the flapping-wing aircraft fixed-wing of the embodiment three describes flapping wing
Another implementation of the aspect ratio of machine fixed-wing, the technical scheme of embodiment one in addition fall within the embodiment
Three, it is not repeated to describe.
In the embodiment, the aspect ratio 6.27 of flapping-wing aircraft fixed-wing.
Example IV
The utility model embodiment four, which provides a kind of flapping-wing aircraft, includes any embodiment into embodiment three of embodiment one
The flapping-wing aircraft fixed-wing of offer.
Referring to shown in Fig. 9 and Figure 10, in the embodiment, flapping-wing aircraft also includes fuselage ring 300, and fuselage ring 300 is with flutterring
The spar 402 of wing machine fixed-wing is fixedly connected.
It should be noted that the flapping-wing aircraft can be unmanned flapping-wing aircraft, or manned flapping-wing machine.
Finally it should be noted that：Various embodiments above is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in foregoing embodiments, either to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical scheme of type.In addition, it will be appreciated by those of skill in the art that although some implementations described herein
Example includes some features included in other embodiments rather than further feature, but the combination of the feature of different embodiments is anticipated
Taste within the scope of the utility model and forms different embodiments.For example, in the following claims, institute
The one of any of claimed embodiment mode can use in any combination.
Claims (10)
1. a kind of flapping-wing aircraft fixed-wing, it is characterised in that including covering, spar and rib, the covering is by the spar and institute
Rib is stated to be supported；The quantity of the spar is more, and the more spar parallel intervals are set；The quantity of the rib is
It is multiple, and multiple rib parallel intervals are set；The spar passes through the rib, and the spar is fixed with the rib
Connection；The spar is hollow pipe, chordwise, by fixed nose of wing to fixed-wing trailing edge, the caliber of the more spars
It is gradually reduced.
2. flapping-wing aircraft fixed-wing according to claim 1, it is characterised in that the rib include upper edge strip, lower edge strip and
Corbeling；The upper edge strip is located at the top of the lower edge strip, and the upper edge strip is fixedly connected with the lower edge strip, described
Corbeling is installed between the upper edge strip and the lower edge strip.
3. flapping-wing aircraft fixed-wing according to claim 2, it is characterised in that the corbeling includes more inclined struts,
The inclined strut is set with chordwise in angle, and one end of the inclined strut is fixedly connected with the upper edge strip, described oblique
The other end of pillar is fixedly connected with the lower edge strip.
4. the flapping-wing aircraft fixed-wing according to any one of claim 1-3, it is characterised in that also support structure including leading edge
Part, for supporting the covering；The leading edge supporting member is installed on the spar of fixed nose of wing.
5. the flapping-wing aircraft fixed-wing according to Claims 2 or 3, it is characterised in that the upper edge strip is with the lower edge strip
Integrative-structure.
6. the flapping-wing aircraft fixed-wing according to any one of claim 1-3, it is characterised in that the flapping-wing aircraft fixed-wing
Aerofoil profile is plano-convex aerofoil profile.
7. the flapping-wing aircraft fixed-wing according to any one of claim 1-3, it is characterised in that the material of the spar is aluminium
Alloy.
8. the flapping-wing aircraft fixed-wing according to any one of claim 1-3, it is characterised in that the material aluminium of the rib closes
Gold.
9. the flapping-wing aircraft fixed-wing according to any one of claim 1-3, it is characterised in that the material of the covering is Buddhist nun
Long Bu.
10. a kind of flapping-wing aircraft, it is characterised in that including flapping-wing aircraft fixed-wing as claimed in any one of claims 1-9 wherein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721059013.1U CN207157531U (en) | 2017-08-23 | 2017-08-23 | Flapping-wing aircraft fixed-wing and flapping-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721059013.1U CN207157531U (en) | 2017-08-23 | 2017-08-23 | Flapping-wing aircraft fixed-wing and flapping-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207157531U true CN207157531U (en) | 2018-03-30 |
Family
ID=61718253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721059013.1U Expired - Fee Related CN207157531U (en) | 2017-08-23 | 2017-08-23 | Flapping-wing aircraft fixed-wing and flapping-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207157531U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108423176A (en) * | 2018-04-18 | 2018-08-21 | 南方科技大学 | Modularized fixed-wing unmanned aerial vehicle |
| CN112249300A (en) * | 2020-10-22 | 2021-01-22 | 航天特种材料及工艺技术研究所 | A carbon fiber composite airfoil leading edge structure |
| CN112278268A (en) * | 2020-10-30 | 2021-01-29 | 航空工业信息中心 | Flapping wing structure imitating dragonfly wing |
| CN112758306A (en) * | 2021-04-08 | 2021-05-07 | 中国航天空气动力技术研究院 | Self-tensioning wing rib, wing and skin laying method |
| CN113060273A (en) * | 2021-04-06 | 2021-07-02 | 西北工业大学 | Fixed-wing UAV single-beam distributed wing front D-box structure |
-
2017
- 2017-08-23 CN CN201721059013.1U patent/CN207157531U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108423176A (en) * | 2018-04-18 | 2018-08-21 | 南方科技大学 | Modularized fixed-wing unmanned aerial vehicle |
| CN108423176B (en) * | 2018-04-18 | 2024-02-27 | 南方科技大学 | Modularized fixed wing unmanned aerial vehicle |
| CN112249300A (en) * | 2020-10-22 | 2021-01-22 | 航天特种材料及工艺技术研究所 | A carbon fiber composite airfoil leading edge structure |
| CN112249300B (en) * | 2020-10-22 | 2022-02-15 | 航天特种材料及工艺技术研究所 | A carbon fiber composite airfoil leading edge structure |
| CN112278268A (en) * | 2020-10-30 | 2021-01-29 | 航空工业信息中心 | Flapping wing structure imitating dragonfly wing |
| CN113060273A (en) * | 2021-04-06 | 2021-07-02 | 西北工业大学 | Fixed-wing UAV single-beam distributed wing front D-box structure |
| CN113060273B (en) * | 2021-04-06 | 2022-12-06 | 西安航科智能信息科技有限公司 | Single-beam distributed wing front D box structure of fixed-wing unmanned aerial vehicle |
| CN112758306A (en) * | 2021-04-08 | 2021-05-07 | 中国航天空气动力技术研究院 | Self-tensioning wing rib, wing and skin laying method |
| CN112758306B (en) * | 2021-04-08 | 2021-07-16 | 中国航天空气动力技术研究院 | Self-tensioning wing rib, wing and skin laying method |
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