CN110386244A - Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it - Google Patents
Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it Download PDFInfo
- Publication number
- CN110386244A CN110386244A CN201810360094.1A CN201810360094A CN110386244A CN 110386244 A CN110386244 A CN 110386244A CN 201810360094 A CN201810360094 A CN 201810360094A CN 110386244 A CN110386244 A CN 110386244A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- rib
- wing skeleton
- plane wing
- transverse slat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000003014 reinforcing effect Effects 0.000 claims description 32
- 210000000988 bone and bone Anatomy 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 5
- 239000000463 material Substances 0.000 abstract description 4
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 25
- 238000004519 manufacturing process Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/185—Spars
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of unmanned plane wing skeleton and include its unmanned plane wing, unmanned plane, the unmanned plane wing skeleton includes at least one transverse slat and several first ribs, first rib is arranged along the cross section of wing, transverse slat is arranged along the length direction of wing, the both ends of first rib are respectively the first wide end and the first tip, first wide end is fixed with transverse slat, and the first tip is protruding；Unmanned plane wing skeleton further includes several second ribs, and the second rib is located between the first tip of two adjacent the first ribs, and the both ends of the second rib are mutually fixed with two adjacent the first ribs respectively.By the way that the second rib is arranged, make the enhanced strength of unmanned plane wing skeleton, the density of wing skeleton material can be reduced under the premise of proof strength, reduce the single-sheet thickness of wing skeleton, to accomplish weight saving and effect that intensity does not subtract, the trend that unmanned plane develops to miniaturization, lightweight is adapted to.
Description
Technical field
The present invention relates to a kind of unmanned plane wing skeletons.
The present invention relates to a kind of unmanned plane wings comprising above-mentioned unmanned plane wing skeleton.
The present invention relates to a kind of unmanned planes comprising above-mentioned unmanned plane wing skeleton.
Background technique
With the rapid development of unmanned air vehicle technique, unmanned plane is used in every field.In the prior art, the kind of unmanned plane
Class includes multi-rotor unmanned aerial vehicle, fixed-wing unmanned plane and VTOL unmanned plane.For fixed-wing unmanned plane and VTOL unmanned plane, wing
It is vital a part.
During wing design, the design of unmanned plane wing skeleton is most important.Unmanned plane wing skeleton is guaranteeing by force
Maximum weight is also needed while spending.And existing unmanned plane wing skeleton, intensity are inadequate, structure is complicated, and weight is larger.
Summary of the invention
The technical problem to be solved by the present invention is to the intensity in order to overcome unmanned plane wing skeleton in the prior art not
It is enough, structure is complicated, the biggish defect of weight, and provide a kind of unmanned plane wing skeleton and comprising its unmanned plane wing, nobody
Machine.
The present invention solves above-mentioned technical problem by the following technical programs:
The present invention provides a kind of unmanned plane wing skeleton, including at least one transverse slat and several first ribs, described
One rib is arranged along the cross section of wing, and the transverse slat is arranged along the length direction of wing, the both ends difference of first rib
For the first wide end and the first tip, first wide end is fixed with the transverse slat, and first tip is protruding；It is described nobody
Machine wing skeleton further includes several second ribs, and second rib is located at the first tip of two adjacent first ribs
Between, the both ends of second rib are mutually fixed with two adjacent first ribs respectively.
In the technical scheme, unmanned plane wing skeleton using the above structure can subtract under the premise of proof strength
The density of small wing skeleton material, reduces the single-sheet thickness of wing skeleton, thus accomplish weight saving and effect that intensity does not subtract,
Adapt to the trend that unmanned plane develops to miniaturization, lightweight.
Preferably, the both ends of second rib are respectively the second wide end and the second tip, second tip with wherein
First tip of one first rib is fixed, the company of second wide end and another first rib and the transverse slat
Place is met to fix.
In the technical scheme, the second rib is fixed with two adjacent the first ribs through the above way, can maximum limit
The intensity of the first rib of degree ground enhancing.
Preferably, two adjacent second ribs are mutually right as the plane of symmetry to be located in the middle first rib
Claim.
In the technical scheme, symmetrically arranged second rib can make the uniform force for being located in the middle the first rib.
Preferably, the unmanned plane wing skeleton further includes several connecting plates, the connecting plate is by several adjacent institutes
State the first rib, the second rib links together.
In the technical scheme, connecting plate plays the role of further increasing the intensity of the first rib.
Preferably, the connecting plate is fixed by way of clamping with first rib, the second rib.
In the technical scheme, the fixed form of clamping keeps unmanned plane wing skeleton easy for installation, and structure is simple, simplifies
The manufacturing procedures of components, reduces production cost.
Preferably, the unmanned plane wing skeleton, which is divided into, is located in the middle intermediate region and positioned at the intermediate region two sides
Side area, the connecting plate is located at the intermediate region of the unmanned plane wing skeleton.
In the technical scheme, intermediate region needs higher intensity, unmanned plane wing skeleton weight by limited time, it is excellent
Connecting plate first is set in the intermediate region of unmanned plane wing skeleton.
Preferably, the unmanned plane wing skeleton, which is divided into, is located in the middle intermediate region and positioned at the intermediate region two sides
Side area, the quantity of the transverse slat of the intermediate region is greater than the quantity of the transverse slat of the side area.
In the technical scheme, limited in the weight of unmanned plane wing skeleton since intermediate region needs higher intensity
When, more transverse slats preferentially are set in the intermediate region of unmanned plane wing skeleton.
Preferably, the unmanned plane wing skeleton, which is divided into, is located in the middle intermediate region and positioned at the intermediate region two sides
Side area, the quantity of the transverse slat is three, and three transverse slats are respectively the first transverse slat, the second transverse slat, third transverse slat,
First transverse slat, the second transverse slat run through intermediate region, the side area of the unmanned plane wing skeleton, third transverse slat position
In the intermediate region of the unmanned plane wing skeleton.
In the technical scheme, third transverse slat is set in intermediate region, makes the intermediate region intensity of unmanned plane wing skeleton
It is bigger.
Preferably, the transverse slat, the first rib, the second rib are fixed by way of clamping.
In the technical scheme, the fixed form of clamping keeps unmanned plane wing skeleton easy for installation, and structure is simple, simplifies
The manufacturing procedures of components, reduces production cost.
Preferably, the unmanned plane wing skeleton further includes the first reinforcing rod, length of first reinforcing rod along wing
Direction setting, first reinforcing rod run through the first tip of first rib, second rib.
In the technical scheme, the first reinforcing rod further enhance the first tip of the first rib, the second rib it is strong
Degree.
Preferably, the unmanned plane wing skeleton, which is divided into, is located in the middle intermediate region and positioned at the intermediate region two sides
Side area, first reinforcing rod is located at the intermediate region of the unmanned plane wing skeleton.
In the technical scheme, since intermediate region needs higher intensity, the first reinforcing rod is preferentially set to unmanned plane
The intermediate region of wing skeleton.
Preferably, the unmanned plane wing skeleton further includes the second reinforcing rod, length of second reinforcing rod along wing
Direction setting, second reinforcing rod run through the first wide end of first rib.
In the technical scheme, the second reinforcing rod further enhances the intensity of the first wide end of the first rib.
Preferably, the edge of first rib is equipped with several first protrusions, the edge of second rib is equipped with several
Second protrusion, first protrusion, the second protrusion are matched with the groove of the covering covered on the unmanned plane wing skeleton.
In the technical scheme, the groove of covering fastens with the first protrusion, the second protrusion, ensure that covering and unmanned plane
The firmness of the connection of wing skeleton.
The present invention also provides a kind of unmanned plane wings, including above-mentioned unmanned plane wing skeleton.
In the technical scheme, the weight saving of unmanned plane wing skeleton and intensity does not subtract, adapt to unmanned plane to miniaturization,
The trend of lightweight development.
The present invention also provides a kind of unmanned planes, including above-mentioned unmanned plane wing skeleton.
In the technical scheme, it by above-mentioned unmanned plane wing skeleton, is applied on unmanned plane, weight saving and intensity are not
Subtract, to adapt to the trend that unmanned plane develops to miniaturization, lightweight.
Preferably, the unmanned plane further includes main body and covering, the unmanned plane wing skeleton, which is divided into, to be located in the middle
Between region and positioned at the side area of the intermediate region two sides, the main body is fixed on the centre of the unmanned plane wing skeleton
Region, the covering cover on the side area of the unmanned plane wing skeleton.
In the technical scheme, the stronger intermediate region of intensity is fixed with main body, it is ensured that the integral strength of unmanned plane.
On the basis of common knowledge of the art, above-mentioned each optimum condition, can any combination to get each preferable reality of the present invention
Example.
The positive effect of the present invention is that:
The unmanned plane wing skeleton and make unmanned plane by the way that the second rib is arranged comprising its unmanned plane wing, unmanned plane
The enhanced strength of wing skeleton can reduce the density of wing skeleton material under the premise of proof strength, reduce wing skeleton
Single-sheet thickness adapt to unmanned plane to accomplish weight saving and effect that intensity does not subtract and become to what miniaturization, lightweight developed
Gesture.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of unmanned plane wing skeleton of the present invention.
Fig. 2 is the enlarged diagram of the intermediate region of unmanned plane wing skeleton shown in FIG. 1.
Fig. 3 is the knot of the first reinforcing rod of removing of the intermediate region of unmanned plane wing skeleton shown in Fig. 2, the second reinforcing rod
Structure schematic diagram.
Fig. 4 is the partial enlarged view of unmanned plane wing skeleton shown in FIG. 1.
Fig. 5 is the structural schematic diagram of the covering of unmanned plane wing of the present invention.
Fig. 6 is the structural schematic diagram of unmanned plane wing of the present invention.
Fig. 7 is the structural schematic diagram of unmanned plane of the present invention.
Description of symbols
Unmanned plane wing skeleton 100
Transverse slat 1
First transverse slat 11
Second transverse slat 12
Third transverse slat 13
First rib 2
First wide end 21
First tip 22
First protrusion 23
Second rib 3
Second wide end 31
Second tip 32
Second protrusion 33
Connecting plate 4
First reinforcing rod 5
Second reinforcing rod 6
First through hole 7
Second through-hole 8
Intermediate region 101
Side area 102
Covering 200
Groove 201
Main body 300
Unmanned plane wing 400
Specific embodiment
The present invention is further illustrated below by the mode of embodiment, but does not therefore limit the present invention to the reality
It applies among a range.
It is as shown in Figures 1 to 4 an embodiment of unmanned plane wing skeleton 100 of the present invention.The unmanned plane wing skeleton 100
Including three transverse slats 1 and several first ribs 2, the first rib 2 is arranged along the cross section of wing, and transverse slat 1 is along the length side of wing
To setting, the both ends of the first rib 2 are respectively the first wide end 21 and the first tip 22, and the first wide end 21 and transverse slat 1 are fixed, and first
Tip 22 is protruding；Unmanned plane wing skeleton 100 further includes several second ribs 3, and the second rib 3 is located at adjacent two the
Between first tip 22 of one rib 2, the both ends of the second rib 3 are fixed with two adjacent 2 phases of the first rib respectively.
In the present embodiment, the quantity of transverse slat 1 is three；And in actual design process, it can also be according to different wings
Design requirement, change transverse slat 1 quantity.The quantity of transverse slat 1 depends on actual design requirement, is not limited to three.
In the present embodiment, the second rib 3 is set between the first tip 22 of two adjacent the first ribs 2, second
The both ends of rib 3 are fixed with two adjacent 2 phases of the first rib respectively.Second rib 3 plays and increases the of the first rib 2
The effect of the intensity at one tip 22, to increase the integral strength of unmanned plane wing skeleton 100.
The unmanned plane wing skeleton 100 of above structure, intensity are big compared with existing wing skeleton.Therefore, using above-mentioned knot
The unmanned plane wing skeleton 100 of structure can reduce the density of wing skeleton material under the premise of proof strength, reduce wing bone
The single-sheet thickness of frame adapts to unmanned plane and develops to miniaturization, lightweight to accomplish weight saving and effect that intensity does not subtract
Trend.
Above-mentioned transverse slat 1, the first rib 2, the second rib 3 are fixed by way of clamping.The fixed form of clamping, makes nobody
Machine wing skeleton 100 is easy for installation, and structure is simple, simplifies the manufacturing procedure of components, reduces production cost.
As shown in Figure 2 to Figure 3, the both ends of the second rib 3 are respectively the second wide end 31 and the second tip 32, the second tip 32
It is fixed with the first tip 22 of one of them the first rib 2, the connection of the second wide end 31 and another the first rib 2 and transverse slat 1
Place is fixed.Second rib 3 is fixed with two adjacent the first ribs 2 through the above way, can enhance first wing to the maximum extent
The intensity of rib 2.
Two adjacent the second ribs 3 are that the plane of symmetry is symmetrical to be located in the middle the first rib 2.Symmetrically arranged
Two ribs 3 can make the uniform force for being located in the middle the first rib 2.As shown in Figure 2 to Figure 3, two adjacent the second ribs
3 form triangular structure with transverse slat 1, and stable structure, intensity is big, and the intensity for being located in the middle the first rib 2 is made to obtain maximum journey
The enhancing of degree.
As shown in Figure 2 to Figure 3, which further includes several connecting plates 4, if connecting plate 4 will be adjacent
Dry the first rib 2, the second rib 3 link together.Connecting plate 4 plays the role of further increasing the intensity of the first rib 2.
Especially when two adjacent the second ribs 3 are fixed with the first tip 22 for being located in the middle the first rib 2 simultaneously, it will necessarily go out
The case where first tip 22 of remaining existing the first rib 2 is not connected with any second rib 3.At this point, using connecting plate 4 by phase
Adjacent several first ribs 2 are connected, it is ensured that the first rib 2 that the first tip 22 is not connected with the second rib 3 it is strong
Degree.
Above-mentioned connecting plate 4 is fixed by way of clamping with the first rib 2, the second rib 3.The fixed form of clamping, makes
Unmanned plane wing skeleton 100 is easy for installation, and structure is simple, simplifies the manufacturing procedure of components, reduces production cost.
As shown in Figure 1, unmanned plane wing skeleton 100 divides to be located in the middle intermediate region 101 and be located at intermediate region 101
The side area 102 of two sides.Intermediate region 101 needs higher intensity, therefore, unmanned plane wing skeleton 100 weight by
In limited time, connecting plate 4 preferentially is set in the intermediate region of unmanned plane wing skeleton 100 101.
Similarly, since intermediate region 101 needs higher intensity, unmanned plane wing skeleton 100 weight by limited time, it is excellent
More transverse slats 1, the i.e. quantity of the transverse slat 1 of intermediate region 101 first are set in the intermediate region of unmanned plane wing skeleton 100 101
The quantity of the transverse slat 1 of side area 102 can be greater than.As shown in Figure 2 to Figure 3, the quantity of transverse slat 1 is three, and three transverse slats 1 divide
Not Wei the first transverse slat 11, the second transverse slat 12, third transverse slat 13, the first transverse slat 11, the second transverse slat 12 run through unmanned plane wing skeleton
100 intermediate region 101, side area 102, third transverse slat 13 are located at the intermediate region 101 of unmanned plane wing skeleton 100.
The width of the side area 102 of above-mentioned unmanned plane wing skeleton 100 is less than the width of intermediate region 101, and second is horizontal
Plate 12 is between the first transverse slat 11, third transverse slat 13, the width of the width of the first transverse slat 11 less than the second transverse slat 12.It is flying
In the process, the intermediate stress of unmanned plane wing skeleton 100 is maximum, and forced area reduces to both ends to spread, therefore, side area
102 width is less than the width of intermediate region 101, the width of the first transverse slat 11 less than the second transverse slat 12 width, in weight one
The integral strength that can guarantee skeleton in the case where fixed to the maximum extent, is not susceptible to be broken.
As shown in Figures 2 and 3, which further includes the first reinforcing rod 5, and the first reinforcing rod 5 is along wing
Length direction setting, the first reinforcing rod 5 is through the first tip 22 of the first rib 2, the second rib 3.Specifically, such as Fig. 3
Shown, first through hole 7 runs through the first tip 22 of the first rib 2, the second rib 3, and the first reinforcing rod 5 is inserted into first through hole 7.
First reinforcing rod 5 further enhances the first tip 22 of the first rib 2, the intensity of the second rib 3.Due in
Between region 101 need higher intensity, the first reinforcing rod 5 is preferentially set to the intermediate region 101 of unmanned plane wing skeleton 100.
As shown in Figures 2 and 3, unmanned plane wing skeleton 100 further includes the second reinforcing rod 6, and the second reinforcing rod 6 is along wing
Length direction setting, the second reinforcing rod 6 run through the first wide end 21 of the first rib 2.Specifically, as shown in figure 3, the second through-hole
8 run through the first wide end 21 of the first rib 2, and the second reinforcing rod 6 is inserted into the second through-hole 8.Second reinforcing rod 6, further strengthens
The intensity of first wide end 21 of the first rib 2.
As shown in figure 4, the edge of the first rib 2 is equipped with several first protrusions 23, the edge of the second rib 3 is equipped with several the
Two protrusions 33, the groove 201 of covering 200 of first the 23, second protrusion 33 of protrusion with illiteracy on unmanned plane wing skeleton 100 is (such as
Shown in Fig. 5) it matches.The groove 201 of covering 200 fastens with the first protrusion 23, the second protrusion 33, and will be covered by glue
Skin 200 and the 100 phase adhesion of unmanned plane wing skeleton.
It is illustrated in figure 6 the unmanned plane wing 400 that covering 200 and unmanned plane wing skeleton 100 form, covering 200 covers
On the side area 102 of unmanned plane wing skeleton 100.It is illustrated in figure 7 nobody for using above-mentioned unmanned plane wing skeleton 100
Machine, the unmanned plane include main body 300 and unmanned plane wing 400, and main body 300 is fixed on the middle area of unmanned plane wing skeleton 100
Domain 101, covering 200 cover on the side area of unmanned plane wing skeleton 100 102.
Above-mentioned unmanned plane wing skeleton 100 is applied on unmanned plane, weight saving and intensity does not subtract, to adapt to nobody
The trend that machine develops to miniaturization, lightweight.
The present invention is not limited to the above-described embodiments, no matter making any variation in its shape or structure, all falls within this hair
Within bright protection scope.Protection scope of the present invention is defined by the appended claims, and those skilled in the art exists
Under the premise of without departing substantially from the principle and substance of the present invention, many changes and modifications may be made, but these
Change and modification each fall within protection scope of the present invention.
Claims (16)
1. a kind of unmanned plane wing skeleton, including at least one transverse slat and several first ribs, first rib is along wing
Cross section setting, the transverse slat are arranged along the length direction of wing, it is characterised in that:
The both ends of first rib are respectively the first wide end and the first tip, and first wide end is fixed with the transverse slat, institute
It is protruding to state the first tip；
The unmanned plane wing skeleton further includes several second ribs, and second rib is located at two adjacent first wings
Between first tip of rib, the both ends of second rib are mutually fixed with two adjacent first ribs respectively.
2. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the both ends of second rib are respectively second
Wide end and the second tip, second tip and the first tip of the first rib described in one of them are fixed, second wide end
It is fixed with the junction of the first rib and the transverse slat described in another.
3. unmanned plane wing skeleton as claimed in claim 1 or 2, it is characterised in that: second rib of adjacent two with
Being located in the middle first rib is that the plane of symmetry is symmetrical.
4. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the unmanned plane wing skeleton further includes several
Connecting plate, the connecting plate link together several adjacent described first ribs, the second rib.
5. unmanned plane wing skeleton as claimed in claim 4, it is characterised in that: the connecting plate and first rib, the
Two ribs are fixed by way of clamping.
6. unmanned plane wing skeleton as claimed in claim 4, it is characterised in that: the unmanned plane wing skeleton, which is divided into, to be located at
Between intermediate region and positioned at the side area of the intermediate region two sides, the connecting plate is located at the unmanned plane wing skeleton
Intermediate region.
7. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the unmanned plane wing skeleton, which is divided into, to be located at
Between intermediate region and positioned at the side area of the intermediate region two sides, the quantity of the transverse slat of the intermediate region is greater than described
The quantity of the transverse slat of side area.
8. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the unmanned plane wing skeleton, which is divided into, to be located at
Between intermediate region and positioned at the side area of the intermediate region two sides, the quantity of the transverse slat is three, three cross
Plate is respectively the first transverse slat, the second transverse slat, third transverse slat, and first transverse slat, the second transverse slat run through the unmanned plane wing bone
Intermediate region, the side area of frame, the third transverse slat are located at the intermediate region of the unmanned plane wing skeleton.
9. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the transverse slat, the first rib, the second rib are logical
The mode for crossing clamping is fixed.
10. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the unmanned plane wing skeleton further includes
One reinforcing rod, first reinforcing rod are arranged along the length direction of wing, and first reinforcing rod is through first rib
First tip, second rib.
11. unmanned plane wing skeleton as claimed in claim 10, it is characterised in that: the unmanned plane wing skeleton, which is divided into, to be located at
Intermediate intermediate region and positioned at the side area of the intermediate region two sides, first reinforcing rod is located at the unmanned plane machine
The intermediate region of wing skeleton.
12. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the unmanned plane wing skeleton further includes
Two reinforcing rods, second reinforcing rod are arranged along the length direction of wing, and second reinforcing rod is through first rib
First wide end.
13. unmanned plane wing skeleton as described in claim 1, it is characterised in that: the edge of first rib is equipped with several
First protrusion, the edge of second rib is equipped with several second protrusions, and first protrusion, the second protrusion are with illiteracy in the nothing
The groove of covering on man-machine wing skeleton matches.
14. a kind of unmanned plane wing, it is characterised in that: including the described in any item unmanned plane wing skeletons of claim 1 to 13.
15. a kind of unmanned plane, it is characterised in that: including the described in any item unmanned plane wing skeletons of claim 1 to 13.
16. unmanned plane as claimed in claim 15, it is characterised in that: the unmanned plane further includes main body and covering, the nothing
Man-machine wing skeleton, which is divided into, is located in the middle intermediate region and positioned at the side area of the intermediate region two sides, the main body is solid
It is scheduled on the intermediate region of the unmanned plane wing skeleton, the covering covers on the side area of the unmanned plane wing skeleton.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810360094.1A CN110386244A (en) | 2018-04-20 | 2018-04-20 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810360094.1A CN110386244A (en) | 2018-04-20 | 2018-04-20 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110386244A true CN110386244A (en) | 2019-10-29 |
Family
ID=68282757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810360094.1A Pending CN110386244A (en) | 2018-04-20 | 2018-04-20 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110386244A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055995A (en) * | 2019-12-31 | 2020-04-24 | 南京儒一航空机械装备有限公司 | Main beam body not easy to deform and processing technology thereof |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2014801A (en) * | 1932-10-25 | 1935-09-17 | Curtiss Aeroplane & Motor Co | Rib construction |
| JP2001048096A (en) * | 1999-08-06 | 2001-02-20 | Fuji Heavy Ind Ltd | Manufacturing method of composite wing |
| US20080245927A1 (en) * | 2007-04-05 | 2008-10-09 | Kulesha Richard L | Methods and systems for composite structural truss |
| US20130099063A1 (en) * | 2011-10-19 | 2013-04-25 | The Boeing Company | Segmented Aircraft Wing Having Solar Arrays |
| CN103832578A (en) * | 2012-11-21 | 2014-06-04 | 空中客车营运有限公司 | Modular structural assembly |
| CN203666969U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Bonded aerofoil architecture |
| CN104724280A (en) * | 2013-12-23 | 2015-06-24 | 空中客车营运有限公司 | Aircraft control surface |
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
| CN205010473U (en) * | 2015-08-26 | 2016-02-03 | 合肥工业大学 | Wing with quick assembly disassembly interfacing apparatus |
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| US20160332409A1 (en) * | 2015-05-15 | 2016-11-17 | Airbus Operations Limited | Aircraft component with closed box structure |
| CN106184697A (en) * | 2016-09-14 | 2016-12-07 | 北京航空航天大学 | A kind of straight line penetrating construction formula composite fuselage construction |
| WO2017051160A2 (en) * | 2015-09-21 | 2017-03-30 | Elson Andrew Charles | Foam aerofoil |
| CN106697258A (en) * | 2016-11-28 | 2017-05-24 | 西北工业大学 | A wing leading edge capable of improving aircraft anti-bird strike performance |
| US20170174313A1 (en) * | 2015-12-17 | 2017-06-22 | Airbus Operations Limited | Wing structure |
| CN208216976U (en) * | 2018-04-20 | 2018-12-11 | 北京京东尚科信息技术有限公司 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
-
2018
- 2018-04-20 CN CN201810360094.1A patent/CN110386244A/en active Pending
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2014801A (en) * | 1932-10-25 | 1935-09-17 | Curtiss Aeroplane & Motor Co | Rib construction |
| JP2001048096A (en) * | 1999-08-06 | 2001-02-20 | Fuji Heavy Ind Ltd | Manufacturing method of composite wing |
| US20080245927A1 (en) * | 2007-04-05 | 2008-10-09 | Kulesha Richard L | Methods and systems for composite structural truss |
| US20130099063A1 (en) * | 2011-10-19 | 2013-04-25 | The Boeing Company | Segmented Aircraft Wing Having Solar Arrays |
| CN103832578A (en) * | 2012-11-21 | 2014-06-04 | 空中客车营运有限公司 | Modular structural assembly |
| CN203666969U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Bonded aerofoil architecture |
| CN104724280A (en) * | 2013-12-23 | 2015-06-24 | 空中客车营运有限公司 | Aircraft control surface |
| US20160332409A1 (en) * | 2015-05-15 | 2016-11-17 | Airbus Operations Limited | Aircraft component with closed box structure |
| CN205010473U (en) * | 2015-08-26 | 2016-02-03 | 合肥工业大学 | Wing with quick assembly disassembly interfacing apparatus |
| WO2017051160A2 (en) * | 2015-09-21 | 2017-03-30 | Elson Andrew Charles | Foam aerofoil |
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
| US20170174313A1 (en) * | 2015-12-17 | 2017-06-22 | Airbus Operations Limited | Wing structure |
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| CN106184697A (en) * | 2016-09-14 | 2016-12-07 | 北京航空航天大学 | A kind of straight line penetrating construction formula composite fuselage construction |
| CN106697258A (en) * | 2016-11-28 | 2017-05-24 | 西北工业大学 | A wing leading edge capable of improving aircraft anti-bird strike performance |
| CN208216976U (en) * | 2018-04-20 | 2018-12-11 | 北京京东尚科信息技术有限公司 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055995A (en) * | 2019-12-31 | 2020-04-24 | 南京儒一航空机械装备有限公司 | Main beam body not easy to deform and processing technology thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2652661C (en) | A stringer for an aircraft wing and a method of forming thereof | |
| CN106335629B (en) | Fuselage spar structure with continuous integral fastened upper and lower chord sections | |
| US9457894B2 (en) | Variable-width aerodynamic device | |
| US2312219A (en) | Aircraft propeller | |
| US2074201A (en) | Airfoil used in aeronautics | |
| CN208216976U (en) | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it | |
| WO2020003239A3 (en) | Tail sitter | |
| CN205931233U (en) | Overlap joint structure of airfoil covering on spar edge strip | |
| CN110386244A (en) | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it | |
| EP1873056A2 (en) | Fixing system for a leading edge to the structure of an aircraft lift plane | |
| CN107512382B (en) | Combined aircraft | |
| US4148450A (en) | Model aircraft construction | |
| US20140131511A1 (en) | Aircraft lifting surface with variable sweep distribution along the span | |
| CN205906205U (en) | Combined material covers body structure | |
| CN206719525U (en) | A kind of unmanned plane fixes the fast assembling-disassembling attachment means of wing | |
| US2432396A (en) | Airplane wing | |
| US4003155A (en) | Model aircraft and package | |
| CN204937457U (en) | A kind of Material Stiffened Panel and there is its aerofoil and aircraft | |
| US10981645B2 (en) | Drag reduction systems for aircraft | |
| CN207292369U (en) | A kind of aircraft conversion deckle board | |
| CN108116652A (en) | Aircraft assembly | |
| CN108116653B (en) | Aircraft assembly | |
| CN216374979U (en) | Fixed wing corrugated structure and fixed wing unmanned aerial vehicle | |
| CN109795699A (en) | Aircraft hanging joint assembly | |
| CN209274881U (en) | A kind of rudder face honeycomb trailing edge component |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20210304 Address after: Room a1905, 19 / F, building 2, No. 18, Kechuang 11th Street, Daxing District, Beijing, 100176 Applicant after: Beijing Jingdong Qianshi Technology Co.,Ltd. Address before: 101, 1st floor, building 2, yard 20, Suzhou street, Haidian District, Beijing 100080 Applicant before: Beijing Jingbangda Trading Co.,Ltd. Effective date of registration: 20210304 Address after: 101, 1st floor, building 2, yard 20, Suzhou street, Haidian District, Beijing 100080 Applicant after: Beijing Jingbangda Trading Co.,Ltd. Address before: 100195 Beijing Haidian Xingshikou Road 65 West Cedar Creative Garden 4 District 11 Building East 1-4 Floor West 1-4 Floor Applicant before: BEIJING JINGDONG SHANGKE INFORMATION TECHNOLOGY Co.,Ltd. Applicant before: BEIJING JINGDONG CENTURY TRADING Co.,Ltd. |
|
| TA01 | Transfer of patent application right |