CN110294100A - Fixed Wing AirVehicle and its wing - Google Patents
Fixed Wing AirVehicle and its wing Download PDFInfo
- Publication number
- CN110294100A CN110294100A CN201810247905.7A CN201810247905A CN110294100A CN 110294100 A CN110294100 A CN 110294100A CN 201810247905 A CN201810247905 A CN 201810247905A CN 110294100 A CN110294100 A CN 110294100A
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- Prior art keywords
- wing
- rib
- conduit
- root
- attachment beam
- 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.)
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- 230000007704 transition Effects 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000005253 cladding Methods 0.000 claims description 2
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 21
- 238000009434 installation Methods 0.000 description 14
- 230000005611 electricity Effects 0.000 description 6
- 238000010276 construction Methods 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000003447 ipsilateral effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
Abstract
The present invention proposes that a kind of Fixed Wing AirVehicle and its wing, the wing include skeleton, and skeleton includes attachment beam, the first conduit, the second conduit, the back rest and multiple ribs, and attachment beam extends along spanwise.Multiple ribs include the root rib that attachment beam is successively installed on along spanwise, switching rib and end rib.First conduit is located at the rear side of attachment beam, and the first conduit is installed on root rib, and can penetrate for one first guide rod along spanwise.The back rest is located at the rear side of the first conduit, and connect with each rib.
Description
Technical field
The present invention relates to a kind of Fixed Wing AirVehicle and the wings of Fixed Wing AirVehicle.
Background technique
Fixed Wing AirVehicle is a kind of using very extensive aircraft, generally includes fuselage and the machine for being fixed on fuselage
Wing etc., wherein wing is indispensable critical component.Existing wing generally comprises skeleton and mask, and mask is coated on bone
Outside frame, the structure of skeleton is directly related to the intensity of wing.
By taking VTOL fixed-wing unmanned plane as an example, the skeleton of wing generally includes the girder being arranged along spanwise, main
Beam is connect with fuselage, and multiple ribs are equipped on girder, multiple ribs from one end of girder to other end dense distribution, i.e., from
To the uniform dense arrangement in end, this makes the weight of skeleton excessive for the root of wing, causes the weight of wing excessive, and materials compared with
It is more, so that higher cost.Meanwhile existing wing is difficult to accurately position, dismounting is inconvenient.
Above- mentioned information are only used for reinforcing the understanding to background of the invention, therefore it disclosed in the background technology part
It may include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
It is an object of the present invention to overcoming above-mentioned the deficiencies in the prior art, providing a kind of can guarantee wing intensity
Under the premise of, reduce the Fixed Wing AirVehicle of wing weight and the wing of Fixed Wing AirVehicle.
It is another object of the present invention to overcome above-mentioned the deficiencies in the prior art, a kind of consolidating convenient for wing dismounting is provided
Determine the wing of rotor aircraft and Fixed Wing AirVehicle.
Additional aspect and advantage of the invention will be set forth in part in the description, and partly will be from description
It is apparent from, or can practice through the invention and acquistion.
According to an aspect of the present invention, a kind of wing of Fixed Wing AirVehicle, including skeleton, the skeleton include connection
Beam, the first conduit, the back rest and multiple ribs, the attachment beam extend along spanwise.Multiple ribs include along span side
To the root rib, switching rib and end rib for being successively installed on the attachment beam.First conduit is located at the connection
The rear side of beam, first conduit is installed on the root rib, and can penetrate for one first guide rod along spanwise.After described
Beam is located at the rear side of first conduit, and connect with each rib.
According to an embodiment of the present invention, the wing further includes the second conduit, and second conduit is located at the company
The front side of beam is connect, second conduit is installed on the root rib, and can penetrate for one second guide rod along spanwise.
According to an embodiment of the present invention, the quantity of the root rib and the switching rib is two, described
The quantity of end rib is one.
According to an embodiment of the present invention, the length of first conduit is greater than the length of second conduit；And/or
The diameter of first conduit is greater than the diameter of second conduit.
According to an embodiment of the present invention, the attachment beam is equipped at least one first lightening hole, and described first subtracts
Repeated hole is between the switching rib and the end rib.
According to an embodiment of the present invention, at least one described rib is equipped with the second lightening hole.
According to an embodiment of the present invention, the wing further includes the third conduit, and the third conduit is located at institute
The rear side of the first conduit is stated, the third conduit is installed on the root rib, and can wear for a third guide rod along spanwise
Enter.
According to an embodiment of the present invention, the wing further includes mask, and the mask is coated on outside the skeleton, and
With root area, the cladding switching rib transition region and the end for coating the end rib for coating the root rib
The wall thickness of portion region, the root area and the transition region is all larger than the wall thickness of the end regions.
According to an embodiment of the present invention, the wing further includes aileron, and the aileron is located at the rear side of the back rest,
And it is hinged with the back rest.
According to an aspect of the present invention, a kind of Fixed Wing AirVehicle, the wing including fuselage and any of the above-described.It is described
The first guide rod and second guide rod are equipped with for installing the position of wing on fuselage.First guide rod cooperation penetrates described the
One conduit, second guide rod penetrate second guide rod.
As shown from the above technical solution, the present invention has at least one of following advantages and good effect:
Can be reinforced by wing root position of the root rib to wing, by switching rib to the transit location of wing into
Row is reinforced, and is reinforced by end position of the end rib to wing.To reinforce the key position of wing, can save
The rib for going other positions advantageously reduces the weight of wing, reduces cost.
Rib can be connected by the back rest, form a frame with rib and attachment beam, kept rib more firm, improve
The intensity of skeleton.
When installing wing, the first guide rod of fuselage can be penetrated the first conduit along spanwise, determining wing can be saved
The time of installation site keeps installation process more convenient, is conducive to improve installation effectiveness.Pass through the first conduit and the first guide rod
Cooperate the installation direction of bootable wing, it is easy to disassemble.
Detailed description of the invention
Its example embodiment is described in detail by referring to accompanying drawing, above and other feature of the invention and advantage will become
It is more obvious.
Fig. 1 is the schematic diagram of the skeleton of the wing of embodiment of the present invention Fixed Wing AirVehicle；
Fig. 2 is the cross-sectional view of the mask of the wing of embodiment of the present invention Fixed Wing AirVehicle；
Fig. 3 is the schematic diagram of embodiment of the present invention Fixed Wing AirVehicle.
In figure: 1, attachment beam；101, the first lightening hole；2, rib；201, the second lightening hole；21, root rib；22, turn
Connect rib；23, end rib；3, the back rest；4, the first conduit；5, the second conduit；6, third conduit；7, mask；8, aileron；9,
One guide rod；10, the second guide rod；11, adapter；12, connecting rod；13, electricity adjusts cover board；14, steering engine cover board；15, pitot；100, machine
Body；200, wing；300, wing platform.
Specific embodiment
Example embodiment is described more fully with reference to the drawings.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein.Although using the term of relativity, example in this specification
Relativeness of the component for another component of icon is described such as "upper", "lower", but these terms are used for this explanation
Merely for convenient in book, for example, with reference to the accompanying drawings described in exemplary direction.It is appreciated that, if the device of icon overturn
It is set to turn upside down, then the component described in "upper" will be as the component in "lower".The term of other relativities, such as
"top", "bottom" etc. also make have similar meaning.When certain structure is at other structures "upper", it is possible to refer to that certain structural integrity is formed
In in other structures, or refers to that certain structure is " direct " and be arranged in other structures, or refer to that certain structure is set by another structure " indirect "
It sets in other structures.Term "one", " one ", "the" and " described " be to indicate that there are one or more elements/composition portions
Point/etc.；Term " comprising " and " having " to indicate the open meaning being included and refer in addition to list element/
Also may be present except component part/wait other element/component part/etc.；Term " first ", " second " and " third " etc. is only made
It is used for label, is not the quantity limitation to its object.
A kind of wing is provided in example embodiment of the present invention, is used for Fixed Wing AirVehicle, Fixed Wing AirVehicle can be
VTOL fixed-wing unmanned plane or other Fixed Wing AirVehicles, will not enumerate herein.It is only solid with VTOL below
Determine to be illustrated for wing unmanned plane, which may include fuselage and wing.It is, of course, also possible to be other fixations
Rotor aircraft.
As depicted in figs. 1 and 2, the wing of present embodiment can have the root along spanwise distribution, switching part and end
Portion, and the wing may include skeleton, which may include attachment beam 1, rib 2, the back rest 3, the first conduit 4, the second conduit
5, third conduit 6, mask 7 and aileron 8.
As shown in Figure 1, in one embodiment, attachment beam 1 can be slab construction, shape can be rectangle or other
Shape, and attachment beam 1 can extend along spanwise.
The first lightening hole 101 can be equipped on attachment beam 1, the shape of the first lightening hole 101 can be circle, but not as
Limit, can also be rectangle, ellipse or other shapes, will not enumerate herein.Meanwhile first the quantity of lightening hole 101 can
Be it is multiple, specifically can be depending on the length of attachment beam 1, to reduce the weight of attachment beam 1 for example, five, six, seven etc.
Amount.
As shown in Figure 1, in one embodiment, rib 2 is also possible to plate-like structure, thickness can be with attachment beam 1
Thickness is identical, might be less that the thickness of attachment beam 1.Notch can be equipped on attachment beam 1, rib 2 is pluggable in the notch, and
With 1 square crossing of attachment beam.It is of course also possible to which notch is arranged on rib 2, attachment beam 1 is plugged in the notch.Rib 2
On can also be equipped with the second lightening hole 201, the shape and size of the second lightening hole 201 not do particular determination herein.Second lightening hole
201 quantity is two, and the two sides of two the second lightening hole 201 separation attachment beams 1 are conducive to reduce the weight of rib 2
Reduce the weight of skeleton.
The quantity of rib 2 is multiple, and multiple ribs 2 are along spanwise distribution, i.e., from the root of wing to the end of wing
Part cloth, and each rib 2, with 1 square crossing of attachment beam, specific connection type is with reference to above rib 2 and attachment beam 1
Connection type, this will not be detailed here.In multiple ribs 2, root rib 21, switching rib 22 and end rib 23 are included at least,
And root rib 21, switching rib 22 and end rib 23 are sequentially distributed along from the root of wing to end.In addition, each rib
2 length can be identical, but not limited to this, the length of each rib 2 can also be different.
As shown in Figure 1, for example, the quantity of rib 2 is six, including two root ribs, 21, two switching ribs
22 and an end rib 23, in which:
Two root ribs 21 can be set to position corresponding with the root of wing on attachment beam 1, and a root wing in parallel
Rib 21 is located at attachment beam 1 close to one end of fuselage, another root rib 21 is located at previous root rib 21 close to wing end
Side.Two root ribs 21 are not in contact with each other, but the spacing of the two does not do particular determination herein.Pass through two root ribs 21
The root of wing is supported, guarantees the intensity of the root of wing.
Two switching ribs 22 can be set to root rib 21 close to the side of the end of wing in parallel, and be connected to attachment beam
Position corresponding with the switching part of wing on 1.Two switching ribs 22 are not in contact with each other, but the spacing of the two does not do special limit herein
It is fixed.The switching part of wing is supported by two switching ribs 22, guarantees the intensity of the switching part of wing.
End rib 23 can be set to the one end of attachment beam 1 far from fuselage, the i.e. end of wing.Due to wing end by
Power is usually smaller than root and switching part, as soon as thus only the end of wing can be supported by end rib 23, can protect
The intensity for demonstrate,proving the end of wing is conducive to avoid rib 2 excessive, weight is caused to increase.Each first lightening hole 101 can be located at
It is located at the region between switching rib 22 and end rib 23 on attachment beam 1.
In other embodiments of the present invention, the quantity of rib 2 can also be not limited to six, as long as at least can include root
Portion's rib 21, switching rib 22 and end rib 23, this will not be detailed here.
As shown in Figure 1, in one embodiment, the back rest 3 can be slab construction, can be located at the rear side of attachment beam 1 and with
Attachment beam 1 is parallel.Meanwhile the back rest 3 can be connect with the rear end of each rib 2 simultaneously, to pass through attachment beam 1, the back rest 3 and rib
2 form a closed frame, are conducive to the intensity for improving skeleton.In addition, two root ribs 21 and close to root rib 21
One switching rib 22 may pass through the back rest 3, and to be then connected only to the back rest 3 close for end rib 23 and another switching rib 22
The side of attachment beam 1, and it is not passed through the back rest 3, in order to install the aileron 8 of wing.Wherein, the rear side of attachment beam 1 is close to machine
The side of the leeward of the wing, the rear end of rib 2 are one end of the leeward close to wing.
As shown in Figure 1, in one embodiment, the first conduit 4 can be located at connection between attachment beam 1 and the back rest 3
The rear side of beam 1, and the first conduit 4 can extend along the center line of wing, that is to say, that attachment beam 1 is located at the center line of wing
Front side.
As shown in Figure 1, the first conduit 4 has the both ends of perforation, and one end may pass through two root ribs 21, and the other end can
Across a switching rib 22 close to root rib 21, so that the first conduit 4 is installed on root rib 21 and switching rib
Between 22.It can be equipped with the first guide rod 9 for installing the region of wing on fuselage, and the first guide rod 9 can be plugged in along spanwise
In first conduit 4, to be conducive to the peace for determining wing by the cooperation guidance installation wing of the first guide rod 9 and the first conduit 4
Holding position improves installation effectiveness.
As shown in Figure 1, in one embodiment, the second conduit 5 can be located at the front side of attachment beam 1, and be located at two roots
Between rib 21, one end passes through a root rib 21, and the other end may pass through another root rib 21.Meanwhile second conduit 5
Length less than the length of the first conduit 4, and the diameter of the second conduit 5 is less than the diameter of the first conduit 4.For installing on fuselage
The region of wing is equipped with the second guide rod 10, and the second guide rod 10 can be plugged in the second conduit 5 along spanwise, so as into one
Step is conducive to the installation site for determining wing, improves peace by the cooperation guidance installation wing of the second guide rod 10 and the second conduit 5
Fill efficiency.
As shown in Figure 1, in one embodiment, third conduit 6 can be located at the rear side of attachment beam 1, and be located at two roots
Between rib 21, one end passes through a root rib 21, and the other end may pass through another root rib 21.Meanwhile third conduit 6
Length can be identical as the length of the second conduit 5, and the diameter of third conduit 6 is smaller than the diameter of the second conduit 5.It is used on fuselage
Be equipped with third guide rod in the region of installation wing, and third guide rod can be plugged in third conduit 6 along spanwise, so as into
One step is conducive to the installation site for determining wing, improves peace by the cooperation guidance installation wing of third guide rod and third conduit 6
Fill efficiency.
As depicted in figs. 1 and 2, in one embodiment, mask 7 can be coated on outside skeleton, to form the shell of wing, be covered
Plate 7 can be spliced by multiple plates, curved slab, and the quantity and size of surface plate and curved slab do not do particular determination herein, only
It wants that skeleton can be coated.Meanwhile mask 7 can have root area, transition region and end regions, wherein root area packet
It is overlying on outside root rib 21, transition region is coated on outside switching rib 22, and end regions are coated on outside end rib 23.Due to
And root and switching part stress it is larger, and end stress is smaller, thus, can make the wall thickness S of root area1And transition region
Wall thickness S2It is all larger than the wall thickness S of end regions3, and the wall thickness of mask 7 is gradually thinned from transition region to end regions, is protecting
While demonstrate,proving the intensity of mask 7, the wall thickness of mask 7 is reduced, is conducive to mitigate weight.
As shown in Figure 1, in one embodiment, aileron 8 can be located at the rear side of the back rest 3, and the back rest 3 is articulated with without rib
2 regions being pierced by can adjust flight attitude by the rotation of aileron 8.The specific structure of aileron 8 can refer to the pair of existing wing
The wing, this will not be detailed here.
As shown in Figure 1, in one embodiment, wing can also include adapter 11, electricity adjust, steering engine and pitot 15,
Wherein:
Adapter 11 can have fixed part and mounting portion, which can be set in mask 7 and be located at two switching ribs
Between 22, which can be at least fixedly connected with a switching rib 22.The mounting portion can be pierced by mask 7, and mountable one
Connecting rod 12, the connecting rod 12 can be perpendicular to spanwises, and the mountable rotor for VTOL on connecting rod 12.Meanwhile it transferring
The quantity of part 11 can be two, and two adapters 11 can live apart the two sides of attachment beam 1, and connecting rod 12 can pass through two switchings simultaneously
Same connecting rod 12 is fixed in part 11.
Electricity reconciles steering engine can be in mask 7, and is located in the space that rib 2, attachment beam 1 and the back rest 3 surround, mask 7
On can be equipped with electricity and adjust installing port and steering engine installing port, electricity is adjusted and can be covered with electricity on installing port and adjust cover board 13, and steering engine installing port can cover
It is stamped steering engine cover board 14.
Pitot 15 can be set to the end of mask 7, for detecting the stagnation pressure and static pressure of air-flow, and the pressure data that will be measured
Send the devices such as computer and the flying instruments of aircraft to.
The wing of the fixed-wing unmanned vehicle of example embodiment of the present invention, can be by root rib 21 to the root of wing
Portion is reinforced, and by transferring, rib 22 reinforces the switching part of wing, by end rib 23 to the end of wing into
Row is reinforced.To reinforce the key position of wing, the rib of other positions can be saved, the weight of wing is advantageously reduced
Amount.Meanwhile can be connected rib 2 by the back rest 3, frame is collectively formed with attachment beam 1, rib 2, the strong of skeleton can be improved
Degree.In addition, the first guide rod 9 of fuselage can be penetrated the first conduit 4 when installing wing along spanwise, determining machine can be saved
Time of wing installation site, and guide the installation direction of wing improves installation effectiveness and easy to disassemble.
Embodiment of the present invention also provides a kind of Fixed Wing AirVehicle, which can be VTOL and fix
Wing unmanned plane, but not limited to this, is also possible to other Fixed Wing AirVehicles, is once only with VTOL fixed-wing unmanned plane
Example is illustrated.
As shown in Figure 1 to Figure 3, the Fixed Wing AirVehicle of present embodiment may include fuselage 100 and wing 200.
As shown in figure 3, in one embodiment, the top of fuselage 100 can be formed with wing platform 300, the two sides of wing platform 300
It can be used for installing wing 200, and the two sides of wing platform 300 can be equipped with the first guide rod 9, and the first guide rod 9 prolongs along spanwise
It stretches.
Wing 200 is the wing of any of the above-described embodiment, and the quantity of wing 200 is two, and is symmetrically set in wing platform
300 two sides, by taking the wing 200 of side as an example, the first guide rod 9, which can cooperate, penetrates the first ipsilateral conduit 4, thus to wing
200 are oriented to and are positioned.In addition, can also be by welding, riveting or in the way of screw connection etc. by skeleton and mask 7 and the wing
Platform 300 connects, and realizes the fixation of wing 200.
In other embodiments of the present invention, the second guide rod 10 and third guide rod can be also equipped on above-mentioned wing platform 300,
Second guide rod 10, which can cooperate, penetrates the second conduit 5, and third guide rod, which can cooperate, penetrates third conduit 6, and the second guide rod 10 can fit through
Enter the second conduit 5, further the installation of wing 200 is guided and positioned.
The beneficial effect of the Fixed Wing AirVehicle of embodiment of the present invention is said in the embodiment of above-mentioned wing
Bright, this will not be detailed here.
It should be appreciated that the present invention is not limited in its application to the detailed construction and arrangement of the component of this specification proposition
Mode.The present invention can have other embodiments, and can realize and execute in many ways.Aforesaid deformation form and
Modification is fallen within the scope of the present invention.It should be appreciated that this disclosure and the present invention of restriction extend in text
And/or it is mentioned in attached drawing or all alternative combinations of two or more apparent independent features.It is all these different
Combination constitutes multiple alternative aspects of the invention.Embodiment described in this specification illustrates to become known for realizing the present invention
Best mode, and will enable those skilled in the art using the present invention.
Claims (10)
1. a kind of wing of Fixed Wing AirVehicle, including skeleton, which is characterized in that the skeleton includes:
Attachment beam (1) extends along spanwise；
Multiple ribs (2), root rib (21), switching rib including being successively installed on the attachment beam (1) along spanwise
(22) and end rib (23)；
First conduit (4), is located at the rear side of the attachment beam (1), and first conduit (4) is installed on the root rib
(21), it and can be penetrated for one first guide rod (9) along spanwise；
The back rest (3), is located at the rear side of first conduit (4), and connect with each rib (2).
2. wing according to claim 1, which is characterized in that the wing further include:
Second conduit (5), is located at the front side of the attachment beam (1), and second conduit (5) is installed on the root rib
(21), it and can be penetrated for one second guide rod (10) along spanwise.
3. wing according to claim 1, which is characterized in that the root rib (21) and switching rib (22)
Quantity is two, and the quantity of the end rib (23) is one.
4. wing according to claim 2, which is characterized in that the length of first conduit (4) is greater than described second and leads
Manage the length of (5)；And/or
The diameter of first conduit (4) is greater than the diameter of second conduit (5).
5. wing according to claim 1, which is characterized in that the attachment beam (1) is equipped at least one first lightening hole
(101), and first lightening hole (101) is between the switching rib (22) and the end rib (23).
6. wing according to claim 1, which is characterized in that at least one described rib (2) is equipped with the second lightening hole
(201)。
7. wing according to any one of claims 1 to 6, which is characterized in that the wing further include:
Third conduit (6), is located at the rear side of first conduit (4), and the third conduit (4) is installed on the root rib
(21), it and can be penetrated for a third guide rod along spanwise.
8. wing according to any one of claims 1 to 6, which is characterized in that the wing further include:
Mask (7), is coated on outside the skeleton, and has and turn described in the root area for coating the root rib (21), cladding
It connects rib (22) transition region and coats the end regions of the end rib (23), the root area and the transition region
Wall thickness be all larger than the wall thickness of the end regions.
9. wing according to any one of claims 1 to 6, which is characterized in that the wing further include:
Aileron (8) is located at the rear side of the back rest (3), and hinged with the back rest (3).
10. a kind of Fixed Wing AirVehicle characterized by comprising
Fuselage (100) is equipped with the first guide rod 9 for installing the position of wing (200) on the fuselage (100)；And
The described in any item wings of claim 1 to 9 (200), the first guide rod (9) cooperation penetrate first conduit (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810247905.7A CN110294100A (en) | 2018-03-23 | 2018-03-23 | Fixed Wing AirVehicle and its wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810247905.7A CN110294100A (en) | 2018-03-23 | 2018-03-23 | Fixed Wing AirVehicle and its wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110294100A true CN110294100A (en) | 2019-10-01 |
Family
ID=68026154
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810247905.7A Pending CN110294100A (en) | 2018-03-23 | 2018-03-23 | Fixed Wing AirVehicle and its wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110294100A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202429344U (en) * | 2011-11-30 | 2012-09-12 | 中国南方航空工业(集团)有限公司 | Unmanned aerial vehicle |
| CN205633013U (en) * | 2016-05-03 | 2016-10-12 | 中国航天空气动力技术研究院 | Rotatory wind wheel circular rector control type wing |
| CN206031756U (en) * | 2016-08-30 | 2017-03-22 | 西安翔宇航空科技股份有限公司 | Unmanned aerial vehicle wing |
| CN208007270U (en) * | 2018-03-23 | 2018-10-26 | 北京京东尚科信息技术有限公司 | Fixed Wing AirVehicle and its wing |
-
2018
- 2018-03-23 CN CN201810247905.7A patent/CN110294100A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202429344U (en) * | 2011-11-30 | 2012-09-12 | 中国南方航空工业(集团)有限公司 | Unmanned aerial vehicle |
| CN205633013U (en) * | 2016-05-03 | 2016-10-12 | 中国航天空气动力技术研究院 | Rotatory wind wheel circular rector control type wing |
| CN206031756U (en) * | 2016-08-30 | 2017-03-22 | 西安翔宇航空科技股份有限公司 | Unmanned aerial vehicle wing |
| CN208007270U (en) * | 2018-03-23 | 2018-10-26 | 北京京东尚科信息技术有限公司 | Fixed Wing AirVehicle and its wing |
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