CN112373674B - Sensor unmanned aerial vehicle's wing connection structure, wing and unmanned aerial vehicle - Google Patents
Sensor unmanned aerial vehicle's wing connection structure, wing and unmanned aerial vehicle Download PDFInfo
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- CN112373674B CN112373674B CN202011302991.0A CN202011302991A CN112373674B CN 112373674 B CN112373674 B CN 112373674B CN 202011302991 A CN202011302991 A CN 202011302991A CN 112373674 B CN112373674 B CN 112373674B
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- wing
- skin
- unmanned aerial
- aerial vehicle
- spar
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a wing connecting structure of a sensor unmanned aerial vehicle, a wing and an unmanned aerial vehicle, wherein the connecting structure comprises: the plug comprises a plurality of stepped holes, a plurality of connecting pieces and a plurality of plugging elements; the multiple stepped holes are distributed on the skin along the edge strip direction of the wing framework and avoid the antenna unit, the large-diameter ends of the stepped holes sequentially penetrate through the glass fiber plate and the foam plate, and the small-diameter ends penetrate through the main bearing plate; the connecting holes are distributed on the edge strip of the wing framework and correspond to the stepped holes one by one; each connecting piece fixes the main bearing plate of the skin on the wing framework through a stepped hole and a connecting hole; each plugging element is filled in one stepped hole so as to complete the surface of the skin. The invention can meet the requirement of the structural integrity of the wing under the premise of ensuring that the antenna assembly in the wing can work normally, so that the connection process of the skin and the framework is feasible, and the connection strength meets the requirement.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a wing connecting structure of a sensor unmanned aerial vehicle, a wing and an unmanned aerial vehicle.
Background
The unmanned sensor plane comprises a sensor component, can scan within a certain angle range and is used for a platform of the unmanned sensor early warning machine, so that the wave-transmitting performance within the working radiation range of the unmanned plane can meet the requirement, the reflecting layer is electrically continuous, the wing structure meets the integrity requirement, the skin and framework connection process is feasible, and the connection strength meets the requirement. Traditional sensor unmanned aerial vehicle's sensor subassembly is independent of organism component, receives the restriction that the ripples required passes through, and antenna aperture area is less relatively, and the working capacity is limited. If the antenna unit and the wing skin are designed integrally, the aperture area of the antenna can be expanded to a greater extent. The integrated design of the antenna unit and the wing skin ensures that the connection structure cannot damage the antenna unit when the skin is connected with the framework. In addition, the foam interlayer of the integrated skin is thick, and the traditional mechanical connection method is difficult.
Therefore, the wing connecting structure of the sensor unmanned aerial vehicle, the wing and the unmanned aerial vehicle are expected to be developed, the requirement of structural integrity of the wing can be met on the premise that the antenna assembly in the wing can work normally, the skin and framework connecting process is feasible, and the connecting strength meets the requirement.
Disclosure of Invention
The invention aims to provide a wing connecting structure of a sensor unmanned aerial vehicle, a wing and an unmanned aerial vehicle, which meet the requirement of structural integrity of the wing on the premise of ensuring that an antenna assembly in the wing can work normally, so that the connection process of a skin and a framework is feasible, and the connection strength meets the requirement.
In order to achieve the above object, the present invention provides a wing connection structure of a sensor unmanned aerial vehicle, where the wing includes a wing skeleton and a skin, the skin covers the wing skeleton, the skin includes a main bearing plate, a foam plate and a glass fiber plate, which are sequentially stacked from inside to outside, the foam plate has an antenna unit therein, and the connection structure includes: the plug comprises a plurality of stepped holes, a plurality of connecting pieces and a plurality of plugging elements;
the plurality of stepped holes are distributed on the skin along the edge strip direction of the wing framework and avoid the antenna unit, the large-diameter ends of the stepped holes sequentially penetrate through the glass fiber plate and the foam plate, and the small-diameter ends penetrate through the main bearing plate;
the connecting holes are distributed on the edge strip of the wing framework and correspond to the stepped holes one by one;
each connecting piece fixes the main bearing plate of the skin on the wing framework through one stepped hole and one connecting hole;
each blocking element is filled in one stepped hole so as to complete the surface of the skin.
Optionally, the blocking element comprises a foam column and a glass cloth;
the foam column is matched with the large-diameter end of the stepped hole in size, the foam column is filled in the large-diameter end, and the bottom of the foam column is bonded with the main bearing plate;
the glass cloth covers the top surfaces of the foam columns and tightly connects the top surfaces of the foam columns with the glass fiber board of the skin;
the small-diameter end of the stepped hole is used for installing the connecting piece.
Optionally, the glass cloth is a double-layer glass cloth.
Optionally, the connecting member includes a bolt and a nut, and the bolt passes through the stepped hole and the connecting hole in sequence and is tightly connected with the nut.
Optionally, the nut is a supporting plate nut and is fixed to one end, facing the inner side of the wing frame, of the connecting hole.
Optionally, the flange of the wing skeleton includes a front spar, a rear spar, and a plurality of central ribs connected between the front spar and the rear spar, the plurality of front edge ribs being sequentially disposed along a length direction of the front spar on a forward end surface of the front spar, the plurality of rear edge ribs being sequentially disposed along a length direction of the rear spar on a rearward end surface of the rear spar;
the rim strips avoid the antenna elements inside the skin.
Optionally, the main bearing plate is a carbon fiber plate.
The invention also provides an unmanned aerial vehicle wing comprising:
a wing skeleton;
the upper skin and the lower skin cover the wing framework, the upper skin and the lower skin have the same structure and comprise a main bearing plate, a foam plate and a glass fiber plate which are sequentially overlapped from inside to outside, and an antenna unit is arranged in the foam plate;
in the wing connecting structure, the upper skin and the lower skin are respectively connected to the wing framework through the connecting structure.
Optionally, the flange of the wing skeleton includes a front spar, a rear spar, and a plurality of central ribs connected between the front spar and the rear spar, the plurality of front edge ribs being sequentially disposed along a length direction of the front spar on a forward end surface of the front spar, the plurality of rear edge ribs being sequentially disposed along a length direction of the rear spar on a rearward end surface of the rear spar;
the rim strips avoid the antenna elements inside the skin.
The invention also provides a sensor unmanned aerial vehicle which comprises the unmanned aerial vehicle wing.
The invention has the beneficial effects that:
1. according to the connecting structure, the shoulder hole is formed in the skin, so that the connecting piece directly connects the main bearing plate of the skin to the edge strip of the wing framework, the antenna unit in the skin is avoided, the connecting process of the skin and the wing framework is feasible on the premise that the antenna assembly in the wing can normally work, the connecting strength meets the requirement, and the sealing element is filled in the shoulder hole, so that the requirement on the structural integrity of the wing is met.
2. The wing of the unmanned aerial vehicle can meet the requirement of structural integrity of the wing on the premise of ensuring that the antenna assembly in the wing can work normally, so that the connection process of the skin and the wing framework is feasible, the connection strength meets the requirement, the wave-transmitting performance in the working radiation range of the unmanned aerial vehicle can be ensured, and the working radiation range of the unmanned aerial vehicle can be expanded.
3. The unmanned aerial vehicle sensor has the advantages of complete wing structure, reliable connection between the skin and the wing framework, good wave-transmitting performance and large working radiation range.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows an exploded view of a wing of a drone according to one embodiment of the invention.
Figure 2 shows a cross-sectional view of a wing of a drone according to one embodiment of the invention.
Figure 3 shows a top view of a wing of a drone according to one embodiment of the invention.
FIG. 4 shows a schematic view of a wing connection structure according to one embodiment of the invention.
Description of the reference numerals
1. Covering the skin; 2. a lower skin; 3. a wing skeleton; 4. a front beam; 5. a rear beam; 6. a leading edge rib; 7. a center rib; 8. a trailing edge rib; 9. an antenna unit; 10. a glass fiber board; 11. a foam board; 12. a main bearing plate; 13. a bolt; 14. a nut; 15. a foam column; 16. double-layer glass cloth; 17. a stepped hole; 18. and connecting the holes.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
The invention discloses a wing connecting structure of a sensor unmanned aerial vehicle, wherein a wing comprises a wing framework and a skin, the skin covers the wing framework, the skin comprises a main bearing plate, a foam plate and a glass fiber plate which are sequentially overlapped from inside to outside, an antenna unit is arranged in the foam plate, and the connecting structure comprises: the plug comprises a plurality of stepped holes, a plurality of connecting pieces and a plurality of plugging elements;
the multiple stepped holes are distributed on the skin along the edge strip direction of the wing framework and avoid the antenna unit, the large-diameter ends of the stepped holes sequentially penetrate through the glass fiber plate and the foam plate, and the small-diameter ends penetrate through the main bearing plate;
the connecting holes are distributed on the edge strip of the wing framework and correspond to the stepped holes one by one;
each connecting piece fixes the main bearing plate of the skin on the wing framework through a stepped hole and a connecting hole;
each plugging element is filled in one stepped hole so as to complete the surface of the skin.
Specifically, the connecting structure of the invention enables the connecting piece to directly connect the main bearing plate of the skin to the edge strip of the wing framework by arranging the stepped hole on the skin and avoids the antenna unit inside the skin, so that the connecting process of the skin and the wing framework is feasible on the premise of ensuring the normal work of the antenna assembly inside the wing, the connecting strength meets the requirement, and the plugging element is filled in the stepped hole to meet the requirement of the structural integrity of the wing.
Alternatively, the blocking element comprises a foam column and a glass cloth;
the size of the foam column is matched with that of the large-diameter end of the stepped hole, the foam column is filled in the large-diameter end, and the bottom of the foam column is bonded with the main bearing plate;
the glass cloth covers the top surface of the foam column and tightly connects the top surface of the foam column with the glass fiber board of the covering;
the small-diameter end of the stepped hole is used for installing a connecting piece.
Specifically, the foam is light in weight, and the weight of the wing cannot be increased by adopting foam column filling; the top surface of the foam column covered by the glass cloth is tightly connected with the glass fiber plate of the covering, so that the foam column can be prevented from falling off, the surface of the wing is smooth, and the wave-transmitting performance can be ensured.
Alternatively, the glass cloth is a double-layer glass cloth.
Specifically, double-layer glass cloth is adopted for fixing, and the firmness of the connecting structure is guaranteed.
Alternatively, the connecting member includes a bolt and a nut, and the bolt passes through the stepped hole and the connecting hole in sequence and is fastened and connected with the nut.
Particularly, the stepped hole is formed, and the diameter of the large-diameter end is larger, so that the operation of bolt connection is facilitated.
As an alternative, the nut is a common nut when the first skin is installed and is fixed at one end, facing the inner side of the wing framework, of the connecting hole.
Specifically, when the second skin is installed, the common nut can be replaced by a supporting plate nut due to the fact that double-sided operation cannot be conducted, and the common nut is riveted to the inner surface of the edge strip corresponding to the connecting hole in advance.
As an alternative, the edge strip of the wing framework comprises a front spar, a rear spar and a plurality of central wing ribs, wherein the front spar and the rear spar are arranged in the span direction of the wing, the central wing ribs are connected between the front spar and the rear spar, the front edge ribs are sequentially arranged on the forward end surface of the front spar along the length direction of the front spar, and the rear edge ribs are sequentially arranged on the rearward end surface of the rear spar along the length direction of the rear spar;
the flanges avoid the antenna elements inside the skin.
Specifically, the wing framework can be made of carbon fiber or aluminum alloy.
As an alternative, the main bearing plate is a carbon fiber plate.
The invention also discloses an unmanned aerial vehicle wing, comprising:
a wing skeleton;
the upper skin and the lower skin are covered on the wing framework, the upper skin and the lower skin have the same structure and comprise a main bearing plate, a foam plate and a glass fiber plate which are sequentially overlapped from inside to outside, and an antenna unit is arranged in the foam plate;
in the wing connecting structure, the upper skin and the lower skin are respectively connected to the wing framework through the connecting structure.
Specifically, the wing of the unmanned aerial vehicle can meet the requirement of structural integrity of the wing on the premise of ensuring that the antenna assembly in the wing can work normally, so that the connection process of the skin and the wing framework is feasible, the connection strength meets the requirement, the wave-transmitting performance in the working radiation range of the unmanned aerial vehicle can be ensured, and the working radiation range of the unmanned aerial vehicle can be enlarged.
As an alternative, the edge strip of the wing framework comprises a front spar, a rear spar and a plurality of central wing ribs, wherein the front spar and the rear spar are arranged in the span direction of the wing, the central wing ribs are connected between the front spar and the rear spar, the front edge ribs are sequentially arranged on the forward end surface of the front spar along the length direction of the front spar, and the rear edge ribs are sequentially arranged on the rearward end surface of the rear spar along the length direction of the rear spar;
the flanges avoid the antenna elements inside the skin.
The invention also discloses a sensor unmanned aerial vehicle which comprises the unmanned aerial vehicle wing.
Specifically, the unmanned aerial vehicle sensor has the advantages of complete wing structure, reliable connection of the skin and the wing framework, good wave-transmitting performance and large working radiation range.
Examples
Fig. 1 shows an exploded view of the wing of the drone of the present embodiment; figure 2 shows a cross-sectional view of the wing of the drone of the present embodiment; figure 3 shows a top view of the wing of the drone of the present embodiment; fig. 4 shows a schematic view of the wing connection structure of the present embodiment.
As shown in fig. 1, the wing of the unmanned aerial vehicle comprises a wing framework 3, an upper skin 1 and a lower skin 2, and as shown in fig. 2, the upper skin 1 and the lower skin 2 cover the wing framework 3; the upper skin 1 and the lower skin 2 have the same structure, and as shown in fig. 4, the upper skin and the lower skin comprise a main bearing plate 12 made of a carbon fiber plate, a foam plate 11 and a glass fiber plate 10 which are sequentially stacked from inside to outside, and an antenna unit 9 is arranged in the foam plate 11;
as shown in fig. 3, the edge strip of the wing skeleton 3 includes a front spar 4 and a rear spar 5 arranged in the span direction of the wing, a plurality of central ribs 7 connected between the front spar 4 and the rear spar 5, a plurality of front edge ribs 6 arranged in sequence along the length direction of the front spar 4 on the forward end surface of the front spar 4, and a plurality of rear edge ribs 8 arranged in sequence along the length direction of the rear spar 5 on the rearward end surface of the rear spar 5, and the position of the edge strip avoids the antenna units 9 inside the upper skin 1 and the lower skin 2;
as shown in fig. 4, a plurality of stepped holes 17 are distributed on the skin (upper skin 1 or lower skin 2) along the edge strip direction of the wing framework 3 and avoid the antenna unit 9, the diameter of the large-diameter end of the stepped hole 17 is phi 15, the diameter of the small-diameter end is phi 5, the large-diameter end of the stepped hole 17 sequentially penetrates through the glass fiber plate 10 and the foam plate 11, and the small-diameter end penetrates through the main bearing plate 12; the diameter of the connecting hole 18 is phi 5, and a plurality of connecting holes 18 are distributed on the edge strip of the wing framework 3 and correspond to the stepped holes 17 one by one; the bolt 13 of M5 passes through the stepped hole 17 and the connecting hole 18 in sequence and is fastened and connected with the nut 14 to fix the main bearing plate 12 of the skin on the wing framework 3; when the skin is installed, common nuts can be replaced by supporting plate nuts at positions which cannot be operated on two sides, and the common nuts are riveted on the inner surfaces of the edge strips at the corresponding connecting holes in advance; the foam column 15 is in a step shape and is filled in the step hole, and the bottom of the foam column 15 is bonded with the main bearing plate 12; a double layer of glass cloth 16 is laid over the top surface of the foam columns 15 and tightly connects the top surface of the foam columns 15 with the glass fiber plate 10 of the skin to complete the skin surface.
The unmanned aerial vehicle wing of this embodiment can satisfy the requirement of wing structural integrity under the prerequisite of guaranteeing that the inside antenna module of wing can normally work for skin and skeleton connection technology are feasible, and joint strength satisfies the requirement.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (9)
1. The utility model provides a sensor unmanned aerial vehicle's wing connection structure, the wing includes wing skeleton and covering, the covering cover in the wing skeleton, the covering includes main bearing plate, cystosepiment and the glass fiber board of superpose from inside to outside in proper order, built-in antenna unit in the cystosepiment, a serial communication port, connection structure includes: the plug comprises a plurality of stepped holes, a plurality of connecting pieces and a plurality of plugging elements;
the plurality of stepped holes are distributed on the skin along the edge strip direction of the wing framework and avoid the antenna unit, the large-diameter ends of the stepped holes sequentially penetrate through the glass fiber plate and the foam plate, and the small-diameter ends of the stepped holes penetrate through the main bearing plate;
the connecting holes are distributed on the edge strip of the wing framework and correspond to the stepped holes one by one;
each connecting piece fixes the main bearing plate of the skin on the wing framework through one stepped hole and one connecting hole;
each plugging element is filled in one stepped hole so as to complete the surface of the skin;
the blocking element comprises a foam column and glass cloth;
the foam column is matched with the large-diameter end of the stepped hole in size, the foam column is filled in the large-diameter end, and the bottom of the foam column is bonded with the main bearing plate;
the glass cloth covers the top surfaces of the foam columns and tightly connects the top surfaces of the foam columns with the glass fiber board of the skin;
the small-diameter end of the stepped hole is used for installing the connecting piece.
2. The wing connection structure of sensor unmanned aerial vehicle of claim 1, characterized in that, the glass cloth is double-layer glass cloth.
3. The wing connection structure of the sensor unmanned aerial vehicle of claim 1, wherein the connecting piece comprises a bolt and a nut, and the bolt passes through the stepped hole and the connecting hole in sequence and is tightly connected with the nut.
4. The wing connection structure of sensor unmanned aerial vehicle of claim 3, characterized in that, the nut is a splint nut, is fixed in the connecting hole towards the inboard one end of wing skeleton.
5. The wing connection structure of a sensor drone of claim 1, wherein the bead of the wing skeleton includes a front spar, a back spar, and a plurality of central ribs connected between the front spar and the back spar disposed along the span direction of the wing, a plurality of front edge ribs disposed sequentially along the length direction of the front spar on a forward facing end surface of the front spar, a plurality of back edge ribs disposed sequentially along the length direction of the back spar on a back facing end surface of the back spar;
the rim strips avoid the antenna elements inside the skin.
6. The wing connection structure of sensor unmanned aerial vehicle of claim 1, wherein the main bearing plate is a carbon fiber plate.
7. An unmanned aerial vehicle wing, comprising:
a wing skeleton;
the upper skin and the lower skin cover the wing framework, the upper skin and the lower skin have the same structure and comprise a main bearing plate, a foam plate and a glass fiber plate which are sequentially overlapped from inside to outside, and an antenna unit is arranged in the foam plate;
the wing connection structure of any one of claims 1 to 6, wherein the upper skin and the lower skin are respectively connected to the wing skeleton through the connection structure.
8. The unmanned aerial vehicle wing of claim 7, wherein the bead of the wing skeleton comprises a front spar, a rear spar, and a plurality of central ribs connected between the front spar and the rear spar disposed along the span direction of the wing, a plurality of front edge ribs disposed sequentially along the length direction of the front spar on a forward facing end surface of the front spar, a plurality of rear edge ribs disposed sequentially along the length direction of the rear spar on a rearward facing end surface of the rear spar;
the rim strips avoid the antenna elements inside the skin.
9. A sensor drone, characterized in that it comprises a drone wing according to claim 7 or 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011302991.0A CN112373674B (en) | 2020-11-19 | 2020-11-19 | Sensor unmanned aerial vehicle's wing connection structure, wing and unmanned aerial vehicle |
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| CN202011302991.0A CN112373674B (en) | 2020-11-19 | 2020-11-19 | Sensor unmanned aerial vehicle's wing connection structure, wing and unmanned aerial vehicle |
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| CN112373674B true CN112373674B (en) | 2022-08-09 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5625999A (en) * | 1994-08-23 | 1997-05-06 | International Paper Company | Fiberglass sandwich panel |
| CN1213999A (en) * | 1996-03-22 | 1999-04-14 | 波音公司 | Determinant spar assembly |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN108023180A (en) * | 2017-11-29 | 2018-05-11 | 中国航空工业集团公司济南特种结构研究所 | A kind of antenna house of assorted fibre interlayer |
| CN109204778A (en) * | 2017-07-07 | 2019-01-15 | 波音公司 | The covering of aircraft-panel interface |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101630774B (en) * | 2009-08-07 | 2012-09-26 | 北京玻钢院复合材料有限公司 | Glass steel radar cover single element and forming method thereof |
| CN103682559B (en) * | 2013-11-29 | 2015-10-28 | 北方通用电子集团有限公司 | Radar antenna linear array assembly technology |
| US9879704B2 (en) * | 2015-04-09 | 2018-01-30 | The Boeing Company | Systems and methods for assembling aircraft wing skins |
| CN205429161U (en) * | 2015-12-22 | 2016-08-03 | 中国航空工业集团公司济南特种结构研究所 | Radome sandwich structure |
| US10329008B2 (en) * | 2016-06-24 | 2019-06-25 | The Boeing Company | Fluid-tight mechanical fastening system and associated structural assembly |
| CN106142814A (en) * | 2016-07-08 | 2016-11-23 | 陕西飞机工业（集团）有限公司 | A kind of adhering method solving foam plastics core and metal skin delamination |
| US10179640B2 (en) * | 2016-08-24 | 2019-01-15 | The Boeing Company | Wing and method of manufacturing |
| CN107651163B (en) * | 2017-10-23 | 2023-06-20 | 重庆通用航空产业集团有限公司 | Fixed wing unmanned aerial vehicle outer wing structure and manufacturing method thereof |
| CN111267413B (en) * | 2019-12-31 | 2020-12-18 | 中电科芜湖钻石飞机制造有限公司 | Composite material intelligent skin and manufacturing method thereof |
-
2020
- 2020-11-19 CN CN202011302991.0A patent/CN112373674B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5625999A (en) * | 1994-08-23 | 1997-05-06 | International Paper Company | Fiberglass sandwich panel |
| CN1213999A (en) * | 1996-03-22 | 1999-04-14 | 波音公司 | Determinant spar assembly |
| CN109204778A (en) * | 2017-07-07 | 2019-01-15 | 波音公司 | The covering of aircraft-panel interface |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN108023180A (en) * | 2017-11-29 | 2018-05-11 | 中国航空工业集团公司济南特种结构研究所 | A kind of antenna house of assorted fibre interlayer |
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