CN201971148U - Intelligent skin with honeycomb interlayer structure - Google Patents
Intelligent skin with honeycomb interlayer structure Download PDFInfo
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- CN201971148U CN201971148U CN 201120041460 CN201120041460U CN201971148U CN 201971148 U CN201971148 U CN 201971148U CN 201120041460 CN201120041460 CN 201120041460 CN 201120041460 U CN201120041460 U CN 201120041460U CN 201971148 U CN201971148 U CN 201971148U
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- honeycomb
- skin
- honeycomb interlayer
- interlayer
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Abstract
The utility model belongs to the field of aircraft structure designs, and relates to an intelligent skin with a honeycomb interlayer structure, which is applicable to aircrafts. The intelligent skin comprises an inner skin (1), an outer skin (2) and a honeycomb interlayer (3) positioned in between, and an electronic antenna element (4) is embedded in the honeycomb interlayer (3). The inner skin (1) and the outer skin (2) are glass fiber-reinforced plastics or fiber fabric layers. The structure of the intelligent skin is compact, both the inner and the outer surfaces of the intelligent skin do not need to be heaved, the structure is simple and reliable, load transfer is reasonable, the weight is light, the electronic antenna is embedded in the honeycomb structure, and the wave transmissivity is high.
Description
Technical field
The utility model belongs to the aeroplane structure design field, relates to a kind of honeycomb sandwich construction smart skins that is applicable on the aircraft.
Background technology
The radar aerial of conventional airplane is operated in 360 degree scopes, and outwards the electromagnetic signal of emission is leaked easily and realized.Conventional airplane has the antenna that much protrudes in fuselage appearance at aircraft surfaces, and these antenna is destroyed easily, and has influenced the aerodynamic configuration of aircraft, has increased resistance, has lowered airworthiness.The antenna requirements that aircraft electronic antenna task aspect proposes concrete, the antenna that requires to adopt must can strengthen aircraft electronic countermeasure, stealthy, communication function, reduces the reflectivity of aircraft communication antenna, increase voice frequency communication context.Under the traction of this demand, by structure characteristic analysis, tail nose of wing and wing tip position in the housing construction, fuselage and radome all possess the condition of using smart skins.The domestic smart skins structure that the electronic antenna element can be wrapped up that still is not used on the aircraft owing to blockade on new techniques, still also has correlation technique abroad for inquiring at present.
Summary of the invention
The purpose of this utility model: a kind of compact conformation is provided, and simple and reliable, power transmission is reasonable, lightweight antenna and structure-integrated smart skins.
The technical solution of the utility model:
A kind of honeycomb sandwich construction smart skins, described honeycomb sandwich construction smart skins comprises inside panel 1, exterior skin 2, honeycomb interlayer 3, described honeycomb interlayer 3 is between inside panel 1 and exterior skin 2, described honeycomb interlayer 3 has been embedded in electronic antenna element 4, described inside panel 1 has circular hole 5, and the feeder line head of the electronic antenna element in the described honeycomb interlayer is connected with interior of aircraft equipment by circular hole.
Described inside panel 1 and exterior skin 2 are glass-felt plastic or fabric shop layer.
Advantage of the present utility model: this honeycomb sandwich construction smart skins compact conformation, covering surfaces externally and internally all need not projection, simple and reliable for structure, power transmission is reasonable, in light weight, electronic antenna is embedded in honeycomb structure, wave is good.
Description of drawings:
Fig. 1 is the structural representation of this honeycomb sandwich construction smart skins;
Fig. 2 is the section-drawing of this honeycomb sandwich construction smart skins;
Wherein, 1 inside panel, 2 exterior skins, 3 honeycomb interlayers, 4 electronic antenna elements, 5 circular holes.
The specific embodiment:
Below in conjunction with accompanying drawing this smart skins structure is described in further details.See also Fig. 1 and Fig. 2.
A kind of honeycomb sandwich construction smart skins, described honeycomb sandwich construction smart skins comprises inside panel 1, exterior skin 2, honeycomb interlayer 3, described honeycomb interlayer 3 is between inside panel 1 and exterior skin 2, described honeycomb interlayer 3 has been embedded in electronic antenna element 4, described inside panel 1 has circular hole 5, and the feeder line head of the electronic antenna element in the described honeycomb interlayer is connected with interior of aircraft equipment by circular hole.
Described inside panel 1 and exterior skin 2 are glass-felt plastic or fabric shop layer.
This smart skins structural principle is characterised in that, the electronic antenna element is installed among the honeycomb interlayer, replaces traditional antenna, to realize various functions such as communication.On inside panel 1, the position at electronic antenna 4 places has feeder line circular hole 5 for antenna feed the end of a thread.This honeycomb interlayer is inlayed in the conformal antenna of electronic antenna, and the covering surfaces externally and internally all need not projection, and the feeder line head of electronic antenna is connected with data line.The smart skins structure is connected by the structure of attaching parts with other suitable positions of fuselage wing or aircraft, has guaranteed the rational power transmission of aircaft configuration.
1 and 2 is inside and outside two-layer Advanced composite material stressed-skin constructions, and the thickness of inside and outside two-layer covering is 1.0mm, and basic shop layer is [45/-45/45/-45].The 3rd, one deck honeycomb interlayer between inside and outside two-layer covering, honeycomb core are selected NH-1-2.75-48 paper wasp nest for use, and the fuse height is 8mm, and density is 48g/mm3.All post glued membrane on the contact surface of honeycomb core and interior exterior skin, the slit filled and process glue SY-P14 between honeycomb core and skin panel.The 4th, be embedded in the electronic antenna element between the honeycomb interlayer 3, transmit and receive various electronic signals.In order to protect and fixing electronic antenna element, on the binding face of electronic antenna element and honeycomb core, post one deck glued membrane.
Referring to Fig. 1, this smart skins structure comprises inside and outside two-layer Advanced composite material covering 1 and 2, and gross thickness is 2mm, and its effect is to guarantee construction profile, for antenna element provides support structure; Every layer of covering formed by 4 layers of shop layer laying, and thickness in monolayer is 0.25mm.The basic shop layer of interior exterior skin is [45/-45/45/-45].
Packed height is the honeycomb interlayer 3 of 8mm between interior exterior skin, and honeycomb interlayer is selected NH-1-2.75-48 paper wasp nest for use, and band height is 8mm, and density is 48g/mm3.All post glued membrane on the contact surface of honeycomb interlayer and interior exterior skin, the slit filled and process glue SY-P14 between honeycomb interlayer and skin panel.The effect of glued membrane and foamed glue is the fixed cellular interlayer, avoid making and process of the test in the electronic antenna element be offset.
During manufacturing, earlier exterior skin 2 is spread layer according to design drawing, on exterior skin 2, place honeycomb interlayer 3 then.Milling goes out several square holes of 40 * 40 on the honeycomb interlayer 3, on the binding face of exterior skin 2, paste 1 layer of glued membrane FM-73M, in square hole, put into earlier then and be of a size of 40 * 40 * 3 honeycomb interlayer fritter, on this honeycomb interlayer fritter, place several electronic antenna elements 4, and then add 1 40 * 40 * 3 honeycomb core fritter, respectively paste 1 layer of glued membrane FM-73M on the contact surface of electronic antenna element and 2 honeycomb core fritters.On the honeycomb core binding face, use SY-P11 that alveolus pellet and former honeycomb core are bonded together.On honeycomb interlayer 3, continue to finish the shop layer of inside panel 1 then, on inside panel 1, process feeder line circular hole 5 at last according to design.
Referring to Fig. 2, electronic antenna element 4 is positioned among the honeycomb interlayer 3, paste one deck glued membrane between electronic antenna element and the honeycomb core, and at the position, slit of honeycomb core and covering filled and process glue SY-P14, with fixing electronic antenna element, prevent that antenna element from slippage or damage taking place when covering and honeycomb core are stressed.In the position of electronic antenna element 4, on inside panel 1, open feeder hole 10.
Claims (2)
1. honeycomb sandwich construction smart skins, it is characterized in that, described honeycomb sandwich construction smart skins comprises inside panel [1], exterior skin [2], honeycomb interlayer [3], described honeycomb interlayer [3] is positioned between inside panel [1] and the exterior skin [2], described honeycomb interlayer [3] has been embedded in electronic antenna element [4], described inside panel [1] has circular hole [5], and the feeder line head of the electronic antenna element in the described honeycomb interlayer is connected with interior of aircraft equipment by circular hole.
2. honeycomb sandwich construction smart skins according to claim 1 is characterized in that, described inside panel [1] and exterior skin [2] are glass-felt plastic or fabric shop layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120041460 CN201971148U (en) | 2011-02-17 | 2011-02-17 | Intelligent skin with honeycomb interlayer structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120041460 CN201971148U (en) | 2011-02-17 | 2011-02-17 | Intelligent skin with honeycomb interlayer structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201971148U true CN201971148U (en) | 2011-09-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120041460 Expired - Lifetime CN201971148U (en) | 2011-02-17 | 2011-02-17 | Intelligent skin with honeycomb interlayer structure |
Country Status (1)
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| CN (1) | CN201971148U (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103029825A (en) * | 2012-12-11 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Embedded antenna installation mouth frame |
| CN103552252A (en) * | 2013-10-25 | 2014-02-05 | 中国电子科技集团公司第三十九研究所 | Manufacture method of high-precision carbon fiber composite antenna panel |
| CN106956765A (en) * | 2017-02-15 | 2017-07-18 | 南京航空航天大学 | A kind of carbon fiber fuselage unmanned plane for improving DVB receiving sensitivity |
| CN109494449A (en) * | 2018-07-13 | 2019-03-19 | 中国航空工业集团公司济南特种结构研究所 | A kind of conformal antenna cover |
| CN110718741A (en) * | 2019-10-16 | 2020-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Bearable sandwich structure of integrated antenna array |
| CN111029770A (en) * | 2019-12-26 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Bearable sandwich structure of vertical antenna array |
| CN111186201A (en) * | 2018-11-15 | 2020-05-22 | 航天特种材料及工艺技术研究所 | Double-skin wave-absorbing honeycomb sandwich structure and preparation method thereof |
| CN111267413A (en) * | 2019-12-31 | 2020-06-12 | 中电科芜湖钻石飞机制造有限公司 | Composite material intelligent skin and manufacturing method thereof |
| EP3715104A1 (en) * | 2019-03-25 | 2020-09-30 | The Boeing Company | Systems and methods for creating a honeycomb core with integrated electronic components |
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN112407235A (en) * | 2020-11-19 | 2021-02-26 | 航天彩虹无人机股份有限公司 | Upper skin opening structure for sensor unmanned aerial vehicle wing, wing and unmanned aerial vehicle |
| CN112615152A (en) * | 2020-12-11 | 2021-04-06 | 中国电子科技集团公司第三十八研究所 | Large thin-wall honeycomb antenna housing for motor-driven radar |
| CN113809534A (en) * | 2021-09-18 | 2021-12-17 | 中国电子科技集团公司第三十八研究所 | Ultra-wide bandwidth wave beam embedded end-fire skin antenna |
| US11292206B2 (en) | 2019-03-25 | 2022-04-05 | The Boeing Company | Systems and methods for creating a honeycomb core with venting pathways |
| US11479004B2 (en) | 2019-03-25 | 2022-10-25 | The Boeing Company | Systems and methods for creating a honeycomb core with venting pathways |
-
2011
- 2011-02-17 CN CN 201120041460 patent/CN201971148U/en not_active Expired - Lifetime
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103029825A (en) * | 2012-12-11 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Embedded antenna installation mouth frame |
| CN103552252A (en) * | 2013-10-25 | 2014-02-05 | 中国电子科技集团公司第三十九研究所 | Manufacture method of high-precision carbon fiber composite antenna panel |
| CN106956765A (en) * | 2017-02-15 | 2017-07-18 | 南京航空航天大学 | A kind of carbon fiber fuselage unmanned plane for improving DVB receiving sensitivity |
| CN109494449A (en) * | 2018-07-13 | 2019-03-19 | 中国航空工业集团公司济南特种结构研究所 | A kind of conformal antenna cover |
| CN111186201A (en) * | 2018-11-15 | 2020-05-22 | 航天特种材料及工艺技术研究所 | Double-skin wave-absorbing honeycomb sandwich structure and preparation method thereof |
| US11292225B2 (en) | 2019-03-25 | 2022-04-05 | The Boeing Company | Systems and methods for creating a honeycomb core with integrated electronic components |
| US11479004B2 (en) | 2019-03-25 | 2022-10-25 | The Boeing Company | Systems and methods for creating a honeycomb core with venting pathways |
| US11292206B2 (en) | 2019-03-25 | 2022-04-05 | The Boeing Company | Systems and methods for creating a honeycomb core with venting pathways |
| EP3715104A1 (en) * | 2019-03-25 | 2020-09-30 | The Boeing Company | Systems and methods for creating a honeycomb core with integrated electronic components |
| CN110718741A (en) * | 2019-10-16 | 2020-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Bearable sandwich structure of integrated antenna array |
| CN111029770A (en) * | 2019-12-26 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Bearable sandwich structure of vertical antenna array |
| CN111267413A (en) * | 2019-12-31 | 2020-06-12 | 中电科芜湖钻石飞机制造有限公司 | Composite material intelligent skin and manufacturing method thereof |
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN112407235A (en) * | 2020-11-19 | 2021-02-26 | 航天彩虹无人机股份有限公司 | Upper skin opening structure for sensor unmanned aerial vehicle wing, wing and unmanned aerial vehicle |
| CN112615152A (en) * | 2020-12-11 | 2021-04-06 | 中国电子科技集团公司第三十八研究所 | Large thin-wall honeycomb antenna housing for motor-driven radar |
| CN112615152B (en) * | 2020-12-11 | 2022-07-01 | 中国电子科技集团公司第三十八研究所 | Large thin-wall honeycomb antenna housing for motor-driven radar |
| CN113809534A (en) * | 2021-09-18 | 2021-12-17 | 中国电子科技集团公司第三十八研究所 | Ultra-wide bandwidth wave beam embedded end-fire skin antenna |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110914 |
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| CX01 | Expiry of patent term |