CN201699124U - Novel embedded composite intelligent skin antenna structure - Google Patents
Novel embedded composite intelligent skin antenna structure Download PDFInfo
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- CN201699124U CN201699124U CN2010202221383U CN201020222138U CN201699124U CN 201699124 U CN201699124 U CN 201699124U CN 2010202221383 U CN2010202221383 U CN 2010202221383U CN 201020222138 U CN201020222138 U CN 201020222138U CN 201699124 U CN201699124 U CN 201699124U
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Abstract
The utility model discloses a novel embedded composite intelligent skin antenna structure. A whole antenna structure is formed by embedding a micro-strip array antenna into the honeycomb core body of the sandwich structure of composite. The embedded composite intelligent skin antenna structure comprises an upper panel, a core body cover plate, the prepacked micro-strip array antenna, the core body, a lower panel and a glue joint layer. The core body cover plate is located above the prepacked micro-strip array antenna. The prepack protection of the micro-strip array antenna is realized through an encapsulation box cover. The utility model can serve as the skin structure of various aerocrafts and greatly reduce the structural weight of the aerocraft when meeting the load bearing and communication requirements of the aerocraft.
Description
Technical field
The utility model relates to a kind of antenna structure, specifically, relate to a kind of functions such as carrying, dimension shape, stealthy, microwave communication of integrating, can effectively alleviate aircraft weight and keep the novel embedded composite material intelligent skin antenna structure of the good aerodynamic configuration of aircraft.
Background technology
At present, the antenna of aircraft radars and communication system often protrudes from body surface with the form that knife-edge or radar radome fairing coat, and has destroyed the desirable aerodynamic configuration of aircraft, has increased aerodynamic drag, influence the radar signal feature, also increased aircraft manufacturing and cost of system maintenance.Existing open source literature " utilizes the structure resonance principle design and manufacturing composite material intelligent structure of radiation field " (" smart material and structure ", the 14th the 2nd phase of volume of April in 2005: 441～448 pages .) characteristics by analysis of Interlayer Structure and slot antenna in the literary composition, Composite Sandwich structure and slot antenna are merged, design and made the absolute construction of the composite material intelligent structure that is used for containing of mobile communication of single slot antenna transmitter unit, the result shows the composite material intelligent structure than the bandwidth of exposed antenna wideer (increasing by 10%), and it is higher to gain.But the work of this article does not relate to micro-strip array antenna, does not consider that glue-line directly covers the influence of transmitter unit to composite material intelligent structure electrical property, does not relate to intelligence structure and integrally-built fusion yet.The utility model proposes a kind of new configuration that micro-strip array antenna is embedded into after pre-packaged in the composite material sandwich structure, this configuration is under the situation of electrical performance indexes that fully guarantees antenna and integrally-built bearing capacity, antenna and structure are optimized, realized the conformal of aerial array and housing construction, obtained to integrate functions such as carrying, dimension shape, stealthy, microwave communication, can effectively alleviate aircraft weight and keep the novel embedded composite material intelligent skin antenna structure of the good aerodynamic configuration of aircraft.
The utility model content
The technical problems to be solved in the utility model is to provide a kind of functions such as carrying, dimension shape, stealthy, microwave communication of integrating, and can effectively alleviate aircraft weight and keep the novel embedded composite material intelligent skin antenna structure of the good aerodynamic configuration of aircraft.
For solving the problems of the technologies described above, the utility model proposes a kind of new configuration that micro-strip array antenna is embedded into after pre-packaged in the composite material sandwich structure, this configuration is optimized antenna and structure under the situation of electrical performance indexes that fully guarantees antenna and integrally-built bearing capacity.The utility model embedded composite material intelligent skin antenna structure is that Combination Design becomes overall structure by top panel, core body cover plate, pre-packaged micro-strip array antenna, core body, lower panel and bonding layer structure.One groove is arranged at the core body top of described embedded composite material intelligent skin antenna structure, and depth of groove is the thickness sum of core body cover plate, pre-packaged micro-strip array antenna and pre-packaged micro-strip array antenna both sides bonding layer; Described core body upper grooves, core body cover plate, pre-packaged micro-strip array antenna, the length and width size of pre-packaged micro-strip array antenna both sides bonding layer and the length and width consistent size of micro-strip array antenna; The length and width size of described top panel, core body, lower panel and other bonding layers is consistent with the applied structure of embedded composite material intelligent skin antenna structure.
The core body cover plate of described embedded composite material intelligent skin antenna structure and core body are that the ripple rate is higher than 70% light composite material, any one of optional foam of material or cellular-core.Any one of optional Nomex honeycomb of cellular-core or glass cloth cellular material, optional hexagon of shape or rhombus or rectangle or sinusoidal and the hexagon of reinforcing band is arranged.Desirable 2～the 15mm of the thickness of core body cover plate, the desirable 10～25mm of core body thickness.
The pre-packaged micro-strip array antenna of described embedded composite material intelligent skin antenna structure becomes overall structure by encapsulation lid and micro-strip array antenna plate by splicing.The encapsulation lid carries out pre-packaged protection to micro-strip array antenna, avoids bonding layer to cover the micro-strip array antenna transmitter unit, and the micro-strip array antenna electrical property is exerted an influence; Any one of the polymer matrix composites that the optional E glass fibre of enclosure cover material, S glass fibre, D glass fibre and quartz glass fibre strengthen; The encapsulation lid is shaped as band groove rectangular structure, its length and width size and micro-strip array antenna length and width consistent size, the wall thickness and the desirable 1～5mm of top thickness of encapsulation lid; Desirable 2～the 15mm of height of encapsulation lid.Micro-strip array antenna is for setting the micro-strip array antenna of resonance frequency.
Any one of the polymer matrix composites that the optional E glass fibre of described top panel and lower panel, S glass fibre, D glass fibre and quartz glass fibre etc. strengthen; Desirable 0.4～the 0.7mm of the thickness of panel.
Described bonding layer can be selected LWF-1, LWF-2, J47A, J47C and J95 intermediate temperature setting glued membrane for use, and every layer of film thickness is 0.1mm, can select 1～5 layer for use.
The utility model embedded composite material intelligent skin antenna structure can not only guarantee the aerodynamic configuration that aircraft is good, promote the aircraft stealth effect, alleviate the construction weight and the volume of aircraft, satisfy structural bearing and pass the mechanical property requirements of carrying, and can have outstanding microwave signal ability to communicate.
Description of drawings
Below in conjunction with accompanying drawing the utility model embedded composite material intelligent skin antenna structure is described in further detail.
Fig. 1 is the schematic diagram of the utility model embedded composite material intelligent skin antenna structure.
Fig. 2 is the schematic diagram of the pre-packaged micro-strip array antenna of the utility model embedded composite material intelligent skin antenna structure.
Fig. 3 is the front view of the encapsulation lid of the utility model embedded composite material intelligent skin antenna structure.
Fig. 4 is the vertical view of the encapsulation lid of the utility model embedded composite material intelligent skin antenna structure.
Among the figure, 1. top panel 2. core body cover plates 3. pre-packaged micro-strip array antenna 4. core bodys 5. lower panels
6. bonding layer 7. encapsulates lids 8. bonding layers 9. micro-strip array antennas
Embodiment
Embodiment one
Fig. 1 shows the utility model embedded composite material intelligent skin antenna structure, and it comprises top panel 1, core body cover plate 2, pre-packaged micro-strip array antenna 3, core body 4, lower panel 5 and bonding layer 6, and Combination Design becomes overall structure.Described integrally-built top panel 1 and lower panel 5 are selected intermediate temperature setting low dielectric-loss glass cloth polymer matrix composites for use, and its thickness is 0.4mm;
Described core body cover plate 2 and core body 4 material selection Nomex honeycombs, the thickness of core body cover plate 2 is 2mm, the thickness of core body 4 is 20mm;
Described bonding layer 6 material selection LWF-2 intermediate temperature setting glued membranes, wherein 1 layer thickness is 0.1mm.
As shown in Figure 2, be the pre-packaged micro-strip array antenna of the utility model embedded composite material intelligent skin antenna structure.Encapsulation lid 7 in the described pre-packaged micro-strip array antenna 3 glueds joint by bonding layer 8 and micro-strip array antenna 9.The shape of bonding layer 8 is consistent with the side shape that micro-strip array antenna 9 glueds joint with encapsulation lid 7.Bonding layer 8 and encapsulation lid 7 offer a slotted eye at feed end, avoid bonding layer to cover encapsulation lid micro-strip array antenna 9 extruding S terminals in the feeder line of micro-strip array antenna 9 and the course of processing.
Described micro-strip array antenna 9 is that resonance frequency is 4 * 8 the micro-strip array antenna of 9.6GHz.
The material selection LWF-2 intermediate temperature setting glued membrane of described bonding layer 8, its material thickness is 0.1mm.
Referring to Fig. 3, Fig. 4, it is the encapsulation lid of the utility model embedded composite material intelligent skin antenna structure, described encapsulation lid 7 is shaped as the rectangular structure of band groove, its length and width size and micro-strip array antenna length and width consistent size, encapsulation lid 7 offers a slotted eye at feed end, covers encapsulation lid micro-strip array antenna 9 extruding S terminals in the feeder line of micro-strip array antenna 9 and the course of processing to avoid bonding layer.
The processing step of embedded composite material intelligent skin antenna structure is:
At first, embedded composite material intelligent skin antenna structure is laid in Clean room in advance, one deck bonding layer 6 is respectively pasted in the upside of the downside of its top panel 1 and lower panel 5 and the top and bottom of pre-packaged micro-strip array antenna 3, and bonding layer is pasted the back that finishes dries with blower fan.Secondly, utilize extraordinary adhesive tape and mould that sub-assembly is fixed, send in the autoclave after sealing vacuumizes, at HTHP solidified forming next time.
Embodiment two
Another kind of execution mode as the utility model embedded composite material intelligent skin antenna structure, as shown in Figure 1, the material of its top panel 1, lower panel 5 can be selected intermediate temperature setting low dielectric-loss glass cloth polymer matrix composites (SW glass cloth/epoxy) for use, and thickness is 0.5mm;
Material for core body cover plate 2, core body 4 can be selected the glass cloth honeycomb for use, and the thickness of core body cover plate 2 is that the thickness of 9mm, core body is 23mm.
Embedded composite material intelligent skin antenna structure is laid in Clean room in advance, and one deck bonding layer 6 is respectively pasted in the top and bottom of the upside of the downside of plate 1, lower panel 5 and pre-packaged micro-strip array antenna 3 in the above, and bonding layer is pasted the back that finishes dries with blower fan.Secondly, utilize extraordinary adhesive tape and mould that sub-assembly is fixed, send in the autoclave after sealing vacuumizes, at HTHP solidified forming next time.
Embodiment three
In the present embodiment, bonding layer 6, bonding layer 8 are to select J47C intermediate temperature setting glued membrane for use, and 5 layers, thickness is 0.5mm.
Core body cover plate 2 and core body 4 are to select the Nomex honeycomb for use, and the thickness of core body cover plate 2 is 15mm, and the thickness of core body 4 is 25mm.
The processing step of embedded composite material intelligent skin antenna structure is:
At first, embedded composite material intelligent skin antenna structure is laid in Clean room in advance, after the dedusting in the above the top and bottom of the upside of the downside of plate 1, lower panel 5 and pre-packaged micro-strip array antenna 3 respectively paste one deck bonding layer 6, bonding layer is pasted the back that finishes dries with blower fan.Utilize extraordinary adhesive tape and mould that sub-assembly is fixed, sealing is sent in the autoclave after vacuumizing, at HTHP solidified forming next time.
Claims (6)
1. novel embedded composite material intelligent skin antenna structure, comprise top panel (1), core body cover plate (2), pre-packaged micro-strip array antenna (3), core body (4), lower panel (5) and bonding layer (6), it is characterized in that: described pre-packaged micro-strip array antenna (3) is combined into overall structure by encapsulation lid (7) and micro-strip array antenna (9) by bonding layer (8) splicing.
2. embedded composite material intelligent skin antenna structure according to claim 1, it is characterized in that: the shape of described bonding layer (8) is consistent with the side shape that micro-strip array antenna (9) glueds joint with encapsulation lid (7), bonding layer (8) and encapsulation lid (7) are provided with a slotted eye at feed end, avoid bonding layer (8) to cover the feeder line of micro-strip array antenna (9).
3. embedded composite material intelligent skin antenna structure according to claim 1, it is characterized in that: described encapsulation lid (7) is the cuboid of band groove, be provided with a slotted eye at feed end, avoid encapsulating in the course of processing S terminal of lid (7) extruding micro-strip array antenna (9); The length and width size and micro-strip array antenna (9) the length and width consistent size of encapsulation lid (7), the wall thickness and the top thickness of encapsulation lid (7) they are 1～5mm; The height of encapsulation lid (7) is 2～15mm.
4. embedded composite material intelligent skin antenna structure according to claim 1, it is characterized in that: described core body cover plate (2), core body (4) are higher than 70% light composite material for high saturating ripple rate, material is any one of foam or cellular-core, desirable 2～the 15mm of thickness of core body cover plate (2), the desirable 10～25mm of thickness of core body (4).
5. embedded composite material intelligent skin antenna structure according to claim 1, it is characterized in that: the material of described top panel (1) and lower panel (5) is that E glass fibre, S glass fibre, D glass fibre and quartz glass fibre etc. strengthen any one of polymer matrix composites, the desirable 0.4～0.7mm of the thickness of panel.
6. embedded composite material intelligent skin antenna structure according to claim 1 is characterized in that: described bonding layer (6) is selected the intermediate temperature setting glued membrane for use, and every layer of film thickness is 0.1mm, can select 1～5 layer for use.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202221383U CN201699124U (en) | 2010-06-10 | 2010-06-10 | Novel embedded composite intelligent skin antenna structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202221383U CN201699124U (en) | 2010-06-10 | 2010-06-10 | Novel embedded composite intelligent skin antenna structure |
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| CN201699124U true CN201699124U (en) | 2011-01-05 |
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| CN2010202221383U Expired - Fee Related CN201699124U (en) | 2010-06-10 | 2010-06-10 | Novel embedded composite intelligent skin antenna structure |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101867084A (en) * | 2010-06-10 | 2010-10-20 | 西北工业大学 | Novel embedded composite material intelligent skin antenna structure |
| CN102569984A (en) * | 2012-01-13 | 2012-07-11 | 北京航空航天大学 | Compound forming method for large-curvature double-curve-degree high-accuracy antenna panel |
| CN102810762A (en) * | 2012-07-31 | 2012-12-05 | 深圳光启创新技术有限公司 | Core metamaterial and preparation method thereof and preparation method of core metamaterial antenna housing |
| CN104794284A (en) * | 2015-04-22 | 2015-07-22 | 西安电子科技大学 | Intelligent skin antenna electric compensation method based on embedded fiber bragg grating |
| 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 |
-
2010
- 2010-06-10 CN CN2010202221383U patent/CN201699124U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101867084A (en) * | 2010-06-10 | 2010-10-20 | 西北工业大学 | Novel embedded composite material intelligent skin antenna structure |
| CN102569984A (en) * | 2012-01-13 | 2012-07-11 | 北京航空航天大学 | Compound forming method for large-curvature double-curve-degree high-accuracy antenna panel |
| CN102810762A (en) * | 2012-07-31 | 2012-12-05 | 深圳光启创新技术有限公司 | Core metamaterial and preparation method thereof and preparation method of core metamaterial antenna housing |
| CN102810762B (en) * | 2012-07-31 | 2015-05-27 | 深圳光启创新技术有限公司 | Core metamaterial and preparation method thereof and preparation method of core metamaterial antenna housing |
| CN104794284A (en) * | 2015-04-22 | 2015-07-22 | 西安电子科技大学 | Intelligent skin antenna electric compensation method based on embedded fiber bragg grating |
| CN104794284B (en) * | 2015-04-22 | 2017-08-22 | 西安电子科技大学 | A kind of smart skins antenna electric compensation method based on embedded fiber grating |
| 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 |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110105 Termination date: 20130610 |