CN108417981A - A kind of segmented airborne radome - Google Patents
A kind of segmented airborne radome Download PDFInfo
- Publication number
- CN108417981A CN108417981A CN201810382192.5A CN201810382192A CN108417981A CN 108417981 A CN108417981 A CN 108417981A CN 201810382192 A CN201810382192 A CN 201810382192A CN 108417981 A CN108417981 A CN 108417981A
- Authority
- CN
- China
- Prior art keywords
- fairing
- architrave
- bulkhead
- radome
- flange
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
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- Details Of Aerials (AREA)
Abstract
The present invention relates to a kind of segmented airborne radomes, including front fairing, Antenna Operation cover, rear radome fairing, preceding bulkhead, rear bulkhead.Preceding bulkhead, rear bulkhead are front fairing, Antenna Operation cover, rear radome fairing provide rigid support, it ensure that the mechanical property requirements such as airborne radome rigidity and load, front fairing flange and rear radome fairing flange, realization is directly docked with airframe structure, and the introducing other structures simple in structure that in turn avoid dock with fuselage and increase construction weight；Radome fairing uses the combination of streamlined multiple material rectification covering and metal reinforced material afterwards, both good aerodynamic configuration had been ensure that, in turn ensure that rear radome fairing has enough strength and stiffness, preceding bulkhead, rear bulkhead are in such a way that mental section and multiple material web are combined, existing enough bearing capacitys, and can effectively reduce construction weight.
Description
Technical field
The invention belongs to field of airplane structure, and in particular to a kind of segmented airborne radome.
Background technology
Antenna house is the structure for protecting airborne antenna system from external environment influence.It has good in electric property
Electromagnetic wave through characteristic, the effect of external adverse circumstances is amenable in mechanical performance.It is as follows using antenna house purpose：
1) it protects antenna system from the influence of the external adverse circumstances such as wind and rain, ice and snow, sand and dust and solar radiation, makes antenna
System stable and reliable working performance, while mitigating the abrasion, corrosion and aging of antenna system, prolong the service life.
2) wind load and wind moment are eliminated, the driving power of rotary antenna is reduced, mitigates mechanical structure weight, is reduced used
Amount improves intrinsic frequency.
3) related equipment can work in antenna house, not be affected by the external environment, and improve the service efficiency of equipment.
4) for the aircraft of high-speed flight, antenna house can solve high temperature, airload and other loads to day
The problem that tape comes.
Antenna house multiselect conventional housings structure, i.e., with streamlined contour single shell structure, antenna house load by
Shell is supported.Antenna over body case be usually again material A type sandwiches, it by the symmetrical high intensity density of two equal thickness epidermis
With the fuse composition of a low-density, advantage is that specific strength and specific stiffness are big.
Conventional housings structural antenna cover (shown in attached drawing 1) is suitable for protection small size airborne antenna system, but can not use
In protection oversize airborne antenna system, (oversize airborne antenna system includes following several situations：Antenna system itself
Size super large, antenna system working space super large, more set antenna system be located at the same working region of aircraft cause it is integrated airborne
Antenna system size and working space super large), this is because conventional housings structural antenna cover increases with size, it is necessary to increase day
Irdome thickness could meet the design requirement of the mechanical properties such as rigidity and load, but do so this and can not only increase structure weight
Amount, will also substantially reduce the electromagnetic wave through characteristic of antenna house.In brief, conventional housings structural antenna cover increases with size
Greatly, mechanical performance cannot be taken into account with electric property, be not used to protection oversize airborne antenna system.
Invention content
To solve the above-mentioned problems, The present invention gives a kind of segmented airborne radome, conventional housings structure is solved
Antenna house increases with size, and mechanical performance cannot be taken into account with electric property to be led to not for protecting oversize antenna system
The problem of.
A kind of segmented airborne radome, including front fairing, Antenna Operation cover, rear radome fairing, preceding bulkhead, rear bulkhead,
Front fairing is that a quarter spherical shell band flange answers material structure, and front fairing is connected by flange with airframe structure；Antenna
Working cover is that semi- cylindrical shell answers material structure；Radome fairing is made of rectification covering and stiffening profile afterwards, and rectification covering turns over for band
The streamlined multiple material shell structure on side, is connected by flange with airframe structure；Stiffening profile is metal material, logical with rectification covering
It crosses fastener to be connected, but is not connected with other structures；Preceding bulkhead, rear bulkhead are by upper architrave, lower architrave, cornual plate, column, web group
At cornual plate, the upper architrave of column connection, web and lower architrave；Upper architrave is for connecting front fairing, Antenna Operation cover, rear rectification
Cover, lower architrave is for connecting airframe structure；Front fairing, Antenna Operation cover in rear radome fairing load transmission to upper architrave, then lead to
Cross cornual plate, column, web to be transmitted in lower architrave, be transmitted on airframe structure finally by lower architrave, upper architrave, lower architrave,
Column is mental section, and cornual plate is sheet metal, and web is multiple material structure.
The advantage of the invention is that：
A kind of segmented airborne radome is front fairing, Antenna Operation cover, rear radome fairing by preceding bulkhead, rear bulkhead
Rigid support is provided, ensure that airborne radome rigidity and load on the basis of not reducing airborne radome electromagnetic wave through characteristic
Equal mechanical property requirements, to solve conventional housings structural antenna cover as size increases, mechanical performance and electric property are not
The problem of leading to not load oversize antenna system can be taken into account；It is real by making front fairing and rear radome fairing carry flange
It is now directly docked with airframe structure, the simple advantage of existing structure, in turn avoids introducing other structures and dock and increase with fuselage
Construction weight；Radome fairing both ensure that using the combination of streamlined multiple material rectification covering and metal material stiffening profile afterwards
Good aerodynamic configuration, and can guarantee rear radome fairing with enough strength and stiffness, at the same stiffening profile only with rectification
Covering, which is connected, to be also convenient for rear radome fairing and is disassembled and installed；Preceding bulkhead, rear bulkhead are using mental section and multiple material web phase group
Conjunction mode may be either that front fairing, Antenna Operation cover, rear radome fairing provide enough rigid supports, and use multiple material web knot
Structure reduces weight.
Description of the drawings
Fig. 1 airborne radome conventional housings structural schematic diagrams.
The shaft side figure of Fig. 2 segmented airborne radomes.
Fig. 3 front fairing shaft side figures.
Fig. 4 Antenna Operation cover shaft side figures.
Radome fairing shaft side figure after Fig. 5.
Bulkhead rearview before Fig. 6.
Bulkhead front view after Fig. 7.
Explanation is numbered in figure：1, airborne radome conventional housings structure；2, front fairing；3, Antenna Operation cover；4, rear whole
Stream cover；5, preceding bulkhead；6, rear bulkhead；7, front fairing flange；8, stiffening profile；9, rectification covering；10, rear radome fairing flange；
11, upper architrave；12, lower architrave；13, cornual plate；14, column；15, web.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term "front", "rear", "upper", "lower", " axis side ", " side view ",
The orientation or positional relationship of the instructions such as " forward sight ", " vertical view ", " backsight " is to be based on the orientation or positional relationship shown in the drawings, and is only
For convenience of description of the present invention and simplification of the description, specific side must be had by not indicating or implying the indicated device or element
Position, with specific azimuth configuration and operation, therefore should not be understood as limiting the scope of the invention.
It is described in detail below with specific embodiment.
It is shown in Figure 2, a kind of segmented airborne radome, by front fairing 2, Antenna Operation cover 3, rear radome fairing 4, preceding
Bulkhead 5, rear bulkhead 6 form.
Referring to Fig. 3, front fairing 2 is that a quarter spherical shell band flange answers material ply angles, with fiberglass according to 0,
45 symmetrical shops are laid with 12 layers altogether per layer thickness 0.25mm；Front fairing carries flange, by front fairing flange 7 realize with
Airframe structure is connected directly.
Referring to Fig. 4, Antenna Operation cover 3 is that semi- cylindrical shell answers material A type sandwiches, outer layer fiberglass according to (0 °/
45 °/90 °) totally 3 layers of progress paving, internal layer carries out paving for totally 3 layers with fiberglass according to (90 °/45 °/0 °), and often layer thickness is
0.25mm, centre are aramid fiber paper honeycomb core, thickness 6mm.
Referring to Fig. 5, rear radome fairing 4 is made of rectification covering 9 and stiffening profile 8.Rectification covering 9 is streamlined multiple material shell
Ply angles per layer thickness 0.25mm, are laid with 12 layers, rectification covering 9 is included to be turned over altogether with fiberglass according to 0,45 symmetrical shops
Side, rectification covering are connected by rear radome fairing flange 10 with airframe structure；Stiffening profile 8 is metal material, by T profile and multiple
L-type material is composed, and is connected by fastener with rectification covering 9, but be not connected with other structures.
Referring to Fig. 6, Fig. 7, preceding bulkhead 5, the effect of rear bulkhead 6 are carried for front fairing 2, Antenna Operation cover 3, rear radome fairing 4
It is acted on for rigid support.Preceding bulkhead 5, rear bulkhead 6 are made of upper architrave 11, lower architrave 12, cornual plate 13, column 14, web 15.On
Architrave 11 is for connecting front fairing 2, Antenna Operation cover 3, rear radome fairing 4, and lower architrave 12 is for connecting airframe structure, cornual plate
13, the upper architrave 11 of the connection of column 14, web 15 and lower architrave 12.Front fairing 2, Antenna Operation cover 3,4 load of rear radome fairing pass
It is delivered in architrave 11, then is transmitted in lower architrave 12 by cornual plate 13, column 14, web 15, passed finally by lower architrave 12
It is delivered on airframe structure.Upper architrave 11,12 section of lower architrave are metal T profile, and 14 section of column is metal L-type material, cornual plate 13
For triangles of metal plank；Web 15 is multiple material ply angles, with fiberglass according to 0,45 symmetrical shops, per layer thickness
0.25mm is laid with 6 layers altogether.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：It is still
Can be with technical scheme described in the above embodiments is modified, or which part technical characteristic is equally replaced
It changes；And these modifications or replacements, the essence for various embodiments of the present invention technical solution that it does not separate the essence of the corresponding technical solution
God and range.
Claims (1)
1. a kind of segmented airborne radome, including front fairing, Antenna Operation cover, rear radome fairing, preceding bulkhead, rear bulkhead,
It is characterized in that front fairing is that a quarter spherical shell band flange answers material structure, front fairing passes through flange and airframe structure phase
Even；Antenna Operation cover is that semi- cylindrical shell answers material structure；Radome fairing is made of rectification covering and stiffening profile afterwards, rectification covering
For the streamlined multiple material shell structure with flange, it is connected with airframe structure by flange；Stiffening profile is metal material, with rectification
Covering is connected by fastener, but is not connected with other structures；Preceding bulkhead, rear bulkhead by upper architrave, lower architrave, cornual plate, column,
Web forms, cornual plate, the upper architrave of column connection, web and lower architrave；Upper architrave for connect front fairing, Antenna Operation cover,
Radome fairing afterwards, lower architrave is for connecting airframe structure；Front fairing, Antenna Operation cover, rear radome fairing load transmission to upper architrave
On, then be transmitted in lower architrave by cornual plate, column, web, it is transmitted on airframe structure finally by lower architrave, upper architrave,
Lower architrave, column are mental section, and cornual plate is sheet metal, and web is multiple material structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810382192.5A CN108417981A (en) | 2018-04-25 | 2018-04-25 | A kind of segmented airborne radome |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810382192.5A CN108417981A (en) | 2018-04-25 | 2018-04-25 | A kind of segmented airborne radome |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108417981A true CN108417981A (en) | 2018-08-17 |
Family
ID=63136674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810382192.5A Pending CN108417981A (en) | 2018-04-25 | 2018-04-25 | A kind of segmented airborne radome |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108417981A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671007A (en) * | 2022-04-01 | 2022-06-28 | 中国科学院空天信息创新研究院 | Long-baseline small-deformation array radome truss for three-dimensional imaging radar |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130214093A1 (en) * | 2012-02-21 | 2013-08-22 | Raytheon Company | Releasable radome cover |
| CN205076029U (en) * | 2015-08-11 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | Appearance radome fairing is taken photograph to boat |
| CN206639924U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft antenna radome fairing |
| CN107799895A (en) * | 2017-09-12 | 2018-03-13 | 陕西飞机工业（集团）有限公司 | A kind of balance beam profile and direction-finder antenna cover |
-
2018
- 2018-04-25 CN CN201810382192.5A patent/CN108417981A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130214093A1 (en) * | 2012-02-21 | 2013-08-22 | Raytheon Company | Releasable radome cover |
| CN205076029U (en) * | 2015-08-11 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | Appearance radome fairing is taken photograph to boat |
| CN206639924U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft antenna radome fairing |
| CN107799895A (en) * | 2017-09-12 | 2018-03-13 | 陕西飞机工业（集团）有限公司 | A kind of balance beam profile and direction-finder antenna cover |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114671007A (en) * | 2022-04-01 | 2022-06-28 | 中国科学院空天信息创新研究院 | Long-baseline small-deformation array radome truss for three-dimensional imaging radar |
| CN114671007B (en) * | 2022-04-01 | 2022-11-22 | 中国科学院空天信息创新研究院 | Long-baseline small-deformation array radome truss for three-dimensional imaging radar |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180817 |
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| WD01 | Invention patent application deemed withdrawn after publication |