CN206639924U - A kind of aircraft antenna radome fairing - Google Patents
A kind of aircraft antenna radome fairing Download PDFInfo
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- CN206639924U CN206639924U CN201720242652.5U CN201720242652U CN206639924U CN 206639924 U CN206639924 U CN 206639924U CN 201720242652 U CN201720242652 U CN 201720242652U CN 206639924 U CN206639924 U CN 206639924U
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- aircraft
- bearing bracket
- antenna
- radome fairing
- main body
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Abstract
The utility model provides a kind of aircraft antenna radome fairing, belongs to space flight and aviation technical field of auxiliary equipment.The aircraft antenna radome fairing, including body, the end cap for being arranged on body both ends.Fly to direction according to aircraft, be arranged on body front end for drive end bearing bracket, be arranged on aircraft rear for rear end cap.Body includes gondola main body and the wave transparent cover being detachably connected with gondola main body, and the enveloping space for accommodating antenna is provided with body；The pinboard of fixed antenna is provided with body, pinboard is detachably connected with gondola main body.For the body to wait straight cylinder, drive end bearing bracket and rear end cap are oval revolving body, and the short axle length of drive end bearing bracket and rear end cap is consistent with the diameter of body.The aircraft antenna radome fairing that the application provides, simple in construction, profile entirety rectification design, aerodynamic effects caused by reducing plug-in radome fairing, resistance coefficient is reduced, and can be according to the different pinboard of the type configuration of antenna, applicability is wide, the use suitable for aircraft assembling antenna.
Description
Technical field
It the utility model is related to space flight and aviation technical field of auxiliary equipment, more particularly to a kind of aircraft antenna radome fairing.
Background technology
Aircraft antenna, it is exactly the device for being used for radiating and receiving radio wave on aircraft.Its principle is exactly to launch day
The alternating electromagnetic that line sends oscillator (emitter) can be changed into electromagnetic wave (radio wave) energy propagated to certain space.Connect
Receive antenna and obtain electromagnetic wave energy from surrounding space, and transmit it to receiving device.In general, antenna size is to wavelength
Ratio is bigger, and the energy of acquisition is also bigger.Antenna has reciprocity, parameter constant when work is launched or received.To antenna parameter
It is required that it is decided by the purposes of radio-electronic equipment.
With the development of aeronautical technology, meet that the antenna of a variety of demands is more and more on aircraft.A part of antenna needs to pacify
Mounted in airframe surface, these antenna protrudes the outer surface of aircraft, certain influence certainly will be brought on aircraft surfaces aerodynamic characteristic,
Increase aircraft flight resistance.Generally install antenna dome additional outside these antenna.
Antenna dome, is mainly used in aircraft and carrys additionally radar etc. needing to be placed on the electronic equipment of aircraft exterior, by special
There is facility -- bird hanger, it is installed on external fuselage.Existing antenna dome easily causes air-flow separation, resistance
Coefficient is big, narrow using antenna range, and the outfit for being unsuitable for aircraft uses.
The content of the invention
Problem to be solved in the utility model be existing antenna dome easily cause air-flow separation, resistance coefficient it is big,
Narrow using antenna range, the outfit for being unsuitable for aircraft uses..
In order to solve the above technical problems, the technical solution adopted in the utility model is：A kind of aircraft antenna radome fairing is provided.
The aircraft antenna radome fairing, including body, the end cap for being arranged on body both ends.Direction is flown to according to aircraft, is arranged on body
Front end for drive end bearing bracket, be arranged on aircraft rear for rear end cap.Body includes gondola main body and detachably connected with gondola main body
The wave transparent cover connect, body is interior to be provided with the enveloping space for accommodating antenna；The pinboard of fixed antenna is provided with body, pinboard is with hanging
Cabin main body is detachably connected.The body is to wait straight cylinder, and drive end bearing bracket and rear end cap are oval revolving body, drive end bearing bracket and rear end
The short axle length of lid is consistent with the diameter of body.
Preferably, the boss of fixed transfer plate is provided with the gondola main body, the peace of installation pinboard is provided with boss
Fill hole.
Further, the drive end bearing bracket with main body, rear end cap is with being equipped with the flange ring being engaged in main body.
Further, the drive end bearing bracket is provided with the radiating tube for radiating, radiating tube from the appearance of drive end bearing bracket forward
Cover internal extends.
Preferably, the drive end bearing bracket is provided with the cover lid for covering radiating tube.
Preferably, the major axis of the drive end bearing bracket and rear end cap and the length ratio of short axle are 1.2~1.8.
Further, the drive end bearing bracket, rear end cap, the material of wave transparent cover are that glass fibre, the material of main body are duralumin
Alloy.
The utility model has the advantages and positive effects of：The aircraft antenna radome fairing that the application provides, it is simple in construction,
Profile entirety rectification design, reduce plug-in radome fairing caused by aerodynamic effects, reduce resistance coefficient, and can be according to antenna
The different pinboard of type configuration, applicability is wide, the use suitable for aircraft assembling antenna.
The aircraft antenna radome fairing that the application provides, body are made up of gondola main body and wave transparent cover, have enough envelopes
Space, meet the space requirement of different type antenna installation.Some boss are provided with gondola main body, some installations are provided with boss
Hole, can be wide according to the type and installation site of the different choice pinboard of antenna type, applicability.
Brief description of the drawings
Fig. 1 is the schematic front view of the application (omitting wave transparent cover).
Fig. 2 is Fig. 1 A-A schematic diagrames.
Fig. 3 is Fig. 1 B-B schematic diagrames.
Fig. 4 is the schematic cross-section of gondola main body in the application.
Fig. 5 is the internal structure schematic diagram of the application.
In figure：1- gondola main bodys, 101- boss, 102- mounting holes, 103- fixing holes, 2- flange rings, 201- flange holes, 3-
Drive end bearing bracket, 301- radiating tubes, 4- rear end caps, 5- wave transparent covers, 6- cover lids, 7- pinboards.
Embodiment
In order to be better understood from the utility model, enter traveling one to the utility model with reference to specific embodiments and the drawings
The description of step.
As Figure 1-Figure 5, the application provides a kind of aircraft antenna radome fairing, including body, end cap, flange ring 2 and turns
Fishplate bar 7.
Body for etc. right cylindrical, including gondola main body 1 and wave transparent cover 5, the two, which is engaged, forms first-class straight cylinder.Body
It is interior to be provided with the enveloping space for accommodating antenna, meet the space requirement of different type antenna installation.Gondola main body 1 and wave transparent cover 5 can
Dismantling connection, as a kind of embodiment, as shown in figure and Fig. 2, gondola main body 1 is connected region with wave transparent cover 5 provided with fixation
Hole, it is bolted, opening wave transparent cover 5 easily can be installed or be repaired to antenna.
The inwall of gondola main body 1 is provided with some boss 101, is provided with some mounting holes 102 on boss, is opened on pinboard 7
There are some through holes being engaged with mounting hole, can be full according to the type and installation site of the different choice pinboard 7 of antenna type
The installation requirements of sufficient different type antenna.
Fly to direction according to aircraft, be arranged on body front end for drive end bearing bracket 3, be arranged on aircraft rear for rear end cap 4.
Drive end bearing bracket 3 and rear end cap 4 are short axle length, the front end consistent with the diameter of body of oval revolving body, drive end bearing bracket 3 and rear end cap 4
The length ratio of the major axis and short axle of lid 3 and rear end cap 4 is 1.2~1.8, the design of this overall rectification, can reduce resistance system
Number, reduces aerodynamic effects caused by plug-in antenna.End cap is detachably connected with main body, as a kind of embodiment, drive end bearing bracket 3 with
In gondola main body 1, rear end cap 4 be equipped with the flange ring 2 being engaged with upper gondola main body 1, be provided with flange hole 201 on flange ring 2,
It is bolted.
Drive end bearing bracket 3 is provided with the radiating tube 301 for radiating, and radiating tube 301 is from the outer surface of drive end bearing bracket 3 end cap 3 forward
Inside extension.Radiating tube 301 is located at the central area of drive end bearing bracket 3, when assembling antenna, radiating tube 301 and antenna or electronic equipment
Radiating tube be connected.Drive end bearing bracket 3 is provided with the cover lid 6 for covering radiating tube 301, and the aircraft antenna radome fairing that the application provides exists
When not in use or aircraft is not at state of flight, cover lid 6 covers radiating tube, prevents dust, debris etc. from entering antenna dome.
Preferably, drive end bearing bracket 3, rear end cap 4, the material of wave transparent cover 5 are glass fiber compound material, gondola main body 1
Material with flange ring 2 is duralumin, hard alumin ium alloy.Other hardwares are digital control processing, ensure the installation with bird hanger
Precision.
Embodiment of the present utility model is described in detail above, but the content is only of the present utility model preferable
Embodiment, it is impossible to be considered as being used to limit practical range of the present utility model.All impartial changes made according to the scope of the utility model
Change and improvement etc., all should still be belonged within this patent covering scope.
Claims (7)
- A kind of 1. aircraft antenna radome fairing, it is characterised in that：Including body, it is arranged on the end cap at body both ends；Fly to direction according to aircraft, be arranged on body front end for drive end bearing bracket, be arranged on aircraft rear for rear end cap；Body includes gondola main body and the wave transparent cover being detachably connected with gondola main body, and the envelope sky for accommodating antenna is provided with body Between；The pinboard of fixed antenna is provided with body, pinboard is detachably connected with gondola main body；For the body to wait straight cylinder, drive end bearing bracket and rear end cap be oval revolving body, the short axle of drive end bearing bracket and rear end cap length and The diameter of body is consistent.
- 2. aircraft antenna radome fairing according to claim 1, it is characterised in that：Fixed transfer is provided with the gondola main body The boss of plate, the mounting hole of installation pinboard is provided with boss.
- 3. aircraft antenna radome fairing according to claim 1 or 2, it is characterised in that：In the drive end bearing bracket and main body, rear end Lid is with being equipped with the flange ring being engaged in main body.
- 4. aircraft antenna radome fairing according to claim 1 or 2, it is characterised in that：The drive end bearing bracket, which is provided with, to be used to dissipate The radiating tube of heat, from the outer surface of drive end bearing bracket, cover internal extends radiating tube forward.
- 5. aircraft antenna radome fairing according to claim 4, it is characterised in that：The drive end bearing bracket, which is provided with, covers radiating tube Cover lid.
- 6. aircraft antenna radome fairing according to claim 1, it is characterised in that：The major axis of the drive end bearing bracket and rear end cap with The length ratio of short axle is 1.2~1.8.
- 7. according to any described aircraft antenna radome fairing of claim 1,2,5,6, it is characterised in that：The drive end bearing bracket, rear end Lid, the material of wave transparent cover are that glass fibre, the material of main body are duralumin, hard alumin ium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720242652.5U CN206639924U (en) | 2017-03-14 | 2017-03-14 | A kind of aircraft antenna radome fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720242652.5U CN206639924U (en) | 2017-03-14 | 2017-03-14 | A kind of aircraft antenna radome fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206639924U true CN206639924U (en) | 2017-11-14 |
Family
ID=60250095
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720242652.5U Active CN206639924U (en) | 2017-03-14 | 2017-03-14 | A kind of aircraft antenna radome fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206639924U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108417981A (en) * | 2018-04-25 | 2018-08-17 | 西安飞机工业（集团）有限责任公司 | A kind of segmented airborne radome |
| CN108791814A (en) * | 2018-06-19 | 2018-11-13 | 吉林化工学院 | A kind of aircraft cowling that shock resistance is good |
| RU199992U1 (en) * | 2020-06-26 | 2020-10-01 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Wedge-shaped radio-transparent front fairing of the supersonic aircraft body |
| RU2733916C1 (en) * | 2020-03-02 | 2020-10-08 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Antenna fairing for high-speed missiles |
| RU2735381C1 (en) * | 2020-04-24 | 2020-10-30 | Акционерное общество «Обнинское научно-производственное предприятие «Технология» им. А.Г.Ромашина» | Antenna fairing |
| CN111965717A (en) * | 2020-08-12 | 2020-11-20 | 彩虹无人机科技有限公司 | Fixed wing unmanned aerial vehicle time domain aviation electromagnetism investigation system |
| CN113348132A (en) * | 2019-01-29 | 2021-09-03 | 汉莎技术有限公司 | Attachment housing for fastening to an aircraft |
-
2017
- 2017-03-14 CN CN201720242652.5U patent/CN206639924U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108417981A (en) * | 2018-04-25 | 2018-08-17 | 西安飞机工业（集团）有限责任公司 | A kind of segmented airborne radome |
| CN108791814A (en) * | 2018-06-19 | 2018-11-13 | 吉林化工学院 | A kind of aircraft cowling that shock resistance is good |
| CN113348132A (en) * | 2019-01-29 | 2021-09-03 | 汉莎技术有限公司 | Attachment housing for fastening to an aircraft |
| CN113348132B (en) * | 2019-01-29 | 2024-05-24 | 汉莎技术有限公司 | Attachment housing for fastening to an aircraft |
| RU2733916C1 (en) * | 2020-03-02 | 2020-10-08 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Antenna fairing for high-speed missiles |
| RU2735381C1 (en) * | 2020-04-24 | 2020-10-30 | Акционерное общество «Обнинское научно-производственное предприятие «Технология» им. А.Г.Ромашина» | Antenna fairing |
| RU199992U1 (en) * | 2020-06-26 | 2020-10-01 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Wedge-shaped radio-transparent front fairing of the supersonic aircraft body |
| CN111965717A (en) * | 2020-08-12 | 2020-11-20 | 彩虹无人机科技有限公司 | Fixed wing unmanned aerial vehicle time domain aviation electromagnetism investigation system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Airplane antenna cowling Effective date of registration: 20191125 Granted publication date: 20171114 Pledgee: Shaanxi SME financing Company limited by guarantee Pledgor: Shan'xi Aiweisen Aviation Engineering Co.,Ltd. Registration number: Y2019980000700 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20201211 Granted publication date: 20171114 Pledgee: Shaanxi SME financing Company limited by guarantee Pledgor: SHAANXI AVIATION ENGINEERING Co.,Ltd. Registration number: Y2019980000700 |