CN208157623U - A kind of fusion type blunt form forward antenna cover structure - Google Patents
A kind of fusion type blunt form forward antenna cover structure Download PDFInfo
- Publication number
- CN208157623U CN208157623U CN201820369681.2U CN201820369681U CN208157623U CN 208157623 U CN208157623 U CN 208157623U CN 201820369681 U CN201820369681 U CN 201820369681U CN 208157623 U CN208157623 U CN 208157623U
- Authority
- CN
- China
- Prior art keywords
- antenna
- antenna cover
- fusion type
- forward antenna
- bulge
- 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.)
- Active
Links
Landscapes
- Details Of Aerials (AREA)
Abstract
The utility model proposes a kind of fusion type blunt form forward antenna cover structures to solve the problems, such as that the multi-task antenna without antenna and antenna house installation space, is provide with meter by course altogether in nose shell for reducing airborne radome quantity.The utility model is installed and is reduced for multitask antenna antenna wave transparent area ranges of incidence angles and provides a kind of fusion type blunt form forward antenna cover structure.Bulge is designed outside forward antenna cover, then the shape intersection of former streamlined forward antenna cover and the shape bulge of forward antenna cover is subjected to round-corner transition, and filleted corner takes R3.Solution original machine head-shield profile antenna installation space is small, and electrical property is difficult to meet the technical problem of technical requirements.Antenna house quantity is reduced, the confined space can be saved, convenient for multiplexing Mux arrangement installation, cable kilometer is reduced, significantly improves structure efficiency, promote airplane complete machine performance.
Description
Technical field
The utility model is about the airborne radome development and design technology in technical field of aircraft structure design.Airborne day
Irdome is used for protective cover internal antenna from the destruction of environment and flight load, while providing Electromgnetically-transparent function for radar antenna
Energy.Airborne radome is both that the structure member (meeting intensity and toughness requirement) of aircraft and the functional component of aircraft (meet antenna
Antenna electric performance requirement).Airborne radome is to reduce aerodynamic drag, is typically designed to streamlined structure.
Background technique
Airborne radome needs to design different shapes and different knots because of antenna performance and antenna pattern difference, different antennas
The antenna house of structure.Streamlined radome has biggish ranges of incidence angles relative to antenna electromagnetic wave difference penetrating region, larger
Ranges of incidence angles has biggish adverse effect to the performance of antenna.But since aircraft configuration space is limited, antenna house quantity increases
Task antenna space layout is not only influenced, can also will increase flight resistance, and then influence aircraft overall performance.
Utility model content
Purpose of utility model：The utility model solves course without antenna and antenna house for reducing airborne radome quantity
The multi-task antenna is provide with meter by installation space problem altogether in nose shell.The utility model is the installation of multitask antenna
A kind of fusion type blunt form forward antenna cover structure is provided with antenna wave transparent area ranges of incidence angles is reduced.
Technical solution：In order to solve the above-mentioned technical problem, the utility model is achieved through the following technical solutions：
(1) bulge is designed outside forward antenna cover
According to nose shell upper antenna installation site, first determine that the work airspace (pitching face and azimuth plane) of antenna is formed
The enveloping space, further according to antenna, using space needed for installation, (use space determines that installation space presses according to requirement on electric performance
Safe distance needed for antenna house dismounting determines, takes it big in the two) determine the enveloping space.Work airspace needed for the enveloping space with
Intersection region using the enveloping space needed for installing is the benchmark shape of forward antenna cover shape bulge, then in benchmark shape and machine
Transiens face is set between previous day irdome, and is intersected with streamlined nose shell.Thereby determine that forward antenna cover shape bulge.
(2) the shape intersection of former streamlined forward antenna cover and the shape bulge of forward antenna cover is subjected to round-corner transition, it is interior
Fillet takes R3.
Advantageous effects：
1 on the basis of holding nose shell original aerodynamic configuration, and convection current line style forward antenna cover shape carries out part and sets again
Meter, forms a fusion type blunt form antenna house.Fusion type blunt form antenna house mainly solves original machine head-shield profile antenna
Installation space is small, and electrical property is difficult to meet the technical problem of technical requirements.
2 reduce airborne radome quantity.If not using fusion type blunt form forward antenna cover, need in the other portions of fuselage
Position is further added by an antenna house.Airborne radome is made of wave transparent functional areas, bonding pad, connector etc., and is connect with fuselage
Position setting is corresponding to reinforce area.Fusion type forward antenna cover by reduce antenna house quantity, eliminate newly-increased antenna house bonding pad,
The structural redundancies parts such as connector, fuselage stiffener assembly only increase wave transparent functional areas, therefore can significantly improve structure efficiency.
3 aircraft configuration spaces are limited, reduce antenna house quantity, can save the confined space, convenient for multiplexing Mux arrangement peace
Dress reduces cable kilometer, promotes airplane complete machine performance.
Detailed description of the invention
Fig. 1 is streamlined forward antenna cover structure schematic diagram,
Fig. 2 is a kind of fusion type blunt form forward antenna cover.
Specific embodiment
The utility model is described in further detail with specific embodiment with reference to the accompanying drawing：The non-streamline head of fusion type
Cover passes through a kind of antenna cover structure form merged with local form's bulge by streamlined nose shell.By streamlined nose shell, machine
The bulge of head-shield local form, transition circle angular region can flow item, interface frame, mating frame, connection lock, lightning diverter item composition.The non-streamline of fusion type
Type antenna house can increase antenna installation space, reduce the ranges of incidence angles that antenna electromagnetic wave threw region, improve electrical property, realize
A variety of antennas cover altogether.
Claims (2)
1. a kind of fusion type blunt form forward antenna cover structure, it is characterised in that：Bulge shape is designed outside forward antenna cover,
Existing streamlined forward antenna cover and the shape intersection of forward antenna cover shape bulge carry out round-corner transition, and filleted corner takes R3.
2. a kind of fusion type blunt form forward antenna cover structure according to claim 1, it is characterised in that：The bulge
Size determined by the work airspace of antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820369681.2U CN208157623U (en) | 2018-03-16 | 2018-03-16 | A kind of fusion type blunt form forward antenna cover structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820369681.2U CN208157623U (en) | 2018-03-16 | 2018-03-16 | A kind of fusion type blunt form forward antenna cover structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208157623U true CN208157623U (en) | 2018-11-27 |
Family
ID=64391862
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820369681.2U Active CN208157623U (en) | 2018-03-16 | 2018-03-16 | A kind of fusion type blunt form forward antenna cover structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208157623U (en) |
-
2018
- 2018-03-16 CN CN201820369681.2U patent/CN208157623U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8746611B2 (en) | Lightning protection arrangement for an electronic unit | |
| CN106654569B (en) | The conical energy selection antenna house and antenna system of a kind of monopole antenna | |
| FR2914622B1 (en) | AIRCRAFT COMPRISING STRUCTURE ENSURING STRUCTURAL AND ELECTRICAL FUNCTIONS | |
| CA2836694A1 (en) | Lightning conductor system comprising a lightning conductor strip mounted in an offset manner | |
| CN204037916U (en) | A kind of low radar scattering cross section photoelectric nacelle | |
| CN202783773U (en) | Lightning stroke-proof composite material wing box for airplane | |
| CN104931228A (en) | Double-body super-high aspect ratio aircraft wind tunnel force measurement test supporting device | |
| CN205675228U (en) | Docking structure on spar flange for a kind of aerofoil covering | |
| CN208157623U (en) | A kind of fusion type blunt form forward antenna cover structure | |
| CN102263317A (en) | Airplane vertical tail front edge parallel feed slot antenna | |
| CN105947174A (en) | Airplane | |
| CN205418067U (en) | Aircraft afterbody radome fairing | |
| CN108657414A (en) | A kind of attachment device and the connection method of unmanned plane central wing, outer wing and shoe | |
| CN209814263U (en) | High lift wing and have its aircraft | |
| CN206516757U (en) | The conical energy selection antenna house and antenna system of a kind of monopole antenna | |
| CN207165759U (en) | A kind of integrated antenna hood mounting structure | |
| CN208433525U (en) | A kind of high-performance blister towards high-speed cruising carrier satellite communication system | |
| CN204788881U (en) | Binary super large aspect ratio aircraft wind -tunnel dynamometer check strutting arrangement | |
| CN204433029U (en) | A kind of structure solar heat protection configuration | |
| Durlu et al. | Monostatic RCS analysis for armed and unarmed UAV | |
| US9362626B2 (en) | Equipment for the reduction of the radar marking for aircrafts | |
| CN219077516U (en) | Externally hung unmanned aerial vehicle target characteristic refitting device and unmanned aerial vehicle | |
| CN219277821U (en) | Externally hung unmanned aerial vehicle target characteristic refitting device and unmanned aerial vehicle | |
| CN221262691U (en) | Radio frequency antenna mounting structure of aircraft tail wing composite structure | |
| CN109720570A (en) | A kind of floating drum connection structure of large size amphibious aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 cuijiashan Town, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
|
| CP03 | Change of name, title or address |