CN203428019U - Aircraft antenna fairing - Google Patents
Aircraft antenna fairing Download PDFInfo
- Publication number
- CN203428019U CN203428019U CN201320377102.6U CN201320377102U CN203428019U CN 203428019 U CN203428019 U CN 203428019U CN 201320377102 U CN201320377102 U CN 201320377102U CN 203428019 U CN203428019 U CN 203428019U
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- fairing
- section
- antenna
- aircraft
- transition
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Abstract
The utility model relates to an aircraft antenna fairing. The aircraft antenna fairing comprises a fuselage appearance section (1), a fairing transition section (2), a fairing equal-diameter section (3), a fairing spindle body section (4) and a fairing tail section (5), wherein the fairing equal-diameter section (3) is a curved surface formed by stretching along the axis direction of an antenna according to an airfoil profile (3'); the fairing spindle body section (4) is a curved surface formed by rotating through taking an airfoil profile chord line as a central line according to an airfoil profile (4'); the fairing tail section (5) is a curved surface formed by multi-section scanning of two sets of curved lines of an airfoil profile (5') and an airfoil profile (5''); the fairing transition section (2) and a fairing transition section (2') are transition curved surfaces formed by rounding the fuselage appearance section (1), the fairing equal-diameter section (3), the fairing spindle body section (4) and the fairing tail section (5) by a certain fillet radius, so as to ensure the gentle transition of all the sections of the antenna fairing. According to the aircraft antenna fairing, the influences on aerodynamic characteristics of an aircraft by the antenna fairing are reduced, and the low resistance characteristic is obvious.
Description
Technical field
The utility model relates to aircraft aerodynamic arrangement design field, particularly antenna dome configuration design.
Background technology
Along with the development of aeronautical technology, the electronic machine on aircraft is more and more many, and the antenna amount of installing on airframe surface is also by increasing.Aircraft surfaces is generally all given prominence in the installation of antenna, to aircraft surfaces aerodynamic characteristic, certainly will bring negative effect, increases aircraft flight resistance.For avoiding fuselage outside face to block, generally by C-band directional antenna arrangement a distance outside fuselage, and adopt elliposoidal antenna dome protection antenna, as shown in Figure 1.Because its leading edge spherical radius is larger, easily produce shock wave; And trailing edge convergence is too fast, with obvious flow separation phenomenon, easily produces pressure drag, increase aircraft drag coefficient.
Utility model content
(1) the purpose of this utility model
The purpose of this utility model is to propose a kind of have good aeroperformance, the aircraft antenna fairing profile of lower drag coefficient.
(2) the technical solution of the utility model
The technical scheme that the utility model is taked is: a kind of aircraft antenna fairing, and according to Curve of wing, stretch or rotate to form, it comprises straight section, fairing spindle section and the fairing rears such as fuselage appearance section, fairing transition phase, fairing; The straight sections such as fairing are the curved surfaces that stretches and form along antenna axis direction according to aerofoil profile 3 '; Spindle section is according to the aerofoil profile 4 ' curved surface that line rotates to form centered by the aerofoil profile string of a musical instrument; Fairing rear is by aerofoil profile 5 ' and 5 ' ' two suite line multi-sections scan the curved surface of formation; Fairing transition phase be by certain radius of rounding by the fillet surface of straight section, fairing spindle section and the fairing rear roundings such as fuselage appearance section, fairing, guarantee that between each section of antenna dome, transition is mild.
Described aerofoil profile is blunt leading edge symmetrical airfoil or sharp leading edge symmetrical airfoil.
(3) the beneficial effects of the utility model:
Technical solutions of the utility model have been avoided the burbling effect of shock wave and the trailing edge of radome leading edge, and assurance radome can be protected antenna, has again lower aerodynamic drag, reduce the impact of radome on aircraft aerodynamic characteristic, have obvious low resistance characteristic.
Accompanying drawing explanation
Fig. 1 is elliposoidal antenna dome schematic diagram;
Fig. 2 is the utility model antenna dome axonometric drawing;
Fig. 3 is the utility model antenna dome aerofoil profile schematic diagram.
The specific embodiment
A kind of embodiment of the present utility model is: as shown in Figure 2, a kind of aircraft antenna fairing, according to Curve of wing, stretch or rotate to form, comprising straight section 3, fairing spindle section 4 and the fairing rears 5 such as fuselage appearance section 1, fairing transition phase 2, fairing; The straight sections such as fairing 3 are the curved surfaces that stretch and form along antenna axis direction according to aerofoil profile 3 '; Spindle section 4 is according to the aerofoil profile 4 ' curved surface that line Rotate 180 degree forms centered by the aerofoil profile string of a musical instrument, guarantees the motion space of antenna array; Fairing rear 5 is by aerofoil profile 5 ' and 5 ' ' two suite line multi-sections scan the curved surface of formation; Fairing transition phase 2 and 2 ' is, by certain radius of rounding, round fillet surface is led in straight section 3, fairing spindle section 4 and fairing rear 5 junctions such as fuselage appearance section 1, fairing, guarantees that between each section of antenna dome, transition is mild.The described straight sections (3) such as connection fairing are 50mm with fairing transition phase (2) radius of circle of fuselage appearance section (1).
Fairing transition phase (the 2 ') radius of circle of described straight section (3), fairing spindle section (4) and the fairing rears (5) such as connection fairing is 20mm.
The utility model is chosen aerofoil profile, first according to antenna size, considers, in the situation that can meeting antenna movement space and requirements of installation space, pursues fairing wetted area minimum as far as possible.For avoiding, produce lateral aerodynamics on fairing simultaneously, and according to aircraft flight speed, should choose blunt leading edge symmetrical airfoil or sharp leading edge symmetrical airfoil, blunt edge Airfoil is applicable to dopey, and sharp edge Airfoil is applicable to high-speed aircraft.
Claims (4)
1. an aircraft antenna fairing, stretches or rotates to form according to Curve of wing, and it comprises straight section (3), fairing spindle section (4) and the fairing rears (5) such as fuselage appearance section (1), fairing transition phase (2), fairing; The straight sections such as fairing (3) are the curved surfaces that stretches and form along antenna axis direction according to aerofoil profile (3 '); Spindle section (4) is according to aerofoil profile (the 4 ') curved surface that line rotates to form centered by the aerofoil profile string of a musical instrument; Fairing rear (5) is that the two suite line multi-sections by aerofoil profile (5 ', 5 ' ') scan the curved surface of formation; Fairing transition phase (2,2 ') be by certain radius of rounding by the fillet surface of straight section (3), fairing spindle section (4) and fairing rear (5) roundings such as fuselage appearance section (1), fairing, guarantee that between each section of antenna dome, transition is mild.
2. a kind of aircraft antenna fairing according to claim 1, is characterized in that selected aerofoil profile is blunt leading edge symmetrical airfoil or sharp leading edge symmetrical airfoil.
3. a kind of aircraft antenna fairing according to claim 1, it is characterized in that connecting the straight sections such as fairing (3), to lead radius of circle with the fairing transition phase (2) of fuselage appearance section (1) be 50mm.
4. a kind of aircraft antenna fairing according to claim 1, it is 20mm that the fairing transition phase (2 ') that it is characterized in that connecting the straight sections such as fairing (3), fairing spindle section (4) and fairing rear (5) is led radius of circle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320377102.6U CN203428019U (en) | 2013-06-28 | 2013-06-28 | Aircraft antenna fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320377102.6U CN203428019U (en) | 2013-06-28 | 2013-06-28 | Aircraft antenna fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203428019U true CN203428019U (en) | 2014-02-12 |
Family
ID=50057074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320377102.6U Withdrawn - After Issue CN203428019U (en) | 2013-06-28 | 2013-06-28 | Aircraft antenna fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203428019U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103303461A (en) * | 2013-06-28 | 2013-09-18 | 江西洪都航空工业集团有限责任公司 | Airplane antenna cowling |
| CN110159358A (en) * | 2018-02-14 | 2019-08-23 | 中国航发商用航空发动机有限责任公司 | Casing between grade |
-
2013
- 2013-06-28 CN CN201320377102.6U patent/CN203428019U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103303461A (en) * | 2013-06-28 | 2013-09-18 | 江西洪都航空工业集团有限责任公司 | Airplane antenna cowling |
| CN110159358A (en) * | 2018-02-14 | 2019-08-23 | 中国航发商用航空发动机有限责任公司 | Casing between grade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140212 Effective date of abandoning: 20160210 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |