CN109484620A - Overlapped disc radome on back of body - Google Patents
Overlapped disc radome on back of body Download PDFInfo
- Publication number
- CN109484620A CN109484620A CN201810220401.6A CN201810220401A CN109484620A CN 109484620 A CN109484620 A CN 109484620A CN 201810220401 A CN201810220401 A CN 201810220401A CN 109484620 A CN109484620 A CN 109484620A
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- China
- Prior art keywords
- antenna
- antenna house
- cover
- aircraft
- bottom disc
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses an overlapped disc radome on the back of a fuselage, belongs to the field of overall aerodynamic shape design, and relates to a fusion design of two radomes on the back of a certain airplane. Because the difference of the external dimensions of the additionally-installed antenna is large, the appearance of a small disc is fused with a large disc in the layout design of the antenna housing, and the basic appearance of the antenna housing is determined under the condition that the minimum envelope of the antenna is met. On the premise of meeting the use requirement of the antenna housing, the size of the antenna housing is reduced as much as possible, the windward area and the infiltration area of the antenna housing are reduced, the aerodynamic resistance is small, the local flow field characteristic is good, the separation flow is inhibited, the wake flow field is improved, the interference on the static stability of the aircraft course and the efficiency of a control surface is reduced, and finally the excellent task use characteristic and the aerodynamic characteristic of the antenna housing are proved through the aircraft test flight verification.
Description
Technical field:
The present invention relates to a kind of Combined designs of the Overlapping disk aerial cover of the fuselage back in aircraft back, belong to winged
Machine totality Design of Aerodynamic Configuration field.
Background technique:
" a kind of " Overlapping disk aerial cover of fuselage back " Disclosure of invention " discloses a kind of RECTIFYING ANTENNA cover.The day
The design of irdome is under the premise of meeting two kinds of antenna requirements, at aircraft back using the conic section conduct of optimization
The antenna house Combined design shape of fairing streamline is longitudinally, laterally generated with lateral control line, and uses CFD and wind tunnel test
Design is optimized to control line parameter in means.Preferred final scheme have aerodynamic drag it is small, to vector static-stability
Property and rudder effectiveness interfere the advantages of.
Summary of the invention:
(1) goal of the invention
The present invention minimizes attaching antenna cover to full machine aerodynamic characteristic under the premise of meeting two kinds of antenna requirements
Influence, propose a kind of Combined design of the Overlapping disk aerial cover of fuselage back.
The technical solution of the invention is as follows, according to the antenna requirement, the antenna mounting locations is determined, according to the type
Antenna minimum envelop determines the basic shape of the antenna house.Two kinds of antenna house fusions and transition repairing type, minimize the outer of antenna house
Shape size, to reduce front face area and wetted area, to reduce augmented resistance.The design of the antenna house is meeting antenna use
Under the premise of it is required that, the small, interference to vector static stability and rudder effectiveness with aerodynamic drag of preferred final scheme
Lesser advantage.
(2) technical solution
In order to solve the above-mentioned technical problem, the present invention is achieved by the following technical solutions: a kind of weight of fuselage back
Stack-type disk aerial cover, using the conic section of optimization as longitudinally, laterally and laterally in the fusion configuration design of antenna house
Control line generate the antenna house smooth-shaped transition of fairing streamline, and control line is joined by CFD and wind tunnel test means
Design is optimized in number.
Bottom disc shape antenna house is rotational ellipsoid, the friendship about aircraft plane of symmetry bilateral symmetry, with the aircraft plane of symmetry
Line is ellipse.The antenna house central point is located in 35 frame plane of aircraft, and central point is located at 6180mm on horizontal plane, bottom circle
Disk antenna cover and aircraft horizontal plane are installed at ± 5 ° of angles, disc radius 3900mm, maximum gauge 1544.5mm.Disk
For zero advance from for 3365mm, its wetted area of disk aerial cover is 102.624m2, front face area to antenna house on fuselage
9.541m2.Left and right supporting leg radome fairing is symmetrical relative to aircraft symmetrical plane.
Upper antenna cover shape is disc, is located at middle position at the top of bottom disc antenna house, prominent disk upper surface
Maximum height 321mm is 906.1mm with back disk aerial cover intersecting lens radius.Upper antenna cover wetted area is
3.113m2, front face area 0.442m2.
Using bottom disc antenna house forward terminal as coordinate origin O, it is positive, is positive in Y-axis, Z axis meets left hand after X axis
Rule, and by bottom big disk, top roundel front and rear edges vertex characterized by, at a certain distance be distributed 11 feature profiles.
Since this disk aerial cover is symmetrical about X/Y plane, the shape of Z axis positive axis is only gived, according to the form below coordinate points are chosen,
Measurement unit is mm:
All coordinate points are connected into spline curve and generate curved surface, form the right side shape of the antenna house, left side about
XOY plane is symmetrical.By the optimization of full mechanism type, final choice bottom disc shape antenna house and aircraft horizontal plane are at -2 °
Angle installation can reach optimal aerodynamic characteristic.
3) beneficial effect
The beneficial effects of the present invention are: a kind of Overlapping disk aerial cover of fuselage back of the invention, by using stream
On the one hand bottom big disk antenna house and top roundel antenna house Combined design are met making for antenna by linear homogeneous transition
With requiring, on the other hand reduces antenna house and install bring structure and aerodynamic effects additional.After merging shape using antenna house, antenna house
Bring augmented resistance and smaller to the interference of full machine directional static stability and rudder effectiveness.
Detailed description of the invention
Attached drawing of the invention has 2, and Detailed description of the invention is as follows:
Fig. 1 is a kind of three-view diagram of the Overlapping disk aerial cover Combined design shape of fuselage back；
Fig. 2 is a kind of scheme of installation of the Overlapping disk aerial cover Combined design shape of fuselage back,
1 is antenna house Combined design shape, and 2 be antenna house supporting leg, and 3 be fuselage.
Specific implementation method
A kind of Overlapping disk aerial cover of fuselage back, characterized in that using antenna house forward terminal as coordinate origin O, X-axis
It is positive, is positive in Y-axis backward, Z axis meets left hand rule.The characteristic face of the shape is chosen after X axis, and total 11 are cutd open
Face, wherein section is respectively 500mm, 1000mm, 2000mm apart from bottom disc leading edge vertex between first three.Three section distances afterwards
Disk rear vertex -500mm, -1000mm, -2000mm.5 intermediate sections are spy with the front and rear edges vertex of top roundel
Sign is equally spaced.Since this antenna house is symmetrical about X/Y plane, the shape of Z axis positive axis, according to the form below coordinate are only gived
Point is chosen, measurement unit mm:
All coordinate points are connected into spline curve and generate curved surface, form the right side shape of the antenna house, left side about
XOY plane is symmetrical.
Claims (5)
1. a kind of Overlapping disk aerial cover of fuselage back, it is characterised in that: the antenna house includes bottom disc shape antenna
Cover and upper antenna cover；The bottom disc shape antenna house is rotational ellipsoid, about aircraft plane of symmetry bilateral symmetry, with aircraft
The intersection of the plane of symmetry is ellipse；The bottom disc shape antenna house central point is located in 35 frame plane of aircraft, and central point is located at level
6180mm on datum level, the bottom disc shape antenna house and aircraft horizontal plane are installed at ± 5 ° of angles, and disc radius is
3900mm, maximum gauge 1544.5mm；Zero advance is from for 3365mm on fuselage for bottom disc shape antenna house, the top day
Irdome shape is disc, is located at middle position at the top of bottom disc antenna house, protrudes disk upper surface maximum height 321mm,
It is 906.1mm with bottom disc shape antenna house intersecting lens radius；Using bottom disc antenna house forward terminal as coordinate origin O, X axis
After be positive, be positive in Y-axis, Z axis meets left hand rule, and with the front and rear edges of bottom disc shape antenna house and upper antenna cover
Vertex is characterized, and is distributed 11 feature profiles at a certain distance；According to the form below coordinate points are chosen, measurement unit mm:
All coordinate points are connected into spline curve and generate curved surface, form the right side shape of the antenna house.
2. a kind of Overlapping disk aerial cover of fuselage back according to claim 1, it is characterised in that: the bottom circle
Its wetted area of disk antenna cover is 102.624m2, front face area 9.541m2；Left and right supporting leg radome fairing is symmetrical relative to aircraft
Plane is symmetrical.
3. a kind of Overlapping disk aerial cover of fuselage back according to claim 1, it is characterised in that: the top day
Irdome wetted area is 3.113m2, front face area 0.442m2。
4. a kind of Overlapping disk aerial cover of fuselage back according to claim 1, it is characterised in that: the bottom circle
Disk antenna cover and aircraft horizontal plane are installed at -2 ° of angles.
5. a kind of Overlapping disk aerial cover of fuselage back according to claim 1, it is characterised in that: the antenna house
Left side is symmetrical about XOY plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810220401.6A CN109484620B (en) | 2018-03-16 | 2018-03-16 | Overlapped disc radome on back of body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810220401.6A CN109484620B (en) | 2018-03-16 | 2018-03-16 | Overlapped disc radome on back of body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109484620A true CN109484620A (en) | 2019-03-19 |
| CN109484620B CN109484620B (en) | 2022-05-13 |
Family
ID=65687388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810220401.6A Active CN109484620B (en) | 2018-03-16 | 2018-03-16 | Overlapped disc radome on back of body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109484620B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB519809A (en) * | 1938-10-04 | 1940-04-05 | Standard Telephones Cables Ltd | Improvements in or relating to casings for enclosing antenna systems on moving vehicles |
| US3026516A (en) * | 1957-12-02 | 1962-03-20 | Lockheed Aircraft Corp | Rotatable radome for aircraft |
| US5986611A (en) * | 1998-07-10 | 1999-11-16 | Northrop Grumman Corporation | Steerable disk antenna |
| CN203937856U (en) * | 2014-06-13 | 2014-11-12 | 陕西飞机工业（集团）有限公司 | A kind of fusion type wing wing tip radome profile |
| CN105024158A (en) * | 2015-06-23 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | Early warning radar and aircraft provided with same |
| CN106628109A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Rotating and connecting structure of aircraft radome |
| CN107745796A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | A kind of double supporting legs of backpack large-scale antenna dome |
| 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
- 2018-03-16 CN CN201810220401.6A patent/CN109484620B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB519809A (en) * | 1938-10-04 | 1940-04-05 | Standard Telephones Cables Ltd | Improvements in or relating to casings for enclosing antenna systems on moving vehicles |
| US3026516A (en) * | 1957-12-02 | 1962-03-20 | Lockheed Aircraft Corp | Rotatable radome for aircraft |
| US5986611A (en) * | 1998-07-10 | 1999-11-16 | Northrop Grumman Corporation | Steerable disk antenna |
| CN203937856U (en) * | 2014-06-13 | 2014-11-12 | 陕西飞机工业（集团）有限公司 | A kind of fusion type wing wing tip radome profile |
| CN105024158A (en) * | 2015-06-23 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | Early warning radar and aircraft provided with same |
| CN106628109A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Rotating and connecting structure of aircraft radome |
| CN107745796A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | A kind of double supporting legs of backpack large-scale antenna dome |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 台风: "E-2鹰眼预警机的前世今生", 《舰载武器》 * |
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| Publication number | Publication date |
|---|---|
| CN109484620B (en) | 2022-05-13 |
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