CN203937856U - A kind of fusion type wing wing tip radome profile - Google Patents
A kind of fusion type wing wing tip radome profile Download PDFInfo
- Publication number
- CN203937856U CN203937856U CN201420316481.2U CN201420316481U CN203937856U CN 203937856 U CN203937856 U CN 203937856U CN 201420316481 U CN201420316481 U CN 201420316481U CN 203937856 U CN203937856 U CN 203937856U
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- wing
- radome
- aircraft
- antenna cover
- profile
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Abstract
The utility model belongs to overall Design of Aerodynamic Configuration field, relates to aircraft wing antenna cover, is specifically related to a kind of fusion type wing wing tip radome profile.Because the antenna shapes size installing additional is larger, in the topological design of radome, adopt radome profile and aircraft wing to merge transition flow line design method, while avoiding airflow passes radome, separate, improve air velocity distribution; Meeting under the prerequisite of task system operating needs, reduce the oad of radome, to reduce the aerodynamic characteristic impact of attaching antenna cover on carrier aircraft as far as possible.Wing wing tip radome has increased the effective aspect ratio of wing, and aircraft maximum lift coefficient is mentioned, and induced drag declines to some extent, has improved aircraft aerodynamic characteristic.
Description
Technical field: the invention belongs to overall Design of Aerodynamic Configuration field, relate to aircraft wing antenna cover.
Background technology: according to carrier aircraft and the full machine antenna arrangement of task system and meet the requirements such as electromagnetic compatibility, aircraft need install enemy and we additional at wing identifies radome, installing the aspect aerodynamic characteristics such as resistance, wing aspect ratio and the lift coefficient of this radome to carrier aircraft additional exerts an influence, in order to ensure that aircraft has good aerodynamic characteristic, preferably airworthiness and flight quality, meeting under task system mission and operation operating needs prerequisite, the wing antenna cover that need as far as possible reduce to install additional affects carrier aircraft aerodynamic characteristic.
Summary of the invention:
1) technical matters solving
The object of the invention is: the wing antenna cover that reduces to install additional, on the impact of carrier aircraft aerodynamic characteristic, proposes a kind of wing antenna cover.
Technical solution of the present invention is, adopts radome profile and outer wing to merge transition flow line design method in the topological design of wing antenna cover, while avoiding airflow passes radome, separates, and improves air velocity distribution; Meeting under the prerequisite of task system operating needs, reduce the oad of radome as far as possible.
2) technical scheme
A kind of fusion type wing wing tip radome profile, wing antenna cover is long 1.2m (containing transition phase), thick 0.3m, is patty from wing outermost end along exhibition to contraction.Wing antenna cover is detachable, and it is screwed on wing outermost end costal margin bar.Taking radome forward terminal as origin of coordinates O, after X axis, for just, in Y-axis, for just, Z-axis direction is left to be chosen by following coordinate points for just, and measure unit is mm:
All coordinate points are connected into SPL and generate curved surface, form the aerodynamic configuration of wing antenna cover.
3) beneficial effect
The advantage that the present invention has and beneficial effect, radome profile of the present invention, by adopting radome profile and aircraft outer wing to merge transition flow line design method, has increased the effective aspect ratio of wing, aircraft maximum lift coefficient is mentioned, and induced drag declines to some extent.Meeting under the prerequisite of task system operating needs, reduce the oad of radome as far as possible, make radome less on the aerodynamic characteristic impact of carrier aircraft.
Brief description of the drawings
Fig. 1: a kind of wing wing tip radome birds-eye view;
A kind of wing wing tip of Fig. 2 radome lateral plan;
A kind of wing wing tip of Fig. 3 radome three-view diagram;
A kind of wing wing tip of Fig. 4 radome profile design sketch.
Concrete implementing method
A kind of wing antenna cover profile, wing antenna cover is long 1.2m (containing transition phase), thick 0.3m, taking certain type machine as example, is patty from wing 27 ribs along exhibition to contraction.Wing antenna cover is detachable, and it is screwed on No. 27 costal margin bars, and outside is wing antenna cover, and wing antenna cover inner side is connected with 27 ribs.
Taking radome forward terminal as origin of coordinates O, after X axis, for just, in Y-axis, for just, Z-axis direction is left to be chosen by following coordinate points for just, and measure unit is mm:
All coordinate points are connected into SPL and generate curved surface, form the aerodynamic configuration of wing antenna cover.
Claims (1)
1. a fusion type wing wing tip radome profile, wing antenna cover is 1.2m, thick 0.3m containing transition segment length, is patty from wing outermost end along exhibition to contraction; Wing antenna cover is detachable, and it is screwed on wing outermost end costal margin bar; Taking radome forward terminal as origin of coordinates O, after X axis, for just, in Y-axis, for just, Z-axis direction is left to be chosen by following coordinate points for just, and measure unit is mm:
All coordinate points are connected into SPL and generate curved surface, form the aerodynamic configuration of wing antenna cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420316481.2U CN203937856U (en) | 2014-06-13 | 2014-06-13 | A kind of fusion type wing wing tip radome profile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420316481.2U CN203937856U (en) | 2014-06-13 | 2014-06-13 | A kind of fusion type wing wing tip radome profile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203937856U true CN203937856U (en) | 2014-11-12 |
Family
ID=51857195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420316481.2U Active CN203937856U (en) | 2014-06-13 | 2014-06-13 | A kind of fusion type wing wing tip radome profile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203937856U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
-
2014
- 2014-06-13 CN CN201420316481.2U patent/CN203937856U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
| CN109484620B (en) * | 2018-03-16 | 2022-05-13 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |