CN203937855U - A kind of abdomeinal fin profile - Google Patents
A kind of abdomeinal fin profile Download PDFInfo
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- CN203937855U CN203937855U CN201420317460.2U CN201420317460U CN203937855U CN 203937855 U CN203937855 U CN 203937855U CN 201420317460 U CN201420317460 U CN 201420317460U CN 203937855 U CN203937855 U CN 203937855U
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- abdomeinal fin
- profile
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- abdomeinal
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- 230000003068 static effect Effects 0.000 abstract description 9
- 210000001015 abdomen Anatomy 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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Abstract
The utility model belongs to Design of Aerodynamic Configuration field, relates to aircraft abdomeinal fin.An abdomeinal fin profile, this abdomeinal fin lateral projection is trapezoid, and abdomeinal fin integral body is the tabular profile of equal thickness, and except the limit being connected with fuselage, suitably rounding has been carried out in the edge on its excess-three limit and edges and corners thereof.Abdomeinal fin profile of the present utility model, can increase the course static stability of aircraft under At High Angle of Attack state effectively, and less on the aerodynamic characteristic impact of aircraft other side.
Description
Technical field
The invention belongs to Design of Aerodynamic Configuration field, relate to a kind of abdomeinal fin.
Background technology
For solving aircraft course static stability when approaching stall, significantly reduce problem, in the design of aircraft rear belly, installed a secondary abdomeinal fin additional, after installing this abdomeinal fin additional, effectively increase the course static stability of aircraft under At High Angle of Attack state, and the aerodynamic characteristic impact on aircraft other side is less, has improved the flight quality of aircraft when approaching stall.
Summary of the invention
The object of the invention is: increase the course static stability of aircraft under At High Angle of Attack state, propose a kind of abdomeinal fin.
Technical solution of the present invention is, in the design of aircraft rear belly, installed a secondary abdomeinal fin additional, to increase the course static stability of aircraft under At High Angle of Attack state, and the impact of strict control abdomeinal fin on aircraft other side aerodynamic characteristic on course stability compensation.An abdomeinal fin profile, abdomeinal fin lateral projection is trapezoid, its root chord length 4526mm, maximum height 1035mm, 60 ° of leading edge sweeps, 73 ° of trailing edge sweepforward angles, the corner angle of abdomeinal fin front and rear edges and sharp string junction carry out rounding, and chamfering radius is 300mm; Abdomeinal fin integral body is the tabular profile of equal thickness, and thickness is 100mm, and except the limit being connected with fuselage, rounding has been carried out in the edge on its excess-three limit and edges and corners thereof.Abdomeinal fin profile and size are shown in Fig. 1 and Fig. 2.
The advantage that the present invention has and beneficial effect: abdomeinal fin profile of the present invention, can effectively increase the course static stability of aircraft under At High Angle of Attack state, and less on the aerodynamic characteristic impact of aircraft other side.The result shows: with respect to not adding abdomeinal fin state, this radome makes vector static stability increase by 50% left and right, and the impact of lift, resistance, rudder effectiveness and Lateral static stability is not more than to 1.5%, and the impact of Longitudinal static stability is not more than to 3.5%.
Accompanying drawing explanation
Tu1Shi lateral projection of the present invention schematic diagram;
Fig. 2 is abdomen perspective view of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described in further detail:
An abdomeinal fin profile, abdomeinal fin lateral projection is trapezoid, its root chord length 4526mm, maximum height 1035mm, 60 ° of leading edge sweeps, 73 ° of trailing edge sweepforward angles, the corner angle of abdomeinal fin front and rear edges and sharp string junction carry out rounding, and chamfering radius is 300mm; Abdomeinal fin integral body is the tabular profile of equal thickness, and thickness is 100mm, and except the limit being connected with fuselage, suitably rounding has been carried out in the edge on its excess-three limit and edges and corners thereof.Abdomeinal fin profile and size are shown in Fig. 1 and Fig. 2.
Claims (1)
1. an abdomeinal fin profile, is characterized in that, abdomeinal fin lateral projection is trapezoid, its root chord length 4526mm, maximum height 1035mm, 60 ° of leading edge sweeps, 73 ° of trailing edge sweepforward angles, the corner angle of abdomeinal fin front and rear edges and sharp string junction carry out rounding, and chamfering radius is 300mm; Abdomeinal fin integral body is the tabular profile of equal thickness, and thickness is 100mm, and except the limit being connected with fuselage, rounding has been carried out in the edge on its excess-three limit and edges and corners thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420317460.2U CN203937855U (en) | 2014-06-13 | 2014-06-13 | A kind of abdomeinal fin profile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420317460.2U CN203937855U (en) | 2014-06-13 | 2014-06-13 | A kind of abdomeinal fin profile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203937855U true CN203937855U (en) | 2014-11-12 |
Family
ID=51857194
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420317460.2U Expired - Lifetime CN203937855U (en) | 2014-06-13 | 2014-06-13 | A kind of abdomeinal fin profile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203937855U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667767A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Tubular beam framework type pelvic fin structure |
| CN110966897A (en) * | 2019-12-18 | 2020-04-07 | 湖北航天技术研究院总体设计所 | Empennage of rocket projectile and design method thereof |
-
2014
- 2014-06-13 CN CN201420317460.2U patent/CN203937855U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667767A (en) * | 2016-03-25 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Tubular beam framework type pelvic fin structure |
| CN110966897A (en) * | 2019-12-18 | 2020-04-07 | 湖北航天技术研究院总体设计所 | Empennage of rocket projectile and design method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141112 |