CN205469849U - Lip of all -wing aircraft overall arrangement aircraft - Google Patents
Lip of all -wing aircraft overall arrangement aircraft Download PDFInfo
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- CN205469849U CN205469849U CN201620140604.0U CN201620140604U CN205469849U CN 205469849 U CN205469849 U CN 205469849U CN 201620140604 U CN201620140604 U CN 201620140604U CN 205469849 U CN205469849 U CN 205469849U
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Abstract
The utility model relates to a lip of all -wing aircraft overall arrangement aircraft belongs to aircraft structural design field. A loop forming element that all -wing aircraft type overall arrangement lip structure, it is one and is connected to form by annular lip outer wall 4 and lip inner wall 5. Its leading edge cross sectional shape is one light -case " V " shape. (The shape of lip rear end face is relative with aircraft intake duct front end shape of face form, is connected through rivet 8 and first frame 7. The shape of terminal surface matches with aircraft fuselage covering 2 before the lip. The utility model is suitable for a lip structure of all -wing aircraft type overall arrangement aircraft, its advantage is simple structure, light in weight, easy assembly, size precision is high, and pneumatic appearance is good, has improved structural strength, the rigidity of lip greatly, can bear great load, long service life, RCS (radar scattering cross section ) value reduces by a wide margin, can extensively be used for all -wing aircraft type overall arrangement aircraft.
Description
Technical field
This utility model belongs to field of airplane structure, relates to the improvement to aircraft lip.
Background technology
The profile of airplane intake lip is complex-curved, and present commonly used segmentation is welded after carrying out metal plate punching
It is connected into the method manufacture of shape.The lip nose thickness of metal plate punching part is extremely thin, affects lip precision, and
And need expensive punch die, add manufacturing cost；Welding procedure to the intensity of part, precision and pneumatic outside
Shape all has an impact, and reduces the lip life-span.It addition, the lip of welding can not bear bigger load after metal plate punching
Lotus.
Summary of the invention
The purpose of this utility model is: proposes that a kind of intensity is high with precision, aerodynamic configuration is good, life-span length, become
This is the lowest, can bear bigger load and adapt to Flying-wing's lip configuration of stealthy demand.
This utility model solves its technical problem and be the technical scheme is that
The lip of a kind of Flying-wing aircraft, it is characterised in that include lip outer wall and lip inwall, lip
Outer wall and lip inwall are that annular, lip outer wall and lip inwall are fixing to be connected, and lip outer wall leading edge is in " W "
Shape, lip rear end face is fixing with airplane intake front end face to be connected.
The described lip outer wall leading edge sides aligned parallel in " W " shape.
Described leading edge cross sectional shape is the " V " shape of a thin-walled.
Described lip inwall arranged beneath has reinforcement 6.
Described lip is cast by aluminium alloy and integrated machine adds shaping.
The shape of this utility model lip rear end face is relative with airplane intake front end face shape, and passes through upper half
Frame connects.The shape at lip front end face edge matches with aircraft fuselage skin.Lip is by upper half frame and enters
Air flue riveting assembling.
This utility model compared with prior art provides the benefit that:
It is global formation part that this utility model becomes molectron, there is not weld seam, and dimensional accuracy is high, pneumatic outside
Shape is good.At lip outer wall arranged beneath reinforcement, substantially increase structural strength, bigger load can be born.
The sweepforward inclined design of outer wall leading edge " W " shape can reduce drag due to shock wave.Outer shroud sets in the edge of " W " shape
Meter have followed parallel principle simultaneously, reduces radar appearance, adapts to stealthy demand.
Accompanying drawing illustrates:
Concrete structure of the present utility model is given by below example and accompanying drawing thereof.But the most therefore by this reality
It is limited among described scope of embodiments with novel.
Fig. 1 is this utility model schematic perspective view
Fig. 2 is front view of the present utility model
Fig. 3 is top view of the present utility model
Fig. 4 is side view of the present utility model
Fig. 5 is leading edge profile figure of the present utility model
Fig. 6 is the lip reinforcement location drawing of the present utility model
Fig. 7 is assembling section of the present utility model
In figure: 1. lip, 2. fuselage skin, 3. air intake duct, 4. lip outer wall, 5. lip inwall, 6. reinforcement,
7. upper half frame, 8. rivet.
Detailed description of the invention:
Below this utility model is described in further details.
See Fig. 1 to Fig. 6, airplane intake lip of the present utility model, it be one by the lip outer wall of annular
4 and inwall 5 connect composition annular element.Top view shows that its profile leading edge is in " W " shape, leading edge profile figure
Show the V-arrangement that its cross sectional shape is a thin-walled.In an embodiment of the present utility model it is, in lip
" L " shape and "×" shape reinforcement 6 it has been arranged symmetrically with below wall 5.
Seeing Fig. 7, the shape of lip rear end face is relative with airplane intake front end face shape, lip 1 rear end face with
Air intake duct 3 eyelid covering front end face is relative, by upper half frame 7 and air intake duct 3, connects and is fixed by rivet 8.Lip
The shape at front end face edge matches with aircraft fuselage skin 2.
Claims (5)
1. the lip of Flying-wing's aircraft, it is characterised in that include lip outer wall and lip inwall, lip outer wall and lip inwall are annular, lip outer wall and the fixing connection of lip inwall, lip outer wall leading edge is in " W " shape, and lip rear end face is fixing with airplane intake front end face to be connected.
The lip of a kind of Flying-wing the most according to claim 1 aircraft, it is characterised in that the described lip outer wall leading edge sides aligned parallel in " W " shape.
The lip of a kind of Flying-wing the most according to claim 1 aircraft, it is characterised in that described leading edge cross sectional shape is the " V " shape of a thin-walled.
The lip of a kind of Flying-wing the most according to claim 1 aircraft, it is characterised in that described lip inwall arranged beneath has reinforcement (6).
The lip of a kind of Flying-wing the most according to claim 1 aircraft, it is characterised in that described lip is cast by aluminium alloy and integrated machine adds shaping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620140604.0U CN205469849U (en) | 2016-02-25 | 2016-02-25 | Lip of all -wing aircraft overall arrangement aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620140604.0U CN205469849U (en) | 2016-02-25 | 2016-02-25 | Lip of all -wing aircraft overall arrangement aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205469849U true CN205469849U (en) | 2016-08-17 |
Family
ID=56679016
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620140604.0U Active CN205469849U (en) | 2016-02-25 | 2016-02-25 | Lip of all -wing aircraft overall arrangement aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205469849U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112644680A (en) * | 2020-12-31 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of stealth aerostat |
| CN112798560A (en) * | 2020-12-24 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Cavity inner wall scattering characteristic pre-estimation carrier |
| CN115571351A (en) * | 2022-11-21 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Flying wing layout backpack air inlet channel with high-low speed performance and stealth performance |
-
2016
- 2016-02-25 CN CN201620140604.0U patent/CN205469849U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112798560A (en) * | 2020-12-24 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Cavity inner wall scattering characteristic pre-estimation carrier |
| CN112644680A (en) * | 2020-12-31 | 2021-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of stealth aerostat |
| CN115571351A (en) * | 2022-11-21 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Flying wing layout backpack air inlet channel with high-low speed performance and stealth performance |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |