CN206050085U - A kind of stealthy lip of aircraft - Google Patents
A kind of stealthy lip of aircraft Download PDFInfo
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- CN206050085U CN206050085U CN201620963059.5U CN201620963059U CN206050085U CN 206050085 U CN206050085 U CN 206050085U CN 201620963059 U CN201620963059 U CN 201620963059U CN 206050085 U CN206050085 U CN 206050085U
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- lip
- stealthy
- main structure
- utility
- permeation layer
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Abstract
This utility model discloses a kind of stealthy lip of aircraft, including the structural member that carbon fiber main structure, suction ripple foam, wave permeation layer are constituted.Lip carbon fiber main structure described in the utility model adopts carbon fibre composite mould pressing technology global formation, inner mold face to increase reinforcement to increase the strength and stiffness requirement of lip configuration, the spacing L=120mm ~ 190mm of reinforcement；Wave permeation layer quartz fibre compression molding；Suction ripple layer is layered on top of each other combination by PMI foams and microwave absorbing coating and constitutes.This utility model is applied to complex structure, has the lip configuration of stealthy requirement, and its advantage is simple structure, lightweight, easily assemble, dimensional accuracy is high, aerodynamic configuration is good, substantially increases structural strength, the rigidity of lip, larger load, long service life, RCS can be born（RCS）Value is greatly lowered；Can be widely used for the structure-design technique field of middle-size and small-size military unmanned air vehicle.
Description
Technical field：
This utility model belongs to field of airplane structure, the more particularly to designing technique of inlet lip.
Background technology：
The complex contour of aircraft lip, now generally using the method manufacture of casting or machining.In modern war
In the environment of, Stealth Fighter becomes the important indicator of operational aircraft, and lip is one stronger scattering source of aircaft configuration, therefore
Lip becomes certainty using stealth structure.
The content of the invention：
The purpose of this utility model is：For the weak point that above-mentioned prior art is present, there is provided one kind can guarantee that aircraft
Overall performance, strength and stiffness are high, lightweight, inner surface quality is good, dimensional accuracy is high, easy to assembly, life-span length, can bear winged
The larger aerodynamic loading of machine and the lip with Stealth Fighter.
This utility model solves the technical scheme adopted by its technical problem：
A kind of stealthy lip of aircraft, including, main structure, inhales ripple foam and wave permeation layer；Main structure is framework, inhale ripple foam and
Wave permeation layer fits in the front portion of main structure successively；The section of main structure is the U-shaped thin-wall construction with wedge, and the front portion of main structure is
V-type wedge.
The U-shaped intracavity that the U-shaped thin-wall construction of the main structure is formed is disposed with reinforcement.
The spacing of the reinforcement is 120mm ~ 190mm.
The main structure is continuous fiber integral die shaping.
It is described to inhale the sandwich that ripple foam is that PMI foams are constituted with the mutual lamination of microwave absorbing coating.
The wave permeation layer adopts continuous quartz fibre compression molding.
This utility model beneficial effect compared with prior art is：
This utility model changes into the stealthy functor of composite global formation by ordinary construction part, lightweight；Size essence
Degree is high, and inner surface quality is good, and aerodynamic configuration is good；Strong muscle be increased in the U-shaped intracavity of lip, lip strength and stiffness are increased, subtracted
It is little compared with the deformation under big load；Lip Radar Cross Section RSC values are significantly reduced using stealth structure.
Description of the drawings：
Fig. 1 is structural representation of the present utility model,
A-A sectional views of the Fig. 2 for Fig. 1,
Fig. 3 is reinforcement view,
Fig. 4 axonometric charts of the present utility model.
In figure：1. main structure, 2. inhales ripple foam, 3. wave permeation layer, 4. reinforcement.
Specific embodiment：
In Fig. 1 to Fig. 4, the stealthy lip of composite of the present utility model is made up of three parts, carbon fiber main structure 1,
Its section is thin-walled with the U-shaped of wedge, is the laminated construction that PMI foams and microwave absorbing coating are constituted in wedge front end, is inhaling ripple bubble
Wave permeation layer of 2 front end of foam for quartz fibre compression molding,
（1）Carbon fiber main structure 1, its section is the U-shaped thin-wall construction with wedge, and the reinforcement 4 of intermediate arrangement lip increases
Plus rigidity and bearing capacity, the spacing of reinforcement is L=120mm ~ 190mm, using continuous fiber integral die shaping；
（2）Inhale the structure that ripple foam 2 is constituted using the mutual lamination of PMI foams and microwave absorbing coating；
（3）Wave permeation layer 3 adopts quartz fibre integral die shaping, and wave transparent performance is good；
（4）In carbon fiber main structure 1, after inhaling the difference molding of ripple foam 2, wave permeation layer 3, then cementation solidifying molding.
In an example of the present utility model, the process of its process implementing is：The reinforcement 4 for arranging lip has 14,
First carbon fiber continuous fiber is laid on mould, main structure 1 is obtained using compression molding；Quartz fibre is laid into mould
On, wave permeation layer 3 is obtained using molded industrial；After Foam machining section, using wave permeation layer as mould, the lamination knot of ripple foam will be inhaled
Structure bonding forming；Finally by carbon fiber main structure 1, suction ripple foam 2,3 cementation solidifying molding of wave permeation layer.
Embodiment and its accompanying drawing of the concrete structure of the present utility model by more than are given.But not therefore by this utility model
Among being limited in described scope of embodiments.
Claims (6)
1. the stealthy lip of a kind of aircraft, it is characterised in that include, main structure, inhales ripple foam and wave permeation layer；Main structure is framework,
Inhale ripple foam and wave permeation layer fits in the front portion of main structure successively；The section of main structure is the U-shaped thin-wall construction with wedge, main knot
The front portion of structure is V-type wedge.
2. a kind of stealthy lip of aircraft according to claim 1, it is characterised in that the U-shaped thin-wall construction of the main structure
The U-shaped intracavity for being formed is disposed with reinforcement.
3. the stealthy lip of a kind of aircraft according to claim 2, it is characterised in that the spacing of the reinforcement be 120mm ~
190mm。
4. the stealthy lip of a kind of aircraft according to claim 1, it is characterised in that the main structure is continuous fiber entirety
Compression molding.
5. the stealthy lip of a kind of aircraft according to claim 1, it is characterised in that the suction ripple foam be PMI foams with
The sandwich that the mutual lamination of microwave absorbing coating is constituted.
6. the stealthy lip of a kind of aircraft according to claim 1, it is characterised in that the wave permeation layer is fine using continuous quartz
Dimension compression molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620963059.5U CN206050085U (en) | 2016-08-29 | 2016-08-29 | A kind of stealthy lip of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620963059.5U CN206050085U (en) | 2016-08-29 | 2016-08-29 | A kind of stealthy lip of aircraft |
Publications (1)
| Publication Number | Publication Date |
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| CN206050085U true CN206050085U (en) | 2017-03-29 |
Family
ID=58382126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201620963059.5U Active CN206050085U (en) | 2016-08-29 | 2016-08-29 | A kind of stealthy lip of aircraft |
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| CN (1) | CN206050085U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107310739A (en) * | 2017-07-31 | 2017-11-03 | 西安天拓航空科技有限公司 | The leading edge load installation system of the stealthy unmanned plane of Flying-wing |
| CN111232227A (en) * | 2020-01-16 | 2020-06-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| CN112407236A (en) * | 2020-10-27 | 2021-02-26 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich graphene stealth front edge and processing method thereof |
| CN112606993A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Flap edge scattering suppression device |
| CN114162336A (en) * | 2021-12-14 | 2022-03-11 | 北京机电工程研究所 | Aircraft radar stealth air inlet duct and preparation method thereof |
-
2016
- 2016-08-29 CN CN201620963059.5U patent/CN206050085U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107310739A (en) * | 2017-07-31 | 2017-11-03 | 西安天拓航空科技有限公司 | The leading edge load installation system of the stealthy unmanned plane of Flying-wing |
| CN111232227A (en) * | 2020-01-16 | 2020-06-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| CN111232227B (en) * | 2020-01-16 | 2021-11-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| CN112407236A (en) * | 2020-10-27 | 2021-02-26 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich graphene stealth front edge and processing method thereof |
| CN112606993A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | Flap edge scattering suppression device |
| CN114162336A (en) * | 2021-12-14 | 2022-03-11 | 北京机电工程研究所 | Aircraft radar stealth air inlet duct and preparation method thereof |
| CN114162336B (en) * | 2021-12-14 | 2024-01-05 | 北京机电工程研究所 | Stealth air inlet channel of aircraft radar and preparation method thereof |
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