CN112591072A - Can carry out flap that suppresses to gap scattering - Google Patents
Can carry out flap that suppresses to gap scattering Download PDFInfo
- Publication number
- CN112591072A CN112591072A CN202011552869.9A CN202011552869A CN112591072A CN 112591072 A CN112591072 A CN 112591072A CN 202011552869 A CN202011552869 A CN 202011552869A CN 112591072 A CN112591072 A CN 112591072A
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- China
- Prior art keywords
- gap
- chamfer
- flap
- skin
- scattering
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000003973 paint Substances 0.000 claims abstract description 18
- 239000000565 sealant Substances 0.000 claims abstract description 11
- 239000003795 chemical substances by application Substances 0.000 claims description 5
- 230000001629 suppression Effects 0.000 abstract description 4
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 10
- 238000013461 design Methods 0.000 description 10
- 230000007547 defect Effects 0.000 description 8
- 230000005764 inhibitory process Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000000181 anti-adherent effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000013100 final test Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 239000004922 lacquer Substances 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000008204 material by function Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K9/00—Screening of apparatus or components against electric or magnetic fields
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The application belongs to the technical field of scattering suppression, and in particular relates to a covering cap capable of suppressing gap scattering. The side face, close to a skin (2), of a cover (1) is provided with a first gap chamfer, the side face, close to the cover (1), of the cover (2) is provided with a second gap chamfer, a gap is formed between the first gap chamfer and the second gap chamfer, and a sealant (3) is filled in the gap; and the joint of the outer surfaces of the opening cover (1) and the skin (2) is provided with conductive paint (4). The technical scheme that this application formed can effectively restrain the electromagnetic scattering that the flap gap of aircraft arouses, reduces secondary scattering RCS, and it is significant to improving the comprehensive stealthy performance of aircraft.
Description
Technical Field
The application belongs to the technical field of scattering suppression, and in particular relates to a covering cap capable of suppressing gap scattering.
Background
In order to ensure the use and maintenance of the airplane, a large number of covering covers are arranged on the surface of the airplane during the design of the stealth airplane, so that the continuity of the skin on the surface of the airplane is influenced, and the surface quality of the airplane has an important influence on the stealth performance of the whole airplane. With the improvement of stealth performance requirements, harmful electromagnetic scattering can be generated on the surface gaps of the airplane due to design and manufacture of the airplane, so that the RCS of the whole airplane is increased, secondary scattering sources are changed into main scattering sources, and the RCS is controlled in the design and manufacture processes.
In order to ensure the surface quality of the airplane, the gap of the covering cap is required to be 0.5-1.0 mm according to the design control requirement of the gap on the surface of the airplane and the requirement of the sawtooth edge gap and the longitudinal gap of the covering cap. As the opening cover of the exposed part, when a gap between the edge of the opening cover and the interface of the airplane body meets a complex use environment, for example, the gap of the opening cover is exposed in salt spray air for a long time, skins in the gap and on two sides of the gap are seriously corroded, so that the electromagnetic defect on the surface is enlarged, the stealth performance is reduced, and the continuous high stealth capability of the whole life cycle of the airplane cannot be ensured.
The high stealth aircraft has high requirements on stealth performance, the continuity of an external skin of the aircraft is damaged by opening a large number of cover covers on the surface of the aircraft, the gap between the cover covers and the skin is enlarged in consideration of the difficulty in avoiding assembly errors in the aircraft manufacturing process, the influence of surface electromagnetic defects caused by a large number of cover gaps on the surface of the aircraft on the RCS of the whole aircraft cannot be ignored, and whether the aircraft can reach stealth indexes is directly influenced. The gaps of the airplane surface opening cover can generate surface electromagnetic defects, scattering cannot be eliminated, and the problems that the inhibition effect of secondary weak scattering sources caused by the surface electromagnetic defects such as airplane gaps is poor and the airplane surface electromagnetic continuity cannot be met are solved.
Disclosure of Invention
The invention provides a cover capable of inhibiting gap scattering, and the application scheme of the stealth material of the high stealth combat aircraft is adopted through the refined application design of an electromagnetic defect inhibition scheme.
This application can carry out the flap that restraines to the gap scattering the side that is close to the covering of flap is provided with first gap chamfer the side that is close to the flap of covering is provided with second gap chamfer, wherein, first gap chamfer and second gap chamfer are configured into:
the distance between the edge of the cover with the first gap chamfer and the edge of the skin with the second gap chamfer is smaller at the position close to the outer surfaces of the cover and the skin, and the distance between the edge of the cover with the first gap chamfer and the edge of the skin with the second gap chamfer is larger at the position close to the inner surfaces of the cover and the skin;
a gap is formed between the first gap chamfer and the second gap chamfer, and a sealant is filled in the gap;
and conductive paint is arranged at the joint of the outer surfaces of the opening cover and the skin.
Preferably, the first chamfered edge and the second chamfered edge are both provided with an anti-sticking agent.
Preferably, the chamfer of the first and second chamfered portions is set to 30 ° to 60 °.
Preferably, the chamfer of the first and second chamfered portions is set to 45 °.
Preferably, the starting position of the first chamfered edge at the side surface of the flap extends to a position after the outer surface of the flap extends to the inner surface by a set dimension, and the ending position of the first chamfered edge is the inner surface of the flap.
Preferably, the set size is 0.5 mm.
Preferably, the width of the conductive paint is 30mm on each side of the central line of the gap, the thickness of the conductive paint is 30-50 μm, and the electrical property of the conductive paint is that the resistance between any two points on the conductive paint with the interval of 30cm is not more than 1 omega.
This application provides effective technical approach for solving high stealth aircraft weak scattering source surface wave scattering suppression technical problem through the electromagnetic scattering suppression design to the flap gap.
The technical scheme that this application formed can effectively restrain the electromagnetic scattering that the flap gap of aircraft arouses, reduces secondary scattering RCS, and it is significant to improving the comprehensive stealthy performance of aircraft.
Drawings
Fig. 1 is a flow chart of a flap capable of suppressing gap scattering according to the present application.
The sealing structure comprises a sealing cover 1, a covering 2, a sealant 3, a conductive paint 4, an anti-sticking agent 5, a gap chamfer 6, a fastening piece 7 and a mouth frame 8.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application aims at the requirement of the full life cycle high stealth performance of the high stealth aircraft covering cap gap, combines the sawtooth design principle of the covering cap gap in order to reduce the influence of surface electromagnetic defects, and simultaneously considers the material mechanics, the environmental performance and the process realizability, and provides the covering cap gap restraining method which is convenient to operate and available for engineering. The technical measures of multilayer repair are innovatively adopted for the gap of the flap. Aiming at the inevitable gap of the opening cover, two layers of functional materials, namely a defect repairing layer and a conducting layer, are adopted, and the surface of a filling material needs to be subjected to conductive treatment, so that the electric continuity of the surface of the platform is realized.
This application can carry out the flap that suppresses to the gap scattering, as shown in figure 1, 2 division gaps of covering carry out the shutoff through flap 1, and flap 1 and covering 2 all fix on mouthful frame 8 through fastener 7.
The utility model provides a flap is provided with first gap chamfer in flap 1's the side that is close to covering 2 skin 2's the side that is close to covering 1 is provided with second gap chamfer, and the structure of gap chamfer 6 is shown in figure 1, and is the structure from flap or covering surface to the internal surface shrink, and is specific, first gap chamfer and second gap chamfer are configured into:
the distance between the edge of the flap 1 with the first gap chamfer and the edge of the skin 2 with the second gap chamfer is smaller near the outer surfaces of the flap 1 and the skin 2, and the distance between the edge of the flap 1 with the first gap chamfer and the edge of the skin 2 with the second gap chamfer is larger near the inner surfaces of the flap 1 and the skin 2;
a gap is formed between the first gap chamfer and the second gap chamfer, and a sealant 3 is filled in the gap;
and the conductive paint 4 is arranged at the joint of the outer surfaces of the opening cover 1 and the skin 2.
In this embodiment, the gap of the flap is filled with a sealant, such as sealant HM112B, and the gap of the flap is cleaned; injecting the sealant to the defect part by using a glue gun, wherein the filled sealant cannot have bubbles, bulges and gaps; and 2h later, polishing can be carried out, so that the thickness of the repaired position is consistent with the height of the original skin and the flap, and the method is used for realizing the physical continuity of the surface of the airplane.
In this embodiment, in order to ensure the electromagnetic performance of the surface of the aircraft, the exterior of the gap of the flap needs to be sprayed with a conductive paint for stealth surface treatment.
In some alternative embodiments, the first and second chamfered edges are each provided with an anti-adhesive agent 5. In this embodiment, the anti-sticking agent may be 7257 universal grease.
In some optional embodiments, the chamfer of the first and second slit chamfers is set to 30 ° to 60 °.
In some alternative embodiments, the initial position of the first chamfered portion at which the side surface of the flap 1 extends is a position after the outer surface of the flap 1 extends to the inner surface by a set dimension, and the final position of the first chamfered portion is the inner surface of the flap 1, and similarly, the initial position of the second chamfered portion at which the side surface of the skin 2 extends is a position after the outer surface of the skin 2 extends to the inner surface by a set dimension, and the final position of the second chamfered portion is the inner surface of the skin 2.
In some alternative embodiments, the dimension is set to 0.5 mm. In order to keep the sealant not easy to fall off after curing, chamfering design is carried out on the cover body and the skin at two sides of the cover gap, chamfering is started after 0.5mm inward from the outer surface of the skin, and the chamfering angle is 45 degrees.
In some alternative embodiments, the width of the conductive paint 4 is 30mm on each side of the center line of the gap, the thickness of the conductive paint 4 is 30 μm to 50 μm, and the electrical property of the conductive paint 4 is that the resistance between any two points on the conductive paint with the interval of 30cm is not more than 1 Ω.
This application is through carrying out the chamfer design to flap gap both sides edge to at chamfer both sides coating antiseized agent, then inside the flap gap, fill the sealant, outside the flap gap, the electrically conductive lacquer of spraying compromises stealthy and maintainability. The formed technical scheme can effectively inhibit electromagnetic scattering caused by a cover gap of the airplane, reduces secondary scattering RCS and has important significance for improving the comprehensive stealth performance of the airplane. The method for suppressing the scattering of the gap of the cover can be popularized to the design of stealth attack machines, stealth early warning machines and other stealth weaponry.
The RCS curves of the 1.0mm gap scattering inhibition front state and the 1.0mm gap scattering inhibition rear state are respectively measured, and the final test and verification result shows that the gap scattering inhibition is reduced by 4.5dB relative to the gap state in the forward direction, and the effect is obvious.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A flap capable of suppressing gap scattering, characterized in that a first gap chamfer is provided on the side of the flap (1) close to the skin (2), and a second gap chamfer is provided on the side of the skin (2) close to the flap (1), wherein the first and second gap chamfers are configured to:
the distance between the edge of the cover (1) with the first gap chamfer and the edge of the skin (2) with the second gap chamfer is smaller at the position close to the outer surfaces of the cover (1) and the skin (2), and the distance between the edge of the cover (1) with the first gap chamfer and the edge of the skin (2) with the second gap chamfer is larger at the position close to the inner surfaces of the cover (1) and the skin (2);
a gap is formed between the first gap chamfer and the second gap chamfer, and a sealant (3) is filled in the gap;
and the joint of the outer surfaces of the opening cover (1) and the skin (2) is provided with conductive paint (4).
2. A flap for suppressing gap scattering according to claim 1, characterized in that said first and second gap chamfers are provided with an anti-sticking agent (5).
3. A flap for suppressing the scattering of the slits according to claim 1, wherein the chamfers of said first and second slit chamfers are set at 30 ° to 60 °.
4. A flap for suppressing slot scattering according to claim 3, wherein the chamfers of said first slot chamfer and said second slot chamfer are set at 45 °.
5. A flap capable of suppressing gap scattering according to claim 1, characterized in that the initial position of the first gap chamfer at which the side of the flap (1) extends is a position after the outer surface of the flap (1) extends to the inner surface by a set dimension, and the terminal position of the first gap chamfer is the inner surface of the flap (1), and similarly, the initial position of the second gap chamfer at which the side of the skin (2) extends is a position after the outer surface of the skin (2) extends to the inner surface by a set dimension, and the terminal position of the second gap chamfer is the inner surface of the skin (2).
6. A flap for suppressing scattering in a gap according to claim 5, wherein said set size is 0.5 mm.
7. A port cover capable of suppressing gap scattering according to claim 1, wherein the width of the conductive paint (4) is 30mm on each side of the center line of the gap, the thickness of the conductive paint (4) is 30 μm to 50 μm, and the electrical property of the conductive paint (4) is such that the resistance between any two points on the conductive paint spaced 30cm apart is not more than 1 Ω.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011552869.9A CN112591072A (en) | 2020-12-24 | 2020-12-24 | Can carry out flap that suppresses to gap scattering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011552869.9A CN112591072A (en) | 2020-12-24 | 2020-12-24 | Can carry out flap that suppresses to gap scattering |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112591072A true CN112591072A (en) | 2021-04-02 |
Family
ID=75202365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011552869.9A Pending CN112591072A (en) | 2020-12-24 | 2020-12-24 | Can carry out flap that suppresses to gap scattering |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112591072A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0303102A2 (en) * | 1987-08-12 | 1989-02-15 | W.L. Gore & Associates GmbH | Sealing strip |
| US5126185A (en) * | 1987-12-30 | 1992-06-30 | W. L. Gore & Associates, Inc. | Conductive shielding and sealing tape |
| CN1551245A (en) * | 2003-05-12 | 2004-12-01 | Wireless communication inside shielded envelope | |
| CN204341407U (en) * | 2014-12-11 | 2015-05-20 | 石家庄飞机工业有限责任公司 | A kind of blimp integral tank inspection cover sealing arrangement |
| CN204775986U (en) * | 2015-06-23 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Airborne flap subassembly and have its aircraft |
| CN108238262A (en) * | 2017-12-08 | 2018-07-03 | 西安飞机工业（集团）有限责任公司 | A kind of sealing structure of nacelle of airplane lid |
-
2020
- 2020-12-24 CN CN202011552869.9A patent/CN112591072A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0303102A2 (en) * | 1987-08-12 | 1989-02-15 | W.L. Gore & Associates GmbH | Sealing strip |
| US5126185A (en) * | 1987-12-30 | 1992-06-30 | W. L. Gore & Associates, Inc. | Conductive shielding and sealing tape |
| CN1551245A (en) * | 2003-05-12 | 2004-12-01 | Wireless communication inside shielded envelope | |
| CN204341407U (en) * | 2014-12-11 | 2015-05-20 | 石家庄飞机工业有限责任公司 | A kind of blimp integral tank inspection cover sealing arrangement |
| CN204775986U (en) * | 2015-06-23 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Airborne flap subassembly and have its aircraft |
| CN108238262A (en) * | 2017-12-08 | 2018-07-03 | 西安飞机工业（集团）有限责任公司 | A kind of sealing structure of nacelle of airplane lid |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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Application publication date: 20210402 |