阅读说明：本技术 一种能够对缝隙散射进行抑制的口盖 (Can carry out flap that suppresses to gap scattering ) 是由 李君哲 刘德力 姜浩 于 2020-12-24 设计创作，主要内容包括：本申请属于散射抑制技术领域,特别涉及一种能够对缝隙散射进行抑制的口盖。本申请在口盖(1)的靠近蒙皮(2)的侧面设置有第一缝隙倒棱,在所述蒙皮(2)的靠近口盖(1)的侧面设置有第二缝隙倒棱,所述第一缝隙倒棱与所述第二缝隙倒棱之间形成缝隙,所述缝隙内填充有密封剂(3)；所口盖(1)及蒙皮(2)的外表面的交接处设置有导电漆(4)。本申请形成的技术方案可以有效抑制飞机的口盖缝隙所引起的电磁散射,降低次级散射RCS,对于提高飞机综合隐身性能具有重要意义。(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.)

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.

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.