Sealing structure for cabin door or movable covering cap of airplane and airplane

Abstract

The invention relates to a sealing structure for an airplane cabin door or a movable covering cap and an airplane in the field of aviation, the sealing structure is used for sealing a gap between the cabin door or the movable covering cap and an airplane body, the sealing structure comprises a supporting piece, the supporting piece covers the gap, and the supporting piece is used for supporting the cabin door or the movable covering cap. One part of the supporting piece extends to the outer side of the cabin door or the movable opening cover, and the other part of the supporting piece extends to the outer side of the machine body; the wave absorbing layer covers at least one side of the supporting piece; the conductive part is connected to the side, facing the gap, of the wave absorbing layer or the supporting part, and the conductive part penetrates through the gap and extends to the inner side of the cabin door or the movable opening cover. The sealing structure not only has excellent stealth performance, but also is simple to mount, the cabin door or the movable covering cap does not need to be punched, the influence on the structural strength of the cabin door or the movable covering cap is reduced, the manufacturability is better, and the cost is lower.

Description

Technical Field

[0001] The present application relates to the aviation field, and in particular to a sealing structure for an aircraft cabin door or a movable cover and an aircraft. Background Art

[0002] In order to ensure that the aircraft doors and movable covers can be closed normally under the influence of the deformation of the fuselage caused by various load conditions of the aircraft, a certain gap between the doors and movable covers and the fuselage must be left during the design. These gaps have a great impact on the electromagnetic wave stealth performance of the aircraft. Therefore, the doors and movable covers need to be sealed. At present, the sealing structure of the aircraft is mostly made of carbon fiber composite materials. In view of the electromagnetic wave stealth requirements of the aircraft, the traditional sealing structure needs to add conductive layers and absorbing coatings, etc. At the same time, the rivets and bolts need to be specially treated during installation, which greatly increases the cost and maintenance. At the same time, the movable covers and doors need to be punched, which affects their structural strength. Summary of the invention

[0003] The main purpose of the present invention is to provide a sealing structure for an aircraft cabin door or a movable cover and an aircraft, aiming to solve at least one of the above-mentioned technical problems.

[0004] To achieve the above-mentioned purpose, the present invention proposes a sealing structure for an aircraft door or a movable cover, comprising: a support member, the support member covers the gap, a part of the support member extends to the outside of the door or the movable cover, and another part extends to the outside of the fuselage; an absorbing layer, the absorbing layer covers at least one side of the support member; and a conductive member, the conductive member is connected to the absorbing layer or the side of the support member facing the gap, and the conductive member passes through the gap and extends to the inside of the door or the movable cover.

[0005] In some embodiments of the present invention, the wave absorbing layer is provided on one side of the support member facing the hatch or the movable cover and one side of the support member away from the hatch or the movable cover.

[0006] In some embodiments of the present invention, the sealing structure further includes: a conductive layer, wherein the conductive layer covers a side of the conductive member away from the hatch or the movable cover.

[0007] In some embodiments of the present invention, the conductive layer extends to and covers the inner side of the absorbing layer or the supporting member at a position close to the fuselage.

[0008] In some embodiments of the present invention, the conductive layer is a conductive fabric or a conductive metal film.

[0009] In some embodiments of the present invention, the absorbing layer is made of a rubber-based electromagnetic absorbing material, and the conductive element is made of a conductive rubber material.

[0010] In some embodiments of the present invention, the material of the support member is selected from composite materials.

[0011] To achieve the above object, the present invention also proposes an aircraft, comprising the above sealing structure, a fuselage, a cabin door and a movable cover; the sealing structure is arranged between the cabin door and the fuselage or between the movable cover and the fuselage.

[0012] In some embodiments of the present invention, the sealing structure is adhered to the hatch or movable cover by adhesive.

[0013] In some embodiments of the present invention, the fuselage is formed with an annular protrusion at the opening where the door or movable cover is installed, the annular protrusion is close to the inner side of the fuselage, and the inner circle of the annular protrusion is staggered with the outer edge of the door or movable cover.

[0014] The present invention provides a sealing structure with integrated functions formed by a support member, an absorbing layer and a conductive member, and the cross-section of the sealing structure is approximately "J"-shaped as a whole. The sealing structure is installed on the edge of a door or a movable cover by bonding, and the part of the sealing structure close to the outer side of the fuselage serves as a movable end. The movable end applies a pre-tightening force to the fuselage when the door or the movable cover is closed, and the pre-tightening force is increased by the support member at the same time, so as to resist the aerodynamic suction generated by the high-speed flight of the aircraft and keep the overall structure of the aircraft flat. The absorbing layer plays a role in electromagnetic wave stealth, the conductive member realizes electrical continuity between the door or the movable cover and the fuselage, and the support member plays a role in enhancing the rigidity of the absorbing layer. While having excellent stealth performance, the sealing structure is easy to install, and there is no need to punch holes in the door or the movable cover, thereby reducing the influence on the structural strength of the door or the movable cover, achieving better processability and lower cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Also, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0016] Figure 1 It is a schematic diagram of the overall structure of the sealing structure of the present invention.

[0017] Figure 2 It is a schematic diagram of the installation of the sealing structure of the present invention.

[0018] Figure 3 It is a schematic diagram of the sealing structure of the present invention after the hatch or movable cover is closed.

[0019] The reference numerals in the accompanying drawings represent the following: 1. Absorbing layer; 2. Conductive member; 3. Support member; 4. Conductive layer; 5. Adhesive; 6. Door or movable cover; 7. Fuselage. DETAILED DESCRIPTION

[0020] It should be clear that the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0021] When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. Instead, they are only examples of devices and methods consistent with some aspects of the present application as detailed in the attached claims.

[0022] In the description of the present application, it should be understood that the terms "first", "second", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances. In addition, in the description of the present application, unless otherwise specified, "multiple" refers to two or more. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the objects associated before and after are in an "or" relationship.

[0023] The present invention discloses a sealing structure, such as Figure 1-3 As shown, the sealing structure is used to seal the gap between the door or movable cover 6 of the aircraft and the fuselage 7, and the sealing structure includes a support member 3, an absorbing layer 1 and a conductive member 2.

[0024] Among them, the support member 3 covers the gap, a part of the support member 3 extends to the outside of the hatch or movable cover 6, and the other part extends to the outside of the fuselage 7; the absorbing layer 1 covers at least one side of the support member 3; the conductive member 2 is connected to the absorbing layer 1 or the side of the support member 3 facing the gap, and the conductive member 2 passes through the gap and extends to the inside of the hatch or movable cover 6.

[0025] In the present invention, a functionally integrated sealing structure is formed by the support member 3, the absorbing layer 1 and the conductive member 2, and the cross-section of the sealing structure is approximately "J"-shaped as a whole. The sealing structure is installed on the edge of the door or movable cover 6 by bonding, and the part of the sealing structure close to the outer side of the fuselage 7 serves as the movable end. The movable end applies a preload force to the fuselage 7 when the door or movable cover 6 is closed, and the preload force is increased by the support member 3 to resist the aerodynamic suction generated by the high-speed flight of the aircraft and keep the overall structure of the aircraft flat. The absorbing layer 1 plays an electromagnetic wave stealth role, the conductive member 2 realizes the electrical continuity between the door or movable cover 6 and the fuselage 7, and the support member 3 plays a role in enhancing the rigidity of the absorbing layer 1. While having excellent stealth performance, the sealing structure is easy to install, and there is no need to punch holes in the door or movable cover 6, which reduces the impact on the structural strength of the door or movable cover 6, and has better processability and lower cost.

[0026] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the wave absorbing layer 1 is provided with one layer on the side of the support member 3 facing the hatch door or the movable cover 6 and the side away from the hatch door or the movable cover 6 respectively.

[0027] It should be understood that the support member 3 is embedded in the two spaced-apart absorbing layers 1, which can not only further improve the stealth performance, but also increase the rigidity of the absorbing layer 1, that is, the stability of the overall structure of the sealing structure.

[0028] It should be noted that, in other embodiments, the absorbing layer 1 can also be separately arranged on the side of the support member 3 facing the hatch or the movable cover 6, or separately arranged on the side of the support member 3 away from the hatch or the movable cover 6. Preferably, the absorbing layer 1 is arranged on both sides of the support member 3, that is, the support member 3 is embedded in the absorbing layer 1.

[0029] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the sealing structure further includes a conductive layer 4, which covers a side of the conductive member 2 away from the hatch or movable cover 6.

[0030] The conductive layer 4 is inside the sealing structure, that is, located on the inner side of the fuselage 7 after the hatch or movable cover 6 is closed. The conductive layer 4 and the conductive member 2 play the role of electrical continuity and can also protect the conductive member 2.

[0031] Furthermore, the conductive layer 4 extends to and covers the inner side of the absorbing layer 1 or the supporting member 3 near the fuselage 7 .

[0032] For example, when the absorbing layer 1 is separately arranged on the side of the support member 3 facing the hatch or the movable cover 6 or on both sides of the support member 3, the conductive layer 4 extends and covers the inner side of the absorbing layer 1 close to the fuselage 7; when the absorbing layer 1 is separately arranged on the side of the support member 3 away from the hatch or the movable cover 6, the conductive layer 4 extends and covers the inner side of the support member 3 close to the fuselage 7.

[0033] By covering the inner side of the sealing structure near the fuselage 7 with the conductive layer 4, wear and cracking of the edge of the sealing structure can be effectively avoided, thereby protecting the sealing structure and increasing the service life of the sealing structure.

[0034] Furthermore, the conductive layer 4 can be selected from conductive fabrics or conductive metal films, etc., and conductive fabrics are preferably used.

[0035] In some embodiments of the present invention, the absorbing layer 1 is made of a rubber-based electromagnetic absorbing material, and the conductive member 2 is made of a conductive rubber material.

[0036] The absorbent layer 1 and the conductive member 2 keep the raw rubber and the vulcanization system consistent, and at the same time, the support member 3 and the conductive member 2 are surface treated so that the sealing structure can be formed in one piece.

[0037] Furthermore, the material of the support member 3 is selected from composite materials, such as carbon fiber composite materials and the like.

[0038] In some embodiments of the present invention, Figure 2 and Figure 3 As shown, the sealing structure is thinned at the edge of the side away from the door or the movable cover 6, and a smooth transition is formed between the sealing structure and the fuselage 7 or the door or the movable cover 6 to reduce wind resistance.

[0039] Furthermore, after the hatch or movable cover 6 is stably buckled in the corresponding opening of the fuselage 7, the outer side of the hatch or movable cover 6 remains flush or approximately flush with the outer side of the fuselage 7 to further reduce wind resistance.

[0040] Furthermore, the portion of the sealing structure close to the fuselage 7 is bent a certain distance in the direction of the fuselage 7, so that after the hatch or movable cover 6 is stably buckled in the corresponding opening of the fuselage 7, the sealing structure applies a stronger pre-tightening force to the fuselage 7 at this point (movable end) to further improve the sealing effect of the sealing structure on the gap.

[0041] The present invention also discloses an aircraft, such as Figure 2 and Figure 3 As shown, the aircraft includes the above-mentioned sealing structure, a fuselage 7, a cabin door and a movable cover, wherein the sealing structure is arranged between the cabin door and the fuselage 7 or between the movable cover and the fuselage 7.

[0042] In some embodiments of the present invention, Figure 2 and Figure 3 As shown, the sealing structure is adhered to the hatch door or movable cover around the periphery by adhesive 5, that is, the adhesive 5 is applied to the inner side of the "J" shape of the sealing structure, and the "J" shape of the sealing structure bites the hatch door or movable cover around the periphery by adhesive 5.

[0043] The sealing structure is combined with the hatch or the movable cover by the adhesive 5, which not only ensures the installation stability of the sealing structure, but also avoids the drilling operation on the hatch or the movable cover, thereby ensuring the structural strength of the hatch or the movable cover.

[0044] Furthermore, the hatch door or movable cover is provided with chamfers or rounded corners at its edge corners near the inner side of the fuselage 7, so that when the hatch door or movable cover is closed, the extrusion damage to the sealing structure can be reduced, thereby further improving the protection of the sealing structure.

[0045] In some embodiments of the present invention, Figure 2 and Figure 3 As shown, the fuselage 7 is formed with an annular protrusion at the opening where the door or movable cover is installed. The annular protrusion is close to the inner side of the fuselage 7, and the inner circle of the annular protrusion is staggered with the outer edge of the door or movable cover.

[0046] The sealing structure is squeezed at the annular protrusion, and the sealing structure applies a pre-tightening force to the fuselage 7, and the two cooperate to form a more stable sealing effect.

[0047] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A sealing structure for sealing the gap between a door or a movable cover and a fuselage, characterized in that: The sealing structure comprises: A support member, the support member covers the gap, a portion of the support member extends to the outside of the door or the movable cover, and another portion of the support member extends to the outside of the fuselage; A wave absorbing layer, the wave absorbing layer covers at least one side of the support member; A conductive member, wherein the conductive member is connected to a side of the absorbing layer or the supporting member facing the gap, and the conductive member passes through the gap and extends to the inner side of the hatch or the movable cover.

2. The sealing structure according to claim 1, characterized in that: The wave absorbing layer is provided on one side of the support member facing the hatch or the movable cover and on one side away from the hatch or the movable cover.

3. The sealing structure according to claim 1, characterized in that: Also includes: A conductive layer covers a side of the conductive member away from the hatch or the movable cover.

4. The sealing structure according to claim 3, characterized in that: The conductive layer extends to and covers the inner side of the absorbing layer or the supporting member close to the fuselage.

5. The sealing structure according to claim 3, characterized in that: The conductive layer is conductive fabric or conductive metal film.

6. The sealing structure according to any one of claims 1 to 5, characterized in that: The wave absorbing layer is made of rubber-based electromagnetic wave absorbing material, and the conductive member is made of conductive rubber material.

7. The sealing structure according to any one of claims 1 to 5, characterized in that: The material of the support member is selected from composite materials.

8. An aircraft, characterized in that: It comprises a sealing structure as described in any one of claims 1 to 7, a fuselage, a hatch and a movable cover; the sealing structure is arranged between the hatch and the fuselage or between the movable cover and the fuselage.

9. The aircraft according to claim 8, characterized in that The sealing structure is adhered to the hatch or movable cover by adhesive.

10. The aircraft according to claim 8, characterized in that The fuselage is provided with the door Or an annular protrusion is formed at the opening of the movable cover, and the annular protrusion is close to the inner side of the fuselage, The inner circle of the annular protrusion is staggered with the outer edge of the hatch or the movable cover.

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