Seal structure for aircraft door or movable hatch and aircraft

Abstract

The application relates to a sealing structure for an aircraft cabin door or movable hatch and an aircraft, which is used for sealing the gap between the cabin door or movable hatch and the fuselage, and comprises a support member covering the gap, one part of the support member extending to the outside of the cabin door or movable hatch, and the other part extending to the outside of the fuselage; a wave-absorbing layer covering at least one side of the support member; and a conductive member connected to the side of the wave-absorbing layer or support member facing the gap, penetrating through the gap and extending to the inside of the cabin door or movable hatch. The sealing structure has excellent stealth performance, is simple to install, does not need to punch holes in the cabin door or movable hatch, reduces the influence on the structural strength of the cabin door or movable hatch, has better process performance, and is lower in cost.

Description

Technical Field

[0001] This application relates to the aviation field, and in particular to a sealing structure for aircraft doors or movable openings and an aircraft. Background Technology

[0002] To ensure that aircraft doors and hatches can close properly under various load conditions and fuselage deformation, a certain gap must be maintained between the doors / hatches and the fuselage during the design phase. These gaps significantly impact the aircraft's electromagnetic stealth performance; therefore, the doors and hatches need to be sealed. Currently, most aircraft sealing structures use carbon fiber composite materials. However, to meet the electromagnetic stealth requirements of aircraft, traditional sealing structures require the addition of conductive layers and radar-absorbing coatings. Furthermore, special treatment is needed for rivets and bolts during installation, significantly increasing costs and maintenance complexity. Additionally, drilling is required for the hatches and hatches, affecting their structural strength. Summary of the Invention

[0003] The main objective of this invention is to provide a sealing structure for aircraft doors or movable openings and an aircraft, aiming to solve at least one of the aforementioned technical problems.

[0004] To achieve the above objectives, the present invention proposes a sealing structure for an aircraft door or movable hatch, comprising: a support member covering the gap, a portion of the support member extending to the outside of the door or movable hatch and another portion extending to the outside of the fuselage; a radar-absorbing layer covering at least one side of the support member; and a conductive member connected to the radar-absorbing layer or the side of the support member facing the gap, the conductive member passing through the gap and extending to the inside of the door or movable hatch.

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

[0006] In some embodiments of the present invention, the sealing structure further includes a conductive layer covering the conductive element on the side away from the hatch or movable cover.

[0007] In some embodiments of the present invention, the conductive layer extends and covers the inner side of the absorbing layer or support near 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 rubber-based electromagnetic absorbing material, and the conductive component is made of 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 objectives, the present invention also proposes an aircraft, including the aforementioned sealing structure, fuselage, cabin door, and movable hatch; the sealing structure is disposed between the cabin door and the fuselage or between the movable hatch and the fuselage.

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

[0013] In some embodiments of the present invention, the fuselage has an annular protrusion at the opening where the hatch or movable cover is installed, the annular protrusion being close to the inner side of the fuselage, and the inner ring of the annular protrusion intersecting with the outer edge of the hatch or movable cover.

[0014] This invention provides a functionally integrated sealing structure comprising a support component, a radar-absorbing layer, and a conductive component. The overall cross-section of the sealing structure is approximately "J"-shaped. The sealing structure is installed on the edge of a hatch or movable cover by adhesive bonding. The portion of the sealing structure near the outer side of the fuselage serves as the movable end. When the hatch or movable cover is closed, the movable end applies a pre-tightening force to the fuselage. This pre-tightening force is amplified by the support component to resist the aerodynamic suction generated by the aircraft's high-speed flight, maintaining the overall flatness of the aircraft structure. The radar-absorbing layer provides electromagnetic stealth, the conductive component ensures electrical continuity between the hatch or movable cover and the fuselage, and the support component enhances the rigidity of the radar-absorbing layer. While possessing excellent stealth performance, the sealing structure is simple to install, requiring no drilling into the hatch or movable cover, reducing the impact on the structural strength of the hatch or movable cover. It also offers good manufacturability and lower cost. Attached Figure Description

[0015] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

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

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

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

[0019] The labels in the attached diagram represent the following: 1. Absorbing layer; 2. Conductive component; 3. Support component; 4. Conductive layer; 5. Adhesive; 6. Door or movable hatch; 7. Fuselage. Detailed Implementation

[0020] It should be understood that the described embodiments are merely some, not all, of the embodiments in this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without inventive effort are within the scope of protection of this application.

[0021] In the following description, when referring to the accompanying drawings, the same numbers in different drawings denote the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0022] In the description of this application, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances. Furthermore, in the description of this application, unless otherwise stated, "multiple" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. The character " / " generally indicates that the preceding and following related objects are in an "or" relationship.

[0023] This invention discloses a sealing structure, such as Figure 1-3 As shown, the sealing structure is used to seal the gap between the aircraft's cabin door or movable hatch 6 and the fuselage 7. The sealing structure includes a support 3, a wave-absorbing layer 1, and a conductive element 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 another part extends to the outside of the fuselage 7; the radar-absorbing layer 1 covers at least one side of the support member 3; the conductive member 2 is connected to the side of the radar-absorbing layer 1 or 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 this invention, a functionally integrated sealing structure is formed by a support member 3, a radar-absorbing layer 1, and a conductive member 2. The cross-section of the sealing structure is approximately "J" shaped. The sealing structure is installed on the edge of the hatch or movable cover 6 by adhesive bonding. The part of the sealing structure near the outer side of the fuselage 7 serves as the movable end. When the hatch or movable cover 6 is closed, the movable end applies a pre-tightening force to the fuselage 7. At the same time, the support member 3 enhances this pre-tightening force to resist the aerodynamic suction generated by the high-speed flight of the aircraft and maintain the overall flatness of the aircraft structure. The radar-absorbing layer 1 provides electromagnetic stealth, the conductive member 2 ensures electrical continuity between the hatch or movable cover 6 and the fuselage 7, and the support member 3 enhances the rigidity of the radar-absorbing layer 1. While possessing excellent stealth performance, the sealing structure is easy to install, requiring no drilling of the hatch or movable cover 6, reducing the impact on the structural strength of the hatch or movable cover 6, achieving good manufacturability, and lower cost.

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

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

[0028] It should be noted that in other embodiments, the absorbing layer 1 may be disposed separately on the side of the support member 3 facing the hatch or the movable cover 6, or separately on the side of the support member 3 away from the hatch or the movable cover 6. Preferably, the absorbing layer 1 is disposed 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, such as Figure 1 and Figure 2 As shown, the sealing structure also includes a conductive layer 4, which covers the conductive component 2 on the side away from the hatch or movable cover 6.

[0030] The conductive layer 4 is located inside the sealing structure, that is, inside the fuselage 7 after the hatch or movable opening cover 6 is closed. The conductive layer 4 and the conductive component 2 work together to maintain electrical continuity, and at the same time, they can also protect the conductive component 2.

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

[0032] For example, when the absorbing layer 1 is disposed alone on the side of the support member 3 facing the cabin door 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 near the fuselage 7; when the absorbing layer 1 is disposed alone on the side of the support member 3 away from the cabin door or the movable cover 6, the conductive layer 4 extends and covers the inner side of the support member 3 near the fuselage 7.

[0033] By covering the inner side of the sealing structure near the body 7 with the conductive layer 4, wear and cracking of the sealing structure edges can be effectively prevented, thus protecting the sealing structure and improving its service life.

[0034] Furthermore, the conductive layer 4 can be selected from conductive fabrics or conductive metal films, with conductive fabrics being preferred.

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

[0036] The absorbing layer 1 and the conductive component 2 maintain consistency between the raw rubber and the vulcanization system. At the same time, by surface treatment of the support component 3 and the conductive component 2, the sealing structure can be integrally formed.

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

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

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

[0040] Furthermore, the portion of the sealing structure near the fuselage 7 is bent a certain distance toward the fuselage 7, so that after the hatch or movable cover 6 is stably fastened to the corresponding opening of the fuselage 7, the sealing structure applies a stronger pre-tightening force to the fuselage 7 at that point (moving 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 aforementioned sealing structure, fuselage 7, cabin door, and movable hatch, wherein the sealing structure is located between the cabin door and fuselage 7 or between the movable hatch and fuselage 7.

[0042] In some embodiments of the present invention, such as Figure 2 and Figure 3 As shown, the sealing structure is attached to the hatch or movable opening cover by adhesive 5. That is, adhesive 5 is applied to the inside of the "J" shape of the sealing structure, and the "J" shape of the sealing structure is locked in place by adhesive 5 around the hatch or movable opening cover.

[0043] By using adhesive 5 to combine the sealing structure with the hatch or movable cover, the installation stability of the sealing structure is ensured, and the drilling operation of the hatch or movable cover is avoided, thus ensuring the structural strength of the hatch or movable cover.

[0044] Furthermore, the hatch or movable cover has chamfered or rounded corners at its edges on the inner side of the fuselage 7, which reduces the squeezing damage to the sealing structure when the hatch or movable cover is closed, and further enhances the protection of the sealing structure.

[0045] In some embodiments of the present invention, such as Figure 2 and Figure 3 As shown, the fuselage 7 has an annular protrusion at the opening where the hatch or movable cover is installed. The annular protrusion is close to the inner side of the fuselage 7, and the inner ring of the annular protrusion intersects with the outer edge of the hatch or movable cover.

[0046] The sealing structure is compressed at the annular protrusion, and together with the pre-tightening force applied to the fuselage 7 by the sealing structure, the two work together to form a more stable sealing effect.

[0047] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A sealing structure for sealing the gap between a hatch or movable cover and the fuselage, characterized in that, The sealing structure includes: A support member that covers the gap, a portion of which extends to the outside of the hatch or movable opening cover, and another portion of which extends to the outside of the fuselage; A wave-absorbing layer, the wave-absorbing layer covering at least one side of the support member; A conductive element is connected to the side of the absorbing layer or support facing the gap, and the conductive element passes through the gap and extends to the inside of the hatch or movable cover.

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

3. The sealing structure according to claim 1, characterized in that, Also includes: A conductive layer covering the conductive element on the side away from the hatch or movable cover.

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

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

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

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

8. An aircraft, characterized in that, Includes a sealing structure, fuselage, hatch, and movable hatch as described in any one of claims 1-7; the sealing structure is disposed between the hatch and the fuselage or between the movable hatch and the fuselage.

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

10. The aircraft according to claim 8, characterized in that, The fuselage is where the hatch is installed. Alternatively, the opening of the movable cover may have an annular protrusion, which is located near the inner side of the body. The inner ring of the annular protrusion intersects with the outer edge of the hatch or movable cover.

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