Flexible sealing structure between main wing box and control surface of aircraft wing

Abstract

The invention belongs to the technical field of design of a sealing structure between a main wing box and a control surface of an aircraft wing, and particularly relates to a flexible sealing structure between the main wing box and the control surface of the aircraft wing, which comprises a rubber layer and a reinforcing skeleton embedded in the rubber layer, the reinforcing frameworks are distributed in the thickness direction of the rubber layer, and the adjacent reinforcing frameworks are connected through bolts; the reinforced skeleton comprises two boundary beams and a corrugated skeleton, and the two boundary beams are arranged in the chordwise direction of the wing; the multiple sets of corrugated frameworks are distributed in the spanwise direction of the wing, and the two ends of the corrugated frameworks are connected to the two boundary beams.

Description

Technical Field

[0001] This application belongs to the technical field of sealing structure design between the main wing box and the control surface of an aircraft wing, specifically relating to a flexible sealing structure between the main wing box and the control surface of an aircraft wing. Background Technology

[0002] A flexible sealing structure between the main wing box and the control surface of an aircraft wing is used to seal the connection between the main wing box and the control surface.

[0003] Currently, the flexible sealing structure between the main wing box and the control surface of aircraft mostly adopts single-sided fixation, and the other side is overlapped with the control surface by applying preload to ensure sealing. This technical solution has the following drawbacks:

[0004] It is difficult to reconcile the contradiction between deformation and load-bearing capacity. Under long-term motion and aerodynamic loads, it is prone to damage or irreversible deformation, requiring regular replacement and limiting the aircraft's availability.

[0005] Using a single rubber or metal plate results in a weak ability to absorb electromagnetic waves.

[0006] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0007] The purpose of this application is to provide a flexible sealing structure between the main wing box and the control surface of an aircraft wing to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A flexible sealing structure between the main wing box and the control surface of an aircraft wing includes a rubber layer and a reinforcing skeleton embedded in the rubber layer;

[0010] There are multiple reinforcing skeletons, distributed along the thickness direction of the rubber layer, and adjacent reinforcing skeletons are connected by bolts;

[0011] The reinforcing frame includes side spars and corrugated frames. There are two side spars arranged along the chord of the wing; there are multiple sets of corrugated frames distributed along the span of the wing, with both ends connected to the two side spars.

[0012] The two ends of the corrugated frame are connected to the protruding parts set on the inner side of the two side beams;

[0013] The corrugated skeleton adopts a double-layer rectangular corrugated skeleton. The double-layer rectangular corrugated skeleton is connected by connecting blocks set between the two side edges. The edge of the corrugated skeleton on the top inner side protrudes inward, and the top of the protrusion is connected to the ring with a short rod. The corresponding rings of adjacent reinforcing skeletons are connected by bolts.

[0014] According to at least one embodiment of this application, in the flexible sealing structure between the main wing box and the control surface of the aircraft wing described above, the rubber layer is a Tecnoflon rubber layer.

[0015] According to at least one embodiment of this application, in the flexible sealing structure between the main wing box and the control surface of the aircraft wing described above, wave-absorbing particles are embedded in the rubber layer.

[0016] According to at least one embodiment of this application, in the flexible sealing structure between the main wing box and the control surface of the aircraft wing described above, the wave-absorbing particles are carbonyl iron / ferrite particles.

[0017] According to at least one embodiment of this application, in the flexible sealing structure between the main wing box and the control surface of the aircraft wing described above, the reinforcing skeleton is a metal or composite material reinforcing skeleton with zero Poisson's ratio.

[0018] According to at least one embodiment of this application, in the above-described flexible sealing structure between the main wing box and the control surface of the aircraft wing, the reinforcing skeleton is prepared by machining or additive manufacturing.

[0019] According to at least one embodiment of this application, in the above-mentioned flexible sealing structure between the main wing box and the control surface of the aircraft wing, the inward protrusion of the edge of the corrugated skeleton on the inner side of the top of the double-layer rectangular corrugated rib is a rectangular protrusion. Attached Figure Description

[0020] Figure 1 This is a schematic diagram illustrating the application of the flexible sealing structure between the main wing box and the control surface of an aircraft wing provided in this application embodiment;

[0021] Figure 2 This is a schematic diagram of the construction of the flexible sealing structure between the main wing box and the control surface of an aircraft wing provided in the embodiments of this application;

[0022] Figure 3 This is a schematic diagram of the reinforced skeleton provided in an embodiment of this application;

[0023] Figure 4 This is a schematic diagram of the corrugated skeleton unit provided in an embodiment of this application;

[0024] in:

[0025] 1-Rubber layer; 2-Reinforcing skeleton; 3-Wave absorbing particles;

[0026] 21-Side beam; 22-Corrugated skeleton.

[0027] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0028] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0029] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0030] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0031] A flexible sealing structure between the main wing box and the control surface of an aircraft wing is connected to the upper and lower surfaces of the connection area between the main wing box and the control surface, forming the aerodynamic shape of the connection area. It is fixed chordally to the main wing box and the control surface on both sides, such as... Figure 1 As shown, this is a flexible skin sealing structure that is fixed on both sides and has electromagnetic wave absorption capabilities, which can overcome the problems of insufficient load-bearing capacity, easy damage, and insufficient electromagnetic wave absorption capabilities of existing sealing structures.

[0032] The flexible sealing structure between the main wing box and the control surface of the aircraft wing includes a rubber layer 1 and a reinforcing skeleton 2 embedded in the rubber layer 1, such as... Figure 2 As shown.

[0033] Rubber layer 1 is made of a large deformation rubber material with certain high and low temperature resistance, such as Tecnoflon. It is the main sealing body of the flexible sealing structure. It can undergo smooth and continuous deformation when the control surface is actively deflected, so as to maintain the seal of the connection between the main wing box and the control surface.

[0034] Microwave-absorbing particles 3, such as carbonyl iron / ferrite particles, can be embedded in the rubber layer 1 to achieve good electromagnetic wave absorption capability.

[0035] The microwave absorbing particles 3 are distributed in the rubber layer 1 and can be prepared by mixing the microwave absorbing particles 3 with liquid rubber and then curing it.

[0036] The reinforcing skeleton 2 can be made of metal or composite materials and can be prepared by machining or additive manufacturing. It has high anisotropy and zero Poisson's ratio and is used to enhance the out-of-plane load-bearing capacity of the rubber layer 1 to ensure the load-bearing capacity of the flexible sealing structure.

[0037] There are multiple reinforcing skeletons 2, which are distributed along the thickness direction of the rubber layer 1, and adjacent reinforcing skeletons 2 are connected by bolts.

[0038] The reinforcing frame 2 includes side beams 21 and corrugated frame 22, such as Figure 3 As shown, there are two side beams 21 arranged along the chord of the wing; there are multiple sets of corrugated frame 22 distributed along the span of the wing, with both ends connected to the two side beams 21.

[0039] The two ends of the corrugated frame 22 are connected to the protruding parts set on the inner side of the two side beams 21.

[0040] The corrugated frame 22 adopts a double-layer rectangular corrugated frame to have a high load-bearing capacity, such as... Figure 4 As shown, the double-layer rectangular corrugated skeletons are connected by connecting blocks set between the two side edges, and the edge of the corrugated skeleton on the top inner side protrudes inward. This protrusion is a rectangular protrusion to reduce stress concentration. The top of the protrusion is connected to a ring with a short rod, and the corresponding rings of adjacent reinforcing skeletons 2 are connected by bolts.

[0041] The number of layers of the reinforcing frame 2, as well as the number of groups of the corrugated frame 22, the number of corrugations, and other relevant parameters, can be designed according to the size of the local aerodynamic load on the wing and the deflection angle requirements of the control surface to ensure structural rigidity and meet the load-bearing capacity requirements.

[0042] The flexible sealing structure between the main wing box and the control surface of the aircraft wing disclosed in the above embodiments has a completely seamless geometric feature. It does not require the application of pre-tightening force, is not prone to premature failure and damage, and can avoid irreversible plastic deformation. It has good durability and good stiffness adjustability, and can well meet the requirements of coordinated deformation and load bearing.

[0043] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A flexible sealing structure between the main wing box and the control surface of an aircraft wing, characterized in that, It includes a rubber layer (1) and a reinforcing skeleton (2) embedded in the rubber layer (1). There are multiple reinforcing skeletons (2), which are distributed along the thickness direction of the rubber layer (1); The reinforcing frame (2) includes side spars (21) and corrugated frame (22). There are two side spars (21) arranged along the chord of the wing; there are multiple sets of corrugated frame (22) distributed along the span of the wing. The two ends of the corrugated frame (22) are connected to the protruding parts set on the inner side of the two side beams (21); The corrugated skeleton (22) adopts a double-layer rectangular corrugated skeleton. The double-layer rectangular corrugated skeleton is connected by connecting blocks set between the two sides. The edge of the corrugated skeleton on the inner side of the top protrudes inward. The top of the protrusion is connected to the ring with a short rod. The corresponding rings of the adjacent reinforcing skeleton (2) are connected by bolts.

2. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 1, characterized in that, The rubber layer (1) is a Tecnoflon rubber layer.

3. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 2, characterized in that, Wave-absorbing particles (3) are embedded in the rubber layer (1).

4. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 3, characterized in that, The microwave absorbing particles (3) are carbonyl iron / ferrite particles.

5. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 4, characterized in that, The reinforcing skeleton (2) is a metal or composite material reinforcing skeleton with zero Poisson's ratio.

6. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 5, characterized in that, The reinforcing skeleton (2) is prepared by machining or additive manufacturing.

7. The flexible sealing structure between the main wing box and the control surface of an aircraft wing according to claim 6, characterized in that, The inner edge of the corrugated skeleton on the top of the double-layer rectangular corrugated skeleton protrudes inward, forming a rectangular protrusion.

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