Composite material combined layer wallboard structure suitable for combined connection of wings

Abstract

A composite material combined layer wall plate structure suitable for combined connection of wings comprises a main box section skin and a plurality of reinforcing ribs which are integrally cured and formed, the front edge and the rear edge of the main box section skin are sequentially provided with recesses, and a front sunken edge for lap joint of the front edge skin and a rear sunken edge for lap joint of the rear edge skin are formed; a front beam reinforcing rib used for being connected with a front spar web is fixedly arranged at the bottom of the transition area of the front sunken edge and the main box section skin body, and a rear beam reinforcing rib used for being connected with a rear spar web is fixedly arranged at the bottom of the transition area of the rear sunken edge and the main box section skin body. The connecting mode of the wall plate and a related structure is simplified, the number of parts is reduced, the assembling efficiency can be improved, and dismounting, replacing and maintaining of an airplane in the using and maintaining process are facilitated.

Description

Technical Field

[0001] The invention relates to the field of aviation structure design, in particular to a composite material combined layer wall panel structure suitable for wing combined connection. Background Art

[0002] In order to reduce weight and improve structural load-bearing efficiency, modern aircraft structures generally use composite materials to manufacture wing panel structures. Aircraft wings are generally box-shaped structures that conform to the aerodynamic shape and are hollow inside. Except for some special aircraft that are used once, conventional aircraft wings usually include components such as the main box section, leading edge and trailing edge, taking into account the assembly process and the need for maintenance and replacement for long-term use. The main box section includes upper and lower panels, front beams, rear beams and wing ribs. In order to increase the structural rigidity, a reinforcing rib structure is usually provided between the upper and lower panels. In order to ensure the connection strength, facilitate the disassembly and assembly of the leading and trailing edges, and ensure the smoothness of the wing aerodynamic shape, the main box section panel forms a more complex connection relationship with the adjacent structure.

[0003] In the prior art, the main box section wall panels and wing beams of small and medium-sized aircraft are connected by permanent fasteners, and the joints connecting the wing and the fuselage are generally set at the root of the wing beam. The wall panels extend a certain width outside the main box section and are connected to the leading edge structure by detachable fasteners. Figure 1 As shown in the figure, one connection form is to connect the main box section wall panel b and the leading edge skin c through a strip plate a. The main box section is connected by a C-section beam e. The main box section wall panel b extends outward and is connected to the leading edge skin c through a transition of the strip plate a. The gaps at the skin joints are filled with sealant to form a smooth aerodynamic profile. This design form requires three rows of fasteners, which are used to connect the main box section wall panel b and the wing beam, the main box section wall panel b and the strip plate, and the strip plate and the leading edge skin. However, due to different stress states, the skin of the main box section wall panel b is generally thicker than the leading edge skin c (usually 2 to 3 times), so the strip plate a needs to form a step difference to compensate for the thickness difference of the skin on both sides of the main box section wall panel b, so as to ensure the smoothness of the aerodynamic shape. This steep step feature limits the selection of the strip plate, which can generally only be achieved by machining slender metal materials. The above connection form is relatively complex in structure, with a large number of parts and a large assembly workload, which to a certain extent limits large-scale mass production.

[0004] like Figure 2As shown, another connection form is to connect through an I-shaped spar f, and the spar flange f1 extends to both sides, respectively connecting the skin on one side of the main box section b and the skin on the leading edge side. This connection form omits the strip plate connection and reduces a row of fasteners. However, in order to compensate for the thickness difference between the main box section wall panel b and the leading edge skin c, a gasket d needs to be added to the mating surface of the I-shaped spar and the leading edge skin, and the number of parts is large. Since the I-shaped beam needs to cooperate with the skin with an airfoil curved surface, a closed angle g is formed between the flange on one side and the web, which can easily lead to difficulties in processing and demolding, and at the same time increase the manufacturing cost of the beam structure. Summary of the invention

[0005] In view of the shortcomings of the prior art mentioned above, the technical problem to be solved by the present invention is to provide a composite composite laminate wall panel structure suitable for wing assembly connection, so as to simplify the connection form between the components, reduce the number of parts, improve assembly efficiency, and facilitate disassembly and maintenance during aircraft use and maintenance.

[0006] The present invention proposes a composite composite laminate wall panel structure suitable for wing assembly connection, comprising a main box section skin and a plurality of reinforcing ribs that are integrally cured and formed, wherein the main box section skin is successively provided with depressions at the front edge and the rear edge to form a front sunken edge for overlapping the leading edge skin and a rear sunken edge for overlapping the trailing edge skin; a front beam reinforcing rib for connecting the front wing beam web is fixedly provided at the bottom of a transition area between the front sunken edge and the main box section skin body, and a rear beam reinforcing rib for connecting the rear wing beam web is fixedly provided at the bottom of a transition area between the rear sunken edge and the main box section skin body.

[0007] Preferably, the depression has a slope of 30° to 60°.

[0008] Preferably, the depth of the front sunken edge is equal to the thickness of the leading edge skin; the depth of the rear sunken edge is equal to the thickness of the trailing edge skin.

[0009] Preferably, the main box section skin includes an outer panel laminate and a main skin core layer, the outer panel laminate is coated on the top of the main skin core layer; the reinforcing ribs include a first laminate, and a plurality of the first laminates are coated on the bottom of the main skin core layer; the front beam reinforcement ribs include a first laminate and a second laminate, and the second laminate is adhered to the bottom of the front edge of the outer panel laminate and the adjacent first laminate; the rear beam reinforcement ribs include a first laminate and a third laminate, and the third laminate is adhered to the bottom of the rear edge of the outer panel laminate and the adjacent first laminate to form a wall panel laminate assembly.

[0010] Preferably, adjacent first plies form a U-shaped ply.

[0011] Preferably, the second ply and the third ply are both arranged in an L-shape.

[0012] Preferably, the lateral side of the second layer is attached to the bottom of the front edge of the outer panel layer, and the lateral side of the second layer is of the same thickness as the front edge of the outer panel layer; the longitudinal side of the second layer is attached to the adjacent first layer, and the longitudinal side of the second layer is of the same thickness as the adjacent first layer.

[0013] Preferably, the transverse side of the third layer is attached to the bottom of the rear edge of the outer panel layer, and the transverse side of the third layer is of equal thickness to the rear edge of the outer panel layer; the longitudinal side of the third layer is attached to the adjacent first layer, and the longitudinal side of the third layer is of equal thickness to the adjacent first layer.

[0014] Preferably, the wall panel ply assembly comprises at least a first partition, a second partition, a third partition and a fourth partition, and the first partition, the second partition, the third partition and the fourth partition are sequentially spliced ​​along the front edge to the rear edge; wherein, a layer dropping zone with an inclined surface is provided between adjacent partitions of the second partition, the third partition and the fourth partition, so that the ply thickness of the second partition, the third partition and the fourth partition decreases step by step.

[0015] Preferably, cavities are formed between the second ply and the adjacent first ply, between the third ply and the adjacent first ply, and at the roots between the adjacent first plies, and fillers are provided inside the cavities.

[0016] As described above, the present invention relates to a composite material combined laminate wall panel structure suitable for wing assembly connection, which has the following beneficial effects:

[0017] The present invention provides step-shaped depressions at the front and rear edges of the main box section skin to form a front sunken edge and a rear sunken edge, so that the front edge skin can be directly overlapped on the front sunken edge and the rear edge skin can be directly overlapped on the rear sunken edge. This avoids the conventional connection form based on a complex-shaped strip plate or gasket structure, reduces the number of parts, simplifies the connection structure, and is conducive to improving assembly and maintenance efficiency.

[0018] The present invention can provide sufficient support for the front sunken edge and the rear sunken edge by fixing a front beam reinforcement rib at the bottom of the main transition area between the front sunken edge and the main box section skin, and fix a rear beam reinforcement rib at the bottom of the main transition area between the rear sunken edge and the main box section skin, while compensating for the step difference in thickness between the front sunken edge and the rear sunken edge and the main box section skin, effectively improving the supporting stiffness of the front sunken edge and the rear sunken edge, and simplifying the connection form of the main box section skin and the wing beam structure.

[0019] The present invention divides the wall panel ply preform into a plurality of partitions that can be spliced ​​together. Each partition is spliced ​​in the form of a preform. The ply design of each partition takes into account that the overall structure has a uniform ply sequence and a complete ply decreasing transition. Thus, while realizing the overall geometric characteristics, the ply relationship inside the material is coordinated to ensure the mechanical properties of the parts, while improving the material utilization rate and the load-bearing efficiency of the structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the first configuration of the prior art;

[0021] Figure 2 It is a schematic diagram of the second configuration of the prior art;

[0022] Figure 3 A three-dimensional schematic diagram of a composite material composite laminate wall panel structure suitable for wing assembly connection provided by an embodiment of the present invention;

[0023] Figure 4 for Figure 3 Bottom view of

[0024] Figure 5 for Figure 3 Section AA of

[0025] Figure 6 for Figure 5 Partial magnification Figure Ⅰ ;

[0026] Figure 7 for Figure 5 Partial magnification Figure II ;

[0027] Figure 8 An assembly diagram of a composite material composite laminate wall panel structure suitable for wing assembly connection provided by an embodiment of the present invention;

[0028] Fig. 9 A schematic diagram of a composite material composite laminate wall panel structure suitable for wing assembly connection provided by an embodiment of the present invention;

[0029] Fig.10 for Fig. 9 A partial enlarged view of the first partition;

[0030] Fig.11 for Fig. 9 A partial enlarged view of the second partition;

[0031] Fig.12 for Fig. 9 A partial enlarged view of the third partition;

[0032] Fig.13 for Fig. 9A partial enlarged view of the fourth district;

[0033] Fig.14 An exploded view of a composite material composite laminate wall panel structure suitable for wing assembly connection provided by one embodiment of the present invention;

[0034] Fig.15 A schematic diagram of a wall panel layer of a composite material composite layer wall panel structure suitable for wing assembly connection provided by an embodiment of the present invention;

[0035] Fig.16 for Fig.15 The ply transition cross-section diagram BB;

[0036] Fig.17 for Fig.16 C-direction view.

[0037] Description of reference numerals:

[0038] a. Strip plate; b. Wall panel; c. Leading edge skin; d. Gasket; e. C-section beam; f. I-shaped spar; f1. Beam flange; g. Closed angle; 100. Main box section skin; 110. Front sunken edge; 120. Rear sunken edge; 130. Outer panel layup; 140. Main skin core layer; 200. Reinforcement rib; 210. First layup; 220. Filler; 300. Depression; 400. Leading edge skin; 500. Front spar web; 600. Front spar reinforcement rib; 610. Second layup; 700. Rear spar reinforcement rib; 710. Third layup; 800. Wall panel layup assembly; 810. First partition; 820. Second partition; 830. Third partition; 840. Fourth partition; 841. Missing layer area. DETAILED DESCRIPTION

[0039] The following is a description of the implementation of the present invention by means of specific embodiments. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification.

[0040] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no substantial technical significance. Any modification of the structure, change of the proportion relationship or adjustment of the size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention. At the same time, the terms such as "upper", "lower", "left", "right", "middle" and so on quoted in this specification are only for the convenience of description, and are not used to limit the scope of the implementation of the present invention. The change or adjustment of the relative relationship should also be regarded as the scope of the implementation of the present invention without substantially changing the technical content.

[0041] like Figure 1-Figure 8 An embodiment of a composite composite laminate wall panel structure suitable for wing assembly connection includes a main box section skin 100 and a plurality of reinforcing ribs 200 that are integrally cured and formed. The main box section skin 100 is provided with depressions 300 at the front edge and the rear edge in sequence, and the depression slope range is preferably but not limited to 30° to 60°. In this embodiment, the depression slope is preferably 45°. The depression 300 is arranged in a step-like shape as a whole to achieve thickness reduction, so as to form a front depression edge 110 for overlapping the leading edge skin 400 and a rear depression edge 120 for overlapping the trailing edge skin (not shown in the figure). The depression depth of the front depression edge 110 is equivalent to the thickness of the leading edge skin 400, and the depression depth of the rear depression edge 120 is equivalent to the thickness of the trailing edge skin. A front beam reinforcement rib 600 for connecting the front spar web 500 is fixedly arranged at the bottom of the transition area between the front sunken edge 110 and the main body of the main box section skin 100, and a rear beam reinforcement rib 700 for connecting the rear spar web (not shown in the figure) is fixedly arranged at the bottom of the transition area between the rear sunken edge 120 and the main body of the main box section skin. The mating surfaces of the front beam reinforcement rib 600 and the front spar web 500, and the rear beam reinforcement rib 700 and the rear spar web are set to be planes. The reinforcement rib 200 is fixed to the bottom of the main box section skin 100, and is evenly distributed between the front beam reinforcement rib 600 and the rear beam reinforcement rib 700. Among them, the reinforcement rib 200, the front beam reinforcement rib 600 and the rear beam reinforcement rib 700 are all arranged along the wing span direction, extending from one end of the main box section skin to the other end.

[0042] When installing the wing, the leading edge skin 400 is overlapped with the front sunken edge 110 and the trailing edge skin is overlapped with the rear sunken edge 120, and fixed by a detachable fastener, so that the wing as a whole forms a smooth aerodynamic profile. Due to the depression 300, a small gap is formed between the end of the leading edge skin 400 and the front sunken edge 110, and the gap amount is comparable to the thickness of the leading edge skin 400. A filler is provided inside the gap, and the filler includes but is not limited to sealant to ensure that the overall aerodynamic profile of the wing is smooth and flat. Similarly, for the gap formed by the trailing edge skin and the rear sunken edge, no further description is given here. The beam stiffener 600 is fitted with the front spar web 500, and the rear beam stiffener 700 is fitted with the rear spar web, and fixedly connected by permanent fasteners, and the permanent fasteners include but are not limited to rivets. This embodiment allows the leading edge skin and the trailing edge cover to be directly overlapped on the main box section skin 100, avoiding the use of indirect connectors such as gaskets or step-type belt plates to simplify the overall structure.

[0043] Furthermore, if Figure 6-Figure 8As shown, the depression depth of the depression 300 is equal to the thickness of the leading edge skin 400 and the trailing edge skin. In this embodiment, the depression depth of the depression 300, the thickness of the main box section skin 100, the thickness of the front beam reinforcement rib 600 and the thickness of the rear beam reinforcement rib 700 are preferably 0.8mm to 6mm, and the sum of the depression depth of the depression 300 and the thickness of the front beam reinforcement rib 600, and the sum of the depression depth of the depression 300 and the thickness of the rear beam reinforcement rib 700 are equal to the thickness of the main box section skin 100. Taking the overlap of the leading edge skin 400 as an example, the depression depth of the depression 300 is 2mm (equal to the thickness of the leading edge skin). According to the strength criterion, the thickness of the main box section skin 100 is preferably 5mm, and the thickness of the front beam reinforcement rib 600 is preferably 3mm. The method used for overlapping the trailing edge skin and the leading edge skin is the same, which will not be repeated here.

[0044] In one embodiment, if Figure 9-Figure 14 As shown, the main box section skin 100 includes an outer panel layer 130 and a main skin core layer 140. The main skin core layer 140 is used as the main layer, and the outer panel layer 130 is coated on the top. The front edge and the rear edge of the outer panel layer 130 are provided with the aforementioned recess 300 to form a sunken edge for overlapping the leading edge skin and the trailing edge skin. The reinforcing rib 200 includes a first layer 210, and a plurality of first layers 210 are coated on the bottom of the main skin core layer 140, which can provide sufficient support for the main skin core layer 100. The front beam reinforcement rib 600 includes a first ply 210 and a second ply 610, and the second ply 610 is attached to the bottom of the front edge of the outer panel ply 130 and the adjacent first ply 210; the rear beam reinforcement rib 700 includes a first ply 210 and a third ply 710, and the third ply 710 is attached to the bottom of the rear edge of the outer panel ply and the adjacent first ply 210, providing support for the outer panel ply 130 and the main skin core layer 140. The outer panel ply 130, the main skin core layer 140, the first plies 210 and the second ply 610 together form a wall panel ply assembly 800.

[0045] Furthermore, adjacent first plies 210 form a U-shaped ply, and the second ply 610 and the third ply 710 are both arranged in an L-shape. The horizontal side of the second ply 610 is attached to the bottom of the front edge of the outer panel ply, and the horizontal side of the second ply 610 is as thick as the front edge of the outer panel ply to form a symmetrical auxiliary layer. The longitudinal side (i.e., the web surface) of the second ply 610 is attached to the adjacent first ply 210, and the longitudinal side of the second ply is as thick as the adjacent first ply 210. The horizontal side of the third ply 710 is attached to the bottom of the rear edge of the outer panel ply, and the horizontal side of the third ply 710 is as thick as the rear edge of the outer panel ply. The longitudinal side of the third ply 710 is attached to the adjacent first ply 210, and the longitudinal side of the third ply 710 is as thick as the adjacent first ply 210 to form a symmetrical auxiliary layer. The horizontal edges of the second layer 610 and the third layer 710 form support and coverage for the edge depression area at the bonding surface to ensure compensation for the thickness and height difference in the area, and at the same time form a flat inner profile in the bonding area. The third layer and the first layer, and the second layer and the first layer are bonded, on the one hand, to provide sufficient support stiffness for the front and rear edges of the outer panel layer; on the other hand, they are also used to connect with the spar web to give full play to the utilization rate of materials.

[0046] In one embodiment, if Figure 10-13 As shown, the roots of the first ply 210, the second ply 610 and the third ply 710 are provided with fillets, and cavities are formed by reverse fillets between the second ply 610 and the adjacent first ply 210, between the third ply 710 and the adjacent first ply 210, and between the adjacent first plies 210, and inside the cavity is provided a filler 220 made of the same material as the main skin core layer, and the filler 220 includes but is not limited to twist strips to maintain the continuity and integrity of the main skin core layer material, thereby providing effective support for the fillet areas of the first ply 210, the second ply 610 and the third ply 710.

[0047] In one embodiment, if Figure 9-Figure 17 As shown, the wall panel ply assembly 800 includes at least a first partition 810, a second partition 820, a third partition 830 and a fourth partition 840. The first partition 810, the second partition 820, the third partition 830 and the fourth partition 840 are sequentially spliced ​​from the front edge to the rear edge, and each partition has a different thickness variation according to its own stress characteristics. Among them, a layer drop zone 841 with an inclined surface is provided between adjacent partitions of the second partition 820, the third partition 830 and the fourth partition 840, so that the ply thickness of the second partition 820, the third partition 830 and the fourth partition 840 decreases step by step, as shown in FIG. Fig.17As shown, the surface of the wall panel ply in the layer loss zone 841 forms a gentle slope. Among them, the first partition 810 is composed of the outer panel ply 130, the main skin core layer 140, the second ply 610 and the first ply 210; the second partition 820 and the third partition 830 are both composed of the outer panel ply 130, the main skin core layer 140 and the first ply 210; the fourth partition 840 is composed of the outer panel ply 130, the main skin core layer 140, the third ply 710 and the first ply 210. Each partition can form a preform according to the above corresponding ply, and then the preforms are combined and cured at one time to form a complete wall panel structure. It should be noted that the outer panel ply 130, the main skin core layer 140, the second ply 610, the first ply 210 and the third ply 710 all contain layer loss, and the layer loss is concentrated between the third partition 830 and the fourth partition 840.

[0048] Specifically, Fig.16 As shown, along the wing span direction, the number of layers of the outer panel 130 is preferably 8, the number of layers of the main skin core layer 140 is 24, the number of layers of the first layer 210 is 8, and the total number of layers of the three is 40. The layers at each position are coordinated through the layer drop zone 841 to form the same transition zone. Through the layer reduction transition, the number of layers of the outer panel 130 is reduced to 6, the number of layers of the main skin core layer 140 is reduced from 24 to 12, and the number of layers of the first layer 210 is reduced from 8 to 6. Through the unified layer sequence and complete layer reduction transition, the overall geometric characteristics are achieved while the layer relationship inside the material is coordinated to ensure the mechanical properties of the wall panel.

[0049] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A composite material composite laminate wall panel structure suitable for wing assembly connection, characterized in that: The invention comprises a main box section skin (100) and a plurality of reinforcing ribs (200) which are integrally solidified and formed, and is characterized in that the main box section skin (100) is provided with depressions (300) at the front edge and the rear edge in sequence, forming a front sunken edge (110) for overlapping the leading edge skin (400) and a rear sunken edge (120) for overlapping the trailing edge skin; a front beam reinforcing rib (600) for connecting the front wing beam web (500) is fixedly provided at the bottom of the transition area between the front sunken edge (110) and the main body of the main box section skin, and a rear beam reinforcing rib (700) for connecting the rear wing beam web is fixedly provided at the bottom of the transition area between the rear sunken edge (120) and the main body of the main box section skin.

2. The composite material composite laminate wall panel structure suitable for wing assembly connection according to claim 1, characterized in that: The depression (300) has a downward slope of 30° to 60°.

3. The composite material combined laminate wall panel structure suitable for wing assembly connection according to claim 2, characterized in that: The depression depth of the depression (300) is equal to the thickness of the leading edge skin (400) and the trailing edge skin.

4. The composite material combined laminate wall panel structure suitable for wing assembly connection according to claim 1, characterized in that: The main box section skin (100) includes an outer panel layer (130) and a main skin core layer (140), wherein the outer panel layer (130) is coated on the top of the main skin core layer (140); the reinforcing rib (200) includes a first layer (210), wherein a plurality of the first layers (210) are coated on the bottom of the main skin core layer (140); the front beam reinforcement rib (600) includes a first layer (210) and a second layer (610), wherein the second layer (610) is attached to the bottom of the front edge of the outer panel layer and the adjacent first layer (210); the rear beam reinforcement rib (700) includes a first layer (210) and a third layer (710), wherein the third layer (710) is attached to the bottom of the rear edge of the outer panel layer and the adjacent first layer (210), so as to form a wall panel layer assembly (800).

5. The composite material combined laminate wall panel structure suitable for wing assembly connection according to claim 4, characterized in that: Adjacent first plies (210) form a U-shaped ply.

6. The composite material combined laminate wall panel structure suitable for wing assembly connection according to claim 4 or 5, characterized in that: The second layer (610) and the third layer (710) are both arranged in an L shape.

7. The composite material composite laminate wall panel structure suitable for wing assembly connection according to claim 6, characterized in that: The transverse side of the second ply (610) is attached to the bottom of the front edge of the outer panel ply, and the transverse side of the second ply (610) is of equal thickness to the front edge of the outer panel ply; the longitudinal side of the second ply (610) is attached to the adjacent first ply (210), and the longitudinal side of the second ply is of equal thickness to the adjacent first ply (210).

8. The composite material composite laminate wall panel structure suitable for wing assembly connection according to claim 7, characterized in that: The transverse side of the third ply (710) is attached to the bottom of the rear edge of the outer panel ply, and the transverse side of the third ply (710) is of equal thickness to the rear edge of the outer panel ply; the longitudinal side of the third ply (710) is attached to the adjacent first ply (210), and the longitudinal side of the third ply (710) is of equal thickness to the adjacent first ply (210).

9. The composite material combined laminate wall panel structure suitable for wing assembly connection according to claim 4, characterized in that: The wall panel ply assembly (800) comprises at least a first partition (810), a second partition (820), a third partition (830) and a fourth partition (840), wherein the first partition (810), the second partition (820), the third partition (830) and the fourth partition (840) are sequentially spliced ​​from the front edge to the rear edge; wherein a layer dropping zone (841) with an inclined surface is provided between adjacent partitions of the second partition (820), the third partition (830) and the fourth partition (840), so that the ply thickness of the second partition (820), the third partition (830) and the fourth partition (840) decreases step by step.

10. The composite material composite laminate wall panel structure suitable for wing assembly connection according to any one of claims 4 to 9, characterized in that: A cavity is formed between the second ply (610) and the adjacent first ply (210), between the third ply (710) and the adjacent first ply (210), and at the root between the adjacent first plies (210), and a filler (220) is provided inside the cavity.

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