Aircraft spar butt joint structure

Abstract

The invention belongs to the technical field of aircraft structure design, and discloses an aircraft spar butt joint structure which comprises an upper butt joint piece, a lower butt joint piece, an inner connecting piece and an outer connecting piece, one side of the upper butt joint piece is connected to an inner upper edge strip of an inner section spar and an outer upper edge strip of an outer section spar, and the other side of the upper butt joint piece is connected to a lower butt joint piece. One side of the upper butt joint piece is connected to an inner-section web of the inner-section spar, the other side of the upper butt joint piece is connected to an outer-section web of the outer-section spar, one side of the lower butt joint piece is connected to an inner lower edge strip of the inner-section spar and an outer lower edge strip of the outer-section spar, the other side of the lower butt joint piece is connected to the inner-section web and the outer-section web, the inner connecting piece is arranged on the inner-section web and the outer-section web, and one end of the inner connecting piece is connected to the upper butt joint piece. The outer connecting piece is installed on the side, away from the inner connecting piece, of the inner section spar and the side, away from the inner connecting piece, of the outer section spar and connected to the inner section web and the outer section web. Through the arrangement, the airplane spar butt joint structure can improve the sealing performance and the structural efficiency, reduce the assembly difficulty and avoid composite material failure under the condition that the structural strength is guaranteed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structure design, in particular to an aircraft wing beam butt joint structure. Background Art

[0002] The wing spar structure of the composite wing of civil aircraft is an important longitudinal load-bearing member. Usually, the spar needs to bear the bending moment and shear force of the wing surface structure, and together with the closed chamber composed of the wall panels, it bears the torque of the wing box and the oil pressure of the fuel tank. At the same time, it can provide installation support for structures such as movable surfaces, suspensions, and landing gear.

[0003] The length of the wing is usually long. Considering the strength of composite materials, manufacturing capabilities, assembly and other factors, the wing spar will be segmented in specific areas. Regarding the segmented wing spar docking, the current existing wing spar docking connection form mainly exists in the metal wing spar or wing root area, and the wing spar docking is achieved by designing multiple joints such as beam web docking and edge strip docking. Given that the wing spar docking point is located in the key area of ​​the box section, and the different structural forms and functions of each component, the relevant design has certain limitations.

[0004] After the outer wing of the aircraft adopts a composite material structure, due to the properties of the composite material itself, the opening sensitivity is poor, and stress concentration is easy to occur in the docking area, making it difficult for the structural strength to meet the operational requirements and prone to composite material failure. At the same time, compared with metal wing spars, due to the instability of the composite material manufacturing process, it is difficult to control the manufacturing and assembly accuracy, resulting in the composite wing spar connection structure (such as the use of the metal wing spar structure connection style), which will increase the precision requirements of the docking joint, causing difficulties in manufacturing and assembly, reduced fatigue life, corrosion, poor sealing and low structural efficiency. Therefore, it poses a huge challenge to the design of the outer wing spar docking area. Summary of the invention

[0005] The object of the present invention is to provide an aircraft wing beam butt joint structure, which can improve the sealing performance and structural efficiency, reduce the difficulty of assembly and avoid composite material failure while ensuring the structural strength.

[0006] To achieve this object, the present invention adopts the following technical solutions:

[0007] An aircraft wing spar butt joint structure, used for butt jointing an inner wing spar and an outer wing spar along a first direction, comprising:

[0008] An upper butt joint, one side of which is connected to the inner upper edge strip of the inner spar and the outer upper edge strip of the outer spar, and the other side of which is connected to the inner web of the inner spar and the outer web of the outer spar;

[0009] A lower butt joint, one side of which is connected to the inner lower edge strip of the inner section spar and the outer lower edge strip of the outer section spar, and the other side of which is connected to the inner section web plate and the outer section web plate;

[0010] An inner connecting member, disposed on the inner section web and the outer section web, with one end connected to the upper docking member and the other end connected to the lower docking member;

[0011] An outer connecting member is installed on a side of the inner section spar and the outer section spar away from the inner connecting member, and is connected to the inner section web and the outer section web.

[0012] Optionally, the upper docking member includes an upper docking edge strip and an upper docking web connected to each other, the upper docking edge strip is connected to the inner upper edge strip and the outer upper edge strip, and the upper docking web is connected to the inner section web and the outer section web; the lower docking member includes a lower docking edge strip and a lower docking web connected to each other, the lower docking edge strip is connected to the inner lower edge strip and the outer lower edge strip, and the lower docking web is connected to the inner section web and the outer section web; the cross-sections of the upper docking member and the lower docking member along the first direction are both L-shaped.

[0013] Optionally, the thickness of the upper butt joint edge strip and the lower butt joint edge strip gradually decreases from the middle to both ends.

[0014] Optionally, the inner connecting member includes an inner connecting edge strip extending along the second direction, the two ends of the inner connecting edge strip are respectively fitted and connected to the upper docking member and the lower docking member, the middle part is fitted and connected to the inner section web and the outer section web, and the second direction is set at an angle to the first direction.

[0015] Optionally, the inner connecting member further comprises an inner connecting web extending along the second direction, the inner connecting web is arranged at an angle with the inner connecting edge strip, the inner connecting web is used to connect the ribs, and the cross-section of the inner connecting member along the second direction is T-shaped.

[0016] Optionally, the external connecting member is a flat plate, which is fitted and connected to the inner section web and the outer section web, and the two ends of the flat plate along the second direction gradually narrow toward the middle, and the outer edges of the two ends along the first direction are concave, and the second direction is set at an angle to the first direction.

[0017] Optionally, the external connecting member includes an external connecting web and two external connecting edge strips, the external connecting web is fitly connected to the inner section web and the outer section web, the two external connecting edge strips are respectively arranged at angles on both sides of the external connecting web for connecting the wing wall panel, and the cross-section of the external connecting member along the first direction is C-shaped.

[0018] Optionally, the external connection member further includes a plurality of reinforcing ribs, and the reinforcing ribs are extended along the second direction and arranged on the external connection web, and two ends of the reinforcing ribs are respectively connected to the opposite sides of the two external connection edge strips.

[0019] Optionally, a recessed area is provided on a side of the inner connecting member facing away from the inner section web and the outer section web.

[0020] Optionally, the thickness of the external connecting member gradually decreases from the middle to both ends.

[0021] Beneficial effects:

[0022] The aircraft wing spar docking structure provided by the present invention is used for docking the inner section wing spar and the outer section wing spar along a first direction, and the aircraft wing spar docking structure includes an upper docking piece, a lower docking piece, an inner connecting piece and an outer connecting piece. One side of the upper docking piece is connected to the inner upper edge strip of the inner section wing spar and the outer upper edge strip of the outer section wing spar, and the other side is connected to the inner section web of the inner section wing spar and the outer section web of the outer section wing spar. One side of the lower docking piece is connected to the inner lower edge strip of the inner section wing spar and the outer lower edge strip of the outer section wing spar, and the other side is connected to the inner section web and the outer section web. For the connection area of ​​the inner section wing spar and the outer section wing spar, the present invention can ensure the connection strength between the edge strip and the web of the corresponding wing spar by arranging the upper docking piece and the lower docking piece, so that the structure is more stable and safe, and the failure of the composite material is avoided. At the same time, the sealing of the wing spar docking is also improved. By setting the inner connecting piece on the inner web and the outer web, one end is connected to the upper docking piece, and the other end is connected to the lower docking piece. The outer connecting piece is installed on the side of the inner wing beam and the outer wing beam away from the inner connecting piece, and is connected to the inner web and the outer web, so that the inner connecting piece and the outer connecting piece are used in combination and cooperate with each other, thereby improving the bearing capacity of the web in the docking area of ​​the wing beam. Compared with the previous metal wing beam structure connection method, the manufacturing and assembly of the above-mentioned components are simpler and more convenient. Moreover, by separately setting the external connecting piece on the outer side of the wing beam, not only the structural connection strength is further improved, but also the component structure is simplified, the structural weight is reduced, and it is beneficial to improve the structural efficiency. Through the mutual cooperation of the upper docking piece, the lower docking piece and the inner connecting piece, the integrity of the inner structure in the docking area of ​​the wing beam can also be guaranteed, and the sealing is further improved. Through the above-mentioned arrangement, the aircraft wing beam docking structure provided by the present invention can improve the sealing and structural efficiency while ensuring the structural strength, reduce the difficulty of assembly, and avoid the failure of composite materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic diagram of the connection between the inner wing spar and the outer wing spar provided by an embodiment of the present invention;

[0024] Figure 2 Schematic diagram of an aircraft wing beam docking mechanism provided by an embodiment of the present invention Figure 1 ;

[0025] Figure 3 Schematic diagram of an aircraft wing beam docking mechanism provided by an embodiment of the present invention Figure 2 ;

[0026] Figure 4 is a schematic diagram of the installation of the upper docking member provided by an embodiment of the present invention;

[0027] Figure 5 is a schematic diagram of the installation of the lower docking member provided by an embodiment of the present invention;

[0028] Figure 6 is a schematic diagram of the installation of the inner connecting member provided in an embodiment of the present invention;

[0029] Figure 7 is a schematic diagram of an upper docking member provided by an embodiment of the present invention;

[0030] Figure 8 is a schematic diagram of a lower docking member provided by an embodiment of the present invention;

[0031] Fig. 9 is a schematic diagram of an inner connecting member provided by an embodiment of the present invention;

[0032] Fig.10 Schematic diagram of an external connection member provided in an embodiment of the present invention Figure 1 ;

[0033] Fig.11 Schematic diagram of an external connection member provided in an embodiment of the present invention Figure 2 ;

[0034] Fig.12 is a schematic diagram of another external connection member provided by an embodiment of the present invention Figure 1 ;

[0035] Fig.13 is a schematic diagram of another external connection member provided by an embodiment of the present invention Figure 2 .

[0036] In the figure:

[0037] 1. Upper butt joint; 11. Upper butt flange; 12. Upper butt web;

[0038] 2. Lower docking piece; 21. Lower docking edge strip; 22. Lower docking web;

[0039] 3. Internal connecting piece; 31. Internal connecting edge strip; 32. Internal connecting web;

[0040] 4. External connection member; 41. External connection web; 42. External connection flange; 43. Reinforcement rib;

[0041] 100, inner spar; 101, inner upper edge strip; 102, inner web; 103, inner lower edge strip;

[0042] 200, outer wing spar; 201, outer upper edge strip; 202, outer web; 203, outer lower edge strip. DETAILED DESCRIPTION

[0043] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0044] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral 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, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0045] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0046] In the description of this embodiment, the terms "upper", "lower", "right", etc., directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0047] In aircraft structure, wing spar refers to the longitudinal member in the wing surface that mainly bears bending moment and shear force. The existing wing spar structure is often made of composite materials, which has the advantages of high strength, light weight and corrosion resistance. Among them, aircraft composite C-type wing spar has a wide range of applications, such as Figure 1As shown, the aircraft composite C-shaped wing beam is specifically composed of an upper beam edge bar, a beam web and a beam lower beam edge bar. The upper beam edge bar and the lower beam edge bar are respectively connected to the two sides of the beam web, and make the cross-section C-shaped. According to the distance from the central wing, the wing beam can be divided into an inner section wing beam 100 and an outer section wing beam 200. The C-shaped opening direction is the inner side of the wing beam, and the direction away from the C-shaped opening is the outer side of the wing beam.

[0048] In addition, the wing spar will be segmented in specific areas to meet actual operation requirements. In view of the segmented docking of the aircraft composite C-type wing spar, this embodiment proposes an aircraft wing spar docking structure for docking the inner wing spar 100 and the outer wing spar 200 along a first direction. Figure 2 As shown, the inner spar 100 and the outer spar 200 are both made of carbon fiber reinforced composite materials. The inner spar 100 includes an inner upper edge strip 101, an inner web 102 and an inner lower edge strip 103. The inner upper edge strip 101 and the inner lower edge strip 103 are arranged opposite to each other and spaced apart. The inner web 102 is connected between the inner upper edge strip 101 and the inner lower edge strip 103, so that the cross section of the inner spar 100 is C-shaped; the outer spar 200 includes an outer upper edge strip 201, an outer web 202 and an outer lower edge strip 203. The outer upper edge strip 201 and the outer lower edge strip 203 are arranged opposite to each other and spaced apart. The outer web 202 is connected between the outer upper edge strip 201 and the outer lower edge strip 203, so that the cross section of the outer spar 200 is C-shaped; one end of the inner spar 100 and one end of the outer spar 200 are arranged opposite to each other and connected by an aircraft spar docking structure.

[0049] like Figure 1-Figure 13 As shown, an embodiment of the present invention provides an aircraft wing spar docking structure, which is used to dock an inner wing spar 100 and an outer wing spar 200 along a first direction, and includes an upper docking member 1, a lower docking member 2, an inner connecting member 3 and an outer connecting member 4, wherein one side of the upper docking member 1 is connected to an inner upper edge strip 101 of the inner wing spar 100 and an outer upper edge strip 201 of the outer wing spar 200, and the other side is connected to an inner web plate 102 of the inner wing spar 100 and an outer web plate 202 of the outer wing spar 200, and the lower docking member 2 One side is connected to the inner lower edge strip 103 of the inner section spar 100 and the outer lower edge strip 203 of the outer section spar 200, and the other side is connected to the inner section web 102 and the outer section web 202. The inner connecting member 3 is arranged on the inner section web 102 and the outer section web 202, one end is connected to the upper docking member 1, and the other end is connected to the lower docking member 2. The outer connecting member 4 is installed on the side of the inner section spar 100 and the outer section spar 200 away from the inner connecting member 3, and is connected to the inner section web 102 and the outer section web 202.

[0050] In this embodiment, one side of the upper docking member 1 is connected to the inner upper edge strip 101 of the inner spar 100 and the outer upper edge strip 201 of the outer spar 200, and the other side is connected to the inner web 102 of the inner spar 100 and the outer web 202 of the outer spar 200. One side of the lower docking member 2 is connected to the inner lower edge strip 103 of the inner spar 100 and the outer lower edge strip 203 of the outer spar 200, and the other side is connected to the inner web 102 and the outer web 202. For the connection area between the inner spar 100 and the outer spar 200, this embodiment can ensure the connection strength between the edge strip and the web of the corresponding spar by arranging the upper docking member 1 and the lower docking member 2, so that the structure is more stable and safe, and the failure of the composite material is avoided. At the same time, the sealing of the spar docking is also improved. The inner connector 3 is arranged on the inner web 102 and the outer web 202, one end of which is connected to the upper docking member 1 and the other end of which is connected to the lower docking member 2. The outer connector 4 is installed on the side of the inner spar 100 and the outer spar 200 away from the inner connector 3, and is connected to the inner web 102 and the outer web 202, so that the inner connector 3 and the outer connector 4 can be used in combination and cooperate with each other, thereby improving the bearing capacity of the web in the docking area of ​​the spar. Compared with the previous metal spar structure connection method, the manufacturing and assembly of the above-mentioned components are simpler and more convenient. Moreover, by separately arranging the outer connector 4 on the outer side of the spar, not only the structural connection strength is further improved, but also the component structure is simplified, the structural weight is reduced, and it is beneficial to improve the structural efficiency. Through the mutual cooperation of the upper docking member 1, the lower docking member 2 and the inner connector 3, the integrity of the inner structure in the docking area of ​​the spar can also be guaranteed, and the sealing is further improved. Through the above-mentioned arrangement, the aircraft spar docking structure of this embodiment can improve the sealing and structural efficiency while ensuring the structural strength, reduce the assembly difficulty, and avoid the failure of the composite material.

[0051] Specifically, Figure 4 and Figure 7 As shown, the upper docking member 1 includes an upper docking edge strip 11 and an upper docking web 12 connected to each other, the upper docking edge strip 11 is connected to the inner upper edge strip 101 and the outer upper edge strip 201, and the upper docking web 12 is connected to the inner section web 102 and the outer section web 202. Figure 5 and Figure 8 As shown, the lower docking member 2 includes a lower docking edge strip 21 and a lower docking web 22 connected to each other, the lower docking edge strip 21 is connected to the inner lower edge strip 103 and the outer lower edge strip 203, the lower docking web 22 is connected to the inner section web 102 and the outer section web 202, and the cross-sections of the upper docking member 1 and the lower docking member 2 along the first direction are both L-shaped. Through the above arrangement, the connection between the upper docking member 1 and the lower docking member 2 and the inner section spar 100 and the outer section spar 200 is more solid and stable, which is conducive to improving the structural strength.

[0052] More specifically, the upper docking edge strip 11 is connected to one end of the upper docking web 12, so that the cross-section of the upper docking member 1 is L-shaped, and the lower docking edge strip 21 is connected to one end of the lower docking web 22, so that the cross-section of the lower docking member 2 is L-shaped. Through the above arrangement, the upper docking member 1 and the lower docking member 2 fit more closely to the inner side of the wing beam, which can improve the sealing between the components.

[0053] Specifically, Figure 4 and Figure 5 As shown, the thickness of the upper docking edge strip 11 and the lower docking edge strip 21 gradually decreases from the middle to the two ends. In this embodiment, the thickness of the above components decreases from the middle to the two ends in a step-like manner. Since the upper docking member 1 and the lower docking member 2 are both made of metal, and the spar is made of composite materials, through the above arrangement, when the spar connection area transitions to the non-connection area, the stiffness change of the metal parts and the composite parts can be slowed down, and the risk of composite material damage can be reduced. At the same time, the weight of the upper docking member 1 and the lower docking member 2 can be reduced while ensuring the strength of the connection area, thereby improving the structural efficiency.

[0054] In other embodiments, a thickness step reduction may be provided on the upper docking web 12 and the lower docking web 22, or a thickness step reduction may be provided on the upper docking web 12, the lower docking web 22, the upper docking edge strip 11 and the lower docking edge strip 21. As long as the above-mentioned functional effects can be achieved, no excessive restrictions are made herein.

[0055] Specifically, Figure 5 and Figure 6 As shown, the inner connecting member 3 includes an inner connecting edge strip 31 extending along the second direction, the two ends of the inner connecting edge strip 31 are respectively fitted and connected to the upper docking member 1 and the lower docking member 2, the middle part is fitted and connected to the inner section web 102 and the outer section web 202, the second direction is arranged at an angle to the first direction, and the connection and cooperation between the upper docking member 1, the lower docking member 2 and the inner connecting member 3 are made tighter, and the inner connecting member 3 is connected to the upper docking member 1, the lower docking member 2, the inner section web 102 and the outer section web 202 through the fitting surface sealing, thereby ensuring the connection strength and sealing between the components.

[0056] More specifically, in this embodiment, the second direction is perpendicular to the first direction, so that the inner connector 3 can be directly connected to the upper docking member 1 and the lower docking member 2, reducing the extension length of the inner connector 3 in the second direction, which is conducive to saving materials and reducing costs. In other embodiments, the angle between the second direction and the first direction is not limited, as long as the connection strength and sealing between the components can be guaranteed.

[0057] More specifically, the inner connecting member 3 further includes an inner connecting web 32 extending along the second direction, the inner connecting web 32 is connected to the inner connecting edge strip 31, the inner connecting web 32 and the inner connecting edge strip 31 are arranged at an angle, the inner connecting web 32 is used to connect the wing ribs, and the cross section of the inner connecting member 3 along the second direction is T-shaped. The inner connecting web 32 in this embodiment can be used to connect other components of the wing box section, including but not limited to the wing ribs, and can meet various requirements in the actual operation of the wing spar.

[0058] Specifically, Figure 3 and Fig.10 As shown, in this embodiment, the external connector 4 is a flat plate, which is attached to the inner web 102 and the outer web 202. The two ends of the flat plate along the second direction gradually narrow toward the middle, and the second direction is set at an angle with the first direction. The outer edges of the two ends along the first direction are concave. Under the condition of ensuring the strength of the structural connection, the amount of flat plate material used can be reduced, thereby reducing the weight of the external connector 4. Moreover, by changing the area of ​​the external connector 4, the weight of the external connector 4 can be reduced under the premise of ensuring the strength of the spar connection area, which is conducive to improving the structural efficiency.

[0059] More specifically, the outer connector 4 can be simplified into a flat plate structure according to the structural connection and load conditions, which is conducive to reducing the manufacturing difficulty and facilitating assembly. The flat plate is directly connected to the inner section web 102 and the outer section web 202 on the outer side of the spar. Figure 3 As shown, the connection area of ​​the flat plate at the joint between the inner wing beam 100 and the outer wing beam 200 is the largest. Along the first direction, the middle part of the outer connecting member 4 extends to both ends, and the connection area between the outer connecting member 4 and the wing beam gradually changes. The two ends of the flat plate along the second direction gradually shrink to present a concave shape, so as to reduce the connection area between the outer connecting member 4 and the wing beam, and further reduce the weight of the outer connecting member 4, so as to bear a larger load through a simple structure, which is conducive to improving structural efficiency.

[0060] More specifically, in this embodiment, the second direction is perpendicular to the first direction, so that the outer connector 4 can reduce the extension length in the second direction, so that the inner spar 100 and the outer spar 200 are respectively connected to the outer connector 4 in a relatively symmetrical structure, which is conducive to uniform force on the spar, and is also conducive to saving materials and reducing costs. In other embodiments, the angle between the second direction and the first direction is not limited, as long as the above-mentioned functions can be achieved.

[0061] Specifically, Fig.12 and Fig.13As shown, in another embodiment, the external connection member 4 is preferably a C-shaped structure, specifically including an external connection web 41 and two external connection edges 42. The external connection web 41 is connected to the inner section web 102 and the outer section web 202 in a close fit. The two external connection edges 42 are respectively connected to the two sides of the external connection web 41, and are respectively arranged at an angle on both sides of the external connection web 41, for connecting the wing wall panels. The cross section of the external connection member 4 along the first direction is C-shaped. Through the above arrangement, the inner section spar 100 and the outer section spar 200 can be further firmly connected through the external connection member 4, ensuring the structural strength of the spar connection area, and also meeting various requirements of the actual operation of the spar. In addition, the two external connection edges 42 can connect the wing wall panels and other components, which are adjusted according to the actual operation.

[0062] More specifically, in this embodiment, both the external connecting web 41 and the external connecting edge strip 42 can be provided with the above-mentioned step-down thickness, that is, the thickness of the external connecting web 41 and the external connecting edge strip 42 are stepped down from the middle to the two ends, so as to reduce the weight of the external connecting web 41 and the external connecting edge strip 42, which is conducive to improving the structural efficiency. In other embodiments, one of the external connecting web 41 and the external connecting edge strip 42 can be provided with the above-mentioned step-down thickness, as long as the above-mentioned functional effects can be achieved, and no excessive restrictions are made here.

[0063] Specifically, Fig.12 As shown, the external connecting member 4 also includes a plurality of reinforcing ribs 43. The reinforcing ribs 43 are extended along the second direction and are arranged on the external connecting web 41. The two ends are respectively connected to the opposite sides of the two external connecting edge strips 42. By arranging the reinforcing ribs 43, the structural strength of the wing beam docking area is further improved.

[0064] like Fig.12 As shown, in this embodiment, two reinforcing ribs 43 are provided, and the structural strength of the spar connection area is strengthened by the two reinforcing ribs 43. In other embodiments, three reinforcing ribs 43 may be provided, and the specific number may be adjusted according to actual operation needs, as long as the above-mentioned functions can be achieved, and no excessive limitation is made here.

[0065] Specifically, Figure 5 , Figure 6 and Fig. 9 As shown, a recessed area is provided on the side of the inner connector 3 away from the inner web 102 and the outer web 202, thereby further reducing the weight of the inner connector 3 and improving the structural efficiency. The recessed area in this embodiment is provided on the inner connecting edge strip 31 and is located on both sides of the inner connecting web 32. In other embodiments, those skilled in the art may adjust the specific setting of the recessed area according to actual operation requirements, as long as the above-mentioned functions can be achieved, and no excessive limitation is made here.

[0066] More specifically, if Fig. 9 As shown, a connecting portion is provided on one side of the inner connecting member 3 facing the inner section web 102 and the outer section web 202, and the cross-section of the connecting portion along the first direction is U-shaped, and both ends of the connecting portion extend along the second direction and are parallel to the upper docking member 1 and the lower docking member 2, and are respectively fitted and connected to the connecting portion by the upper docking member 1 and the lower docking member 2, so that when the inner connecting member 3 is fitted and connected with the upper docking member 1, the lower docking member 2, the inner section web 102 and the outer section web 202, it can ensure that the inner connecting member 3 is fitted with the inner section web 102 and the outer section web 202, and can accommodate the connecting part with the upper docking member 1 and the lower docking member 2, so that the inner connecting edge strip 31 of the inner connecting member 3 can be parallel to the inner section web 102 and the outer section web 202, that is, the inner connecting edge strip 31 can maintain a consistent thickness when connected with other components, thereby ensuring that the components are subjected to uniform force.

[0067] Specifically, Figure 3 and Fig.11 As shown, the thickness of the external connector 4 gradually decreases from the middle to both ends. In this embodiment, the thickness of the external connector 4 decreases in a step-like manner from the middle to both ends. This setting can slow down the stiffness change of metal parts and composite parts when the spar connection area transitions to the non-connection area, reduce the risk of composite material damage, and at the same time, reduce the weight of the external connector 4 while ensuring the strength of the connection area, further improving the structural efficiency.

[0068] Specifically, in this embodiment, the upper docking member 1, the lower docking member 2, the inner connecting member 3 and the outer connecting member 4 are all made of metal, and the metal material includes but is not limited to aluminum alloy and titanium alloy, so that the components of the aircraft wing beam docking structure have high strength, good corrosion resistance and are easy to process.

[0069] In addition, the stepwise reduction of thickness described in this embodiment may adopt the following scheme:

[0070] like Figure 1-Figure 13 As shown, the middle parts of the upper docking member 1, the lower docking member 2 and the outer connecting member 4 are all located at the connection between the inner wing spar 100 and the outer wing spar 200, and the thickness of the above-mentioned components is the largest (the maximum thickness of the parts) at this location. Along the extension direction of the inner wing spar 100 and the outer wing spar 200, the thickness of the above-mentioned components decreases stepwise toward both ends. Further, taking into account the structural strength and self-weight of each component, the step-by-step decrease includes at least two steps, wherein the first step-by-step decrease has a step thickness of 60% to 80% of the maximum thickness of the part, and the second step-by-step decrease has a step thickness of 30% to 50% of the maximum thickness of the part. Through the above-mentioned arrangement, not only the self-weight of the corresponding components can be reduced, which is beneficial to improving the structural efficiency, but also the connection strength between the components can be guaranteed. When the wing spar connection area transitions to the non-connection area, the stiffness change of the metal parts and the composite parts can be slowed down, the risk of composite damage can be reduced, and composite failure can be avoided.

[0071] It should be noted that, in this embodiment, the upper docking member 1, the lower docking member 2, the inner connecting member 3 and the outer connecting member 4 can all be designed according to the specific structure of the spar body, and mechanically connected by fasteners, and the structural fitting surfaces of the corresponding components are all sealed, and the technical personnel in this field are clear about the specific principles of the design and the sealing of the fitting surfaces, which will not be repeated here. The technical personnel in this field can also adjust and improve the above components based on the above technical solution and in combination with actual operation requirements to better achieve the docking between the inner section spar 100 and the outer section spar 200.

[0072] The aircraft wing spar docking structure provided in this embodiment can complete the structural design of the composite material C-type wing spar docking area that has been verified in practice. By setting the upper docking member 1 and the lower docking member 2, the connection strength between the corresponding edge strips and webs of the inner section wing spar 100 and the outer section wing spar 200 can be guaranteed, making the structure more stable and safe. By the conformal design of the inner connector 3, the integrity of the inner side connection structure of the wing spar can be guaranteed, and the sealing of the wing spar docking area can be improved. By the combined use of the inner connector 3 and the outer connector 4, the inner section web 102 and the outer section web 202 at the wing spar connection area are guaranteed to be a double shear structure, thereby improving the bearing capacity of the wing spar docking area. By separately setting the outer connector 4 on the outer side of the wing spar, the structural connection strength is further improved. By further simplifying the outer connector 4 into a flat plate structure, the structure is simplified, the structural weight is reduced, which is conducive to improving the structural efficiency and reducing the difficulty of manufacturing and assembly. When the wing spar connection area transitions to the non-connection area, the thickness of the corresponding components is gradually reduced, which can slow down the stiffness change of metal parts and composite parts, reduce the risk of composite damage, and avoid composite failure. Through the above-mentioned arrangement, the aircraft wing spar docking structure of the present application can improve the sealing and structural efficiency of the wing spar after the docking operation while ensuring the structural strength, reduce the difficulty of assembly, and avoid failure of composite materials.

[0073] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An aircraft wing spar docking structure, used for docking an inner wing spar (100) and an outer wing spar (200) along a first direction, characterized in that: include: An upper docking member (1), one side of which is connected to the inner upper edge strip (101) of the inner spar (100) and the outer upper edge strip (201) of the outer spar (200), and the other side of which is connected to the inner web plate (102) of the inner spar (100) and the outer web plate (202) of the outer spar (200); A lower docking member (2), one side of which is connected to the inner lower edge strip (103) of the inner section spar (100) and the outer lower edge strip (203) of the outer section spar (200), and the other side of which is connected to the inner section web plate (102) and the outer section web plate (202); An inner connecting member (3) is arranged on the inner section web (102) and the outer section web (202), one end of which is connected to the upper docking member (1) and the other end of which is connected to the lower docking member (2); An outer connecting member (4) is installed on the side of the inner section spar (100) and the outer section spar (200) away from the inner connecting member (3), and is connected to the inner section web (102) and the outer section web (202).

2. The aircraft wing spar butt joint structure according to claim 1, characterized in that: The upper docking member (1) comprises an upper docking edge strip (11) and an upper docking web (12) which are connected to each other, wherein the upper docking edge strip (11) is connected to the inner upper edge strip (101) and the outer upper edge strip (201), and the upper docking web (12) is connected to the inner section web (102) and the outer section web (202); the lower docking member (2) comprises a lower docking edge strip (21) and a lower docking web (22) which are connected to each other, wherein the lower docking edge strip (21) is connected to the inner lower edge strip (103) and the outer lower edge strip (203), and the lower docking web (22) is connected to the inner section web (102) and the outer section web (202); and the cross-sections of the upper docking member (1) and the lower docking member (2) along the first direction are both L-shaped.

3. The aircraft wing beam butt joint structure according to claim 2, characterized in that: The thickness of the upper butt joint edge strip (11) and the lower butt joint edge strip (21) both gradually decreases from the middle to both ends.

4. The aircraft wing spar butt joint structure according to claim 1, characterized in that: The inner connecting member (3) comprises an inner connecting edge strip (31) extending along a second direction, the two ends of the inner connecting edge strip (31) are respectively fitted and connected to the upper docking member (1) and the lower docking member (2), the middle part is fitted and connected to the inner section web (102) and the outer section web (202), and the second direction is arranged at an angle to the first direction.

5. The aircraft wing spar butt joint structure according to claim 4, characterized in that: The inner connecting member (3) further comprises an inner connecting web (32) extending along the second direction, the inner connecting web (32) being arranged at an angle with the inner connecting edge strip (31), the inner connecting web (32) being used to connect the wing ribs, and the cross section of the inner connecting member (3) along the second direction is T-shaped.

6. The aircraft wing spar butt joint structure according to claim 1, characterized in that: The external connecting member (4) is a flat plate, which is fitted and connected to the inner section web (102) and the outer section web (202). The two ends of the flat plate along the second direction gradually narrow toward the middle, and the outer edges of the two ends along the first direction are concave. The second direction is set at an angle to the first direction.

7. The aircraft wing spar butt joint structure according to claim 1, characterized in that: The external connecting member (4) comprises an external connecting web (41) and two external connecting edge strips (42); the external connecting web (41) is fitted and connected to the inner section web (102) and the outer section web (202); the two external connecting edge strips (42) are respectively arranged at an angle on both sides of the external connecting web (41) for connecting the wing wall panel; the cross section of the external connecting member (4) along the first direction is C-shaped.

8. The aircraft wing spar butt joint structure according to claim 7, characterized in that: The external connection member (4) further comprises a plurality of reinforcing ribs (43), wherein the reinforcing ribs (43) are extended along the second direction and arranged on the external connection web (41), and the two ends of the reinforcing ribs (43) are respectively connected to the opposite sides of the two external connection edge strips (42).

9. The aircraft wing spar butt joint structure according to claim 1, characterized in that: A recessed area is provided on the side of the inner connecting member (3) facing away from the inner section web (102) and the outer section web (202).

10. The aircraft wing spar butt joint structure according to any one of claims 1 to 9, characterized in that: The thickness of the external connecting member (4) gradually decreases from the middle to the two ends.

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