Design method of supporting wing connecting structure with high aspect ratio

Abstract

The invention belongs to the technical field of aviation structures, and relates to a design method of a high-aspect-ratio supporting wing connecting structure. By designing the efficient load transfer supporting wing main connection structure, efficient load transfer of the structure, high strength / rigidity design of the structure and low aerodynamic configuration interference are considered, and a design scheme of the supporting wing main connection structure is formed. Connecting points and a connecting form are determined through the design of shortest path and direct force transmission on the connection of a supporting wing configuration main wing and a supporting wing, and a reinforcing rib and a supporting rib are adopted for connecting load transmission and dispersion, so that the local rigidity and strength of a wing connecting structure are enhanced; through the design of the connector between the main wing and the supporting wing, simple and efficient large-load hinged force transmission of the connector is achieved, meanwhile, the connector is designed and placed in the rear edge space of the wing, the structure is compact, force transmission is reasonable, and the structure efficiency is high; by adopting the reinforcing rib load transfer design, the design that the wing lower skin protrudes out of the adapter support is avoided, and the interference of supporting wing connection on the aerodynamic configuration of the main wing is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation structures and relates to a design method for a large aspect ratio supporting wing connection structure. Background Art

[0002] The main connection structure of the strut wing configuration is the main way to transfer large loads between the main wing and the strut wing. The design of the connection structure is an important support for structural strength and performance. At present, the component-level connection methods on civil aircraft mainly include: pin / ear connection, plate-type multi-pin connection, etc. The main connection design of the strut wing configuration has a significant impact on the size and direction of the transferred load. On the one hand, the main connection should reduce the impact of the connection on the structural integrity of the main wing box. On the other hand, the axial force generated by the connection will change the stress state of the original structure. An unreasonable connection structure design will lead to structural weight gain.

[0003] At present, the main connection method of the large aspect ratio support wing is to set the connection support at the lower edge of the front / rear beam of the main wing box, connect and fix the connection support through two sets of high shear bolts, and connect the main joint of the support wing with the support through pins / ears. The front and rear connection support has the problem of load distribution during the loading process, and the problem of load fluctuation in dynamic response. Summary of the invention

[0004] Purpose of the invention: The supporting wing connection structure proposed in the present application realizes simple and efficient load transfer through a single-point, two-force rod connection at the rear beam position of the main wing. On the one hand, this method carries and transfers the load through the internal reinforcing ribs of the wing, the transfer route is direct, and the structural connection efficiency is high; on the other hand, the joint docking point is placed in the trailing edge space inside the wing, reducing the change of the aerodynamic shape of the supporting wing configuration caused by the local connection. The core of the design of a large aspect ratio supporting wing connection structure proposed by the present invention is that the axial load at the connection point of the supporting configuration wing is very high, mainly tensile load, which is attached to the main wing as compression of the inner section of the wing, and the bending moment load at the root of the main wing is reduced. Due to factors such as structural load redistribution and additional mass of the connection structure, the selection of the support point position, the structural form of the main connection, and the load transfer method all affect the structural efficiency of the supporting configuration wing. The introduction of the supporting structure provides more design variables and a high design space for the design of the large aspect ratio wing, which is beneficial to structural weight reduction and efficiency improvement.

[0005] The present invention proposes a method for designing a large aspect ratio support wing connection structure, comprising the following steps:

[0006] Step S1: Determine a span-wise connection station A for the supporting wing on the main wing 1, and the vertical plane where the span-wise connection station A is located intersects the wing front beam 2 and the rear beam 3 at points B and C respectively;

[0007] Step S2: adopting a rear beam connection scheme for the support wing 4, the support wing neutral axis 5 is connected to the intersection C. In the rear beam connection scheme, the support wing neutral axis 5 is extended to the intersection D with the front beam of the main wing;

[0008] Step S3: connecting line CD to form the longitudinal main force transmission reinforcement rib 11 of the support wing connection point, and the vertical line of the reinforcement rib 11 intersects the main wing front beam at point E, and connecting line CE to form the auxiliary connection rib 12 of the support wing connection point;

[0009] Step S4: the front ends of the reinforcing rib 11 and the connecting rib 12 inside the wing are connected to the front beam 2, the rear end of the reinforcing rib 11 extends to the outside of the rear beam 3 to form a reinforcing rib joint lug 13, and the rear end of the connecting rib 12 extends to the outside of the rear beam 3 to form a connecting rib joint lug 14;

[0010] Step S5: the supporting wing is connected to the main wing through the connecting joint 15, the main joint is pin-connected to the reinforcing rib joint lug 13 through the main docking lug 16, and the main joint is pin-connected to the connecting rib joint lug 14 through the secondary docking lug 17;

[0011] Step S6: The supporting wing is connected to the main joint bolt hole 18 through the structural skin by multiple nails, the main joint and the supporting wing joint form an assembled whole, and are pin-connected to the main wing.

[0012] Preferably, the connection structure between the supporting wing and the main wing is located at the rear beam of the wing, and a two-force rod connection is achieved through a single-point load transfer of a large load.

[0013] Preferably, the supporting wing and the main wing connection structure are arranged in the trailing edge space outside the main wing box of the wing, so as to reduce the influence of the connection structure on the main wing box structure.

[0014] Preferably, the position of the reinforcing rib is determined by the shortest force transmission path inside the main wing, and the load transfer direction of the supporting wing is collinear with the reinforcing rib in the vertical plane, and the load of the main connection is dispersed in the wing box through the reinforcing rib.

[0015] Preferably, auxiliary ribs are used inside the main wing to strengthen the restraint stiffness of the supporting wing and the main wing, and to transfer the coupling load in a direction perpendicular to the main force transmission path.

[0016] Preferably, a main joint is designed in the space between the trailing edge of the main wing and the inner part of the supporting wing, and the main joint is connected with the reinforcing rib and the auxiliary rib ears by pins through two groups of ears.

[0017] Preferably, the main connection structure and the supporting wing skin are mechanically connected by multiple nails, which effectively disperses the load transfer and distribution of the structural transition and improves the strength of the connection structure.

[0018] Preferably, the connection structure between the support wing and the main wing is completely contained in the geometric intersection space between the two, thereby reducing the change in appearance.

[0019] Beneficial effects of the present invention:

[0020] 1. In the connection between the main wing and the supporting wing of the supporting wing configuration, the connection point and connection form are determined through the design of the shortest path and direct force transmission, and the strengthening ribs and supporting ribs are used to transfer and disperse the connection load to enhance the local stiffness and strength of the wing connection structure;

[0021] 2. Through the design of the connection joint between the main wing and the supporting wing, a simple and efficient large-load hinged force transmission is achieved. At the same time, the connection joint is designed to be placed in the space of the trailing edge of the wing, achieving a compact structure, reasonable force transmission and high structural efficiency;

[0022] 3. The reinforced rib load-transfer design avoids the design of the lower wing skin protruding from the adapter support, reducing the interference of the support wing connection on the aerodynamic shape of the main wing.

[0023] In summary, the present invention takes into account the high-efficiency load transmission, high-strength / rigidity design and low aerodynamic shape interference of the structure by designing the main connection structure of the support wing with high efficiency. The design scheme of the main connection structure of the support wing is formed, which supports the current design and verification of the new configuration of the large aspect ratio wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is the technical roadmap of the present invention.

[0025] Figure 2 It is a schematic diagram of the arrangement of the rear beam connection points of the present invention.

[0026] Figure 3 It is a schematic diagram of a method for determining the main force transmission reinforcement ribs and the auxiliary ribs of the present invention.

[0027] Figure 4 It is a schematic diagram of the arrangement of reinforcing ribs, auxiliary ribs and connecting ears in the wing box of the main wing of the present invention.

[0028] Figure 5 It is a schematic diagram of the mechanical connection between the main connection structure of the present invention and the main wing and the supporting wing.

[0029] Figure 6 It is a schematic diagram of the overall appearance of the main wing, support wing and connection area of ​​the present invention.

[0030] Among them: 1. main wing; 2. front beam; 3. rear beam; 4. supporting wing; 5. neutral axis of supporting wing; A. spanwise connecting position; B. intersection of position A and front beam; C. intersection of position A and rear beam; D. intersection of neutral axis of supporting wing and front beam; 11. reinforcing rib; 12. connecting rib; E. intersection of connecting rib and front beam; 13. reinforcing rib joint ear; 14. connecting rib joint ear; 16. main docking ear; 17. auxiliary docking ear; 18. main joint bolt hole. DETAILED DESCRIPTION

[0031] The present invention is described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0032] like Figure 1 As shown, a method for designing a large aspect ratio braced wing connection structure comprises the following steps:

[0033] Step S1: Determine a span-wise connection station A for the supporting wing on the main wing 1, and the vertical plane where the span-wise connection station A is located intersects the wing front beam 2 and the rear beam 3 at points B and C respectively;

[0034] Step S2: adopting a rear beam connection scheme for the support wing 4, the support wing neutral axis 5 is connected to the intersection C. In the rear beam connection scheme, the support wing neutral axis 5 is extended to the intersection D with the front beam of the main wing;

[0035] Step S3: connecting line CD to form the longitudinal main force transmission reinforcement rib 11 of the support wing connection point, and the vertical line of the reinforcement rib 11 intersects the main wing front beam at point E, and connecting line CE to form the auxiliary connection rib 12 of the support wing connection point;

[0036] Step S4: the front ends of the reinforcing rib 11 and the connecting rib 12 inside the wing are connected to the front beam 2, the rear end of the reinforcing rib 11 extends to the outside of the rear beam 3 to form a reinforcing rib joint lug 13, and the rear end of the connecting rib 12 extends to the outside of the rear beam 3 to form a connecting rib joint lug 14;

[0037] Step S5: the supporting wing is connected to the main wing through the connecting joint 15, the main joint is pin-connected to the reinforcing rib joint lug 13 through the main docking lug 16, and the main joint is pin-connected to the connecting rib joint lug 14 through the secondary docking lug 17;

[0038] Step S6: The supporting wing is connected to the main joint bolt hole 18 through the structural skin by multiple nails, the main joint and the supporting wing joint form an assembled whole, and are pin-connected to the main wing.

[0039] The connection structure between the supporting wing and the main wing is located at the rear beam of the wing, and a two-force rod connection is achieved through a single-point load transfer of large loads.

[0040] The connecting structure between the supporting wing and the main wing is arranged in the trailing edge space outside the main wing box of the wing, so as to reduce the influence of the connecting structure on the main wing box structure.

[0041] The position of the reinforcing rib is determined by the shortest force transmission path inside the main wing. At the same time, the load transfer direction of the supporting wing is collinear with the reinforcing rib in the vertical plane. The load of the main connection is dispersed in the wing box through the reinforcing rib.

[0042] Auxiliary ribs are used inside the main wing to strengthen the constraint stiffness of the support wing and the main wing, and to transfer the coupling load in a direction perpendicular to the main force transmission path.

[0043] The main joint is designed in the space between the trailing edge of the main wing and the inner part of the supporting wing. The main joint is connected with the reinforcing rib and the auxiliary rib ears through two groups of ears.

[0044] The main connection structure and the supporting wing skin are mechanically connected through multiple nails, which effectively disperses the load transfer and distribution of the structural transition and improves the strength of the connection structure.

[0045] The connection structure between the supporting wing and the main wing is completely contained in the geometric intersection space between the two, thus reducing the change in appearance.

[0046] like Figure 2 As shown, the present invention determines the connection point position for a large aspect ratio supporting wing connection structure, and the implementation method is: determine the main wing trailing edge connection point according to the intersection of the longitudinal position of the main wing connection point and the horizontal plane of the supporting wing main axis, extend the supporting wing main axis to intersect with the main beam front beam, and determine the geometric position of the reinforcing rib in the horizontal plane.

[0047] like Figure 3 As shown in the figure, the auxiliary rib geometric position is determined perpendicular to the reinforcing rib and through the rear beam connection point in the horizontal plane. The reinforcing rib and auxiliary rib structural design are determined in the envelope space between the main wing and the rear beam, as shown in the figure. Figure 4 The connecting lugs between the reinforcing ribs and the auxiliary ribs are designed on the outside of the rear beam, and the geometric dimensions of the lugs are determined according to the magnitude of the force transmission load.

[0048] like Figure 5 As shown in the figure, the main connection structure is designed to realize the ear connection of the main wing reinforcement rib and auxiliary rib and the distributed bolt connection of the support wing through a diffusion box. The main connection box joint is located inside the main wing and the support wing outer envelope. The support wing connection installation is firstly performed by bolting the support wing and the main connection structure, and the installation operation hole is set on the main wing trailing edge skin to realize the mechanical connection of the main connection pin. The high aspect ratio wing support wing configuration with completed connection design and installation is shown in the figure Figure 6 shown.

[0049] It should be noted that, according to the needs of implementation, the steps described in this embodiment can be split and combined into new steps to achieve the purpose of the present invention. It is easy for those skilled in the art to understand that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modification, equivalent replacement and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for designing a high aspect ratio support wing connection structure, characterized in that: The following steps are involved: Step S1: determining a span-wise connection station A of the supporting wing on the main wing (1), and the vertical plane where the span-wise connection station A is located intersects the wing front beam (2) and the rear beam (3) at points B and C respectively; Step S2: A rear beam connection scheme is adopted for the support wing (4), and the support wing neutral axis (5) is connected to the intersection point C. In the rear beam connection scheme, the support wing neutral axis (5) is extended to the intersection point D with the front beam of the main wing; Step S3: connecting line CD to form the longitudinal main force transmission reinforcement rib (11) of the support wing connection point, and the vertical line of the reinforcement rib (11) intersects the main wing front beam at point E, and connecting line CE to form the auxiliary connection rib (12) of the support wing connection point; Step S4: the front ends of the reinforcing rib (11) and the connecting rib (12) inside the wing are connected to the front beam (2), the rear ends of the reinforcing rib (11) extend to the outside of the rear beam (3) to form a reinforcing rib joint lug (13), and the rear ends of the connecting rib (12) extend to the outside of the rear beam (3) to form a connecting rib joint lug (14); Step S5: the supporting wing is connected to the main wing via the connecting joint (15), the main joint is connected to the reinforcing rib joint ear piece (13) via the main docking ear piece (16), and the main joint is connected to the connecting rib joint ear piece (14) via the secondary docking ear piece (17); Step S6: The supporting wing is connected to the main joint bolt hole (18) through multiple nails through the structural skin, the main joint and the supporting wing joint form an assembled whole, and are pin-connected to the main wing.

2. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The supporting wing and the main wing connection structure are located at the rear beam of the wing, and a structural two-force rod connection is achieved through single-point load transmission of a large load.

3. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The supporting wing and the main wing connection structure are arranged in the trailing edge space outside the main wing box of the wing, thereby reducing the influence of the connection structure on the main wing box structure.

4. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The position of the reinforcing rib is determined by the shortest force transmission path inside the main wing. At the same time, the load transfer direction of the supporting wing is collinear with the reinforcing rib in the vertical plane. The load of the main connection is dispersed in the wing box through the reinforcing rib.

5. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: Auxiliary ribs are used inside the main wing to strengthen the constraint stiffness of the support wing and the main wing, and to transfer the coupling load in a direction perpendicular to the main force transmission path.

6. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The main joint is designed in the space between the trailing edge of the main wing and the inner part of the supporting wing. The main joint is connected with the reinforcing rib and the auxiliary rib ears through two groups of ears.

7. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The main connection structure is mechanically connected to the supporting wing skin through multiple nails.

8. The method for designing a high aspect ratio braced wing connection structure according to claim 1, characterized in that: The connection structure between the supporting wing and the main wing is completely contained in the geometric intersection space between the two, thus reducing the change in appearance.

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