A design method for a high aspect ratio wing support connection structure

Abstract

This invention belongs to the field of aerospace structural technology and relates to a design method for a high aspect ratio supported wing connection structure. This invention designs a high-efficiency load-transfer supporting wing main connection structure, taking into account high-efficiency load transfer, high structural strength / stiffness, and low aerodynamic interference, thus forming a supporting wing main connection structure design scheme. In the connection between the main wing and the supporting wing configuration, the connection point and connection form are determined by the shortest path and direct force transfer design. Reinforcing ribs and supporting ribs are used to transfer and distribute the connection load, enhancing the local stiffness and strength of the wing connection structure. Through the design of the connection joint between the main wing and the supporting wing, a simple and efficient high-load hinged force transfer is achieved. Simultaneously, the connection joint is designed and placed in the trailing edge space of the wing, achieving a compact structure, reasonable force transfer, and high structural efficiency. The reinforcing rib load transfer design avoids the design of the underwing skin protruding from the transition support, reducing the interference of the supporting wing connection on the aerodynamic shape of the main wing.

Description

Technical Field

[0001] This invention belongs to the field of aerospace structural technology and relates to a design method for a high aspect ratio supported wing connection structure. Background Technology

[0002] The main connection structure of the support wing configuration is the primary means of transferring large loads between the main wing and the support wing. The design of this connection structure is crucial for structural strength and performance. Currently, component-level connection methods in civil aircraft mainly include pin / lug connections and multi-prong plate connections. The design of the main connection in the support wing configuration has a significant impact on the magnitude and direction of the transferred loads. On the one hand, the main connection must minimize its impact on the structural integrity of the main wing box; on the other hand, the axial force generated by the connection will alter the original stress state of the structure. An unreasonable connection structure design will lead to increased structural weight.

[0003] Currently, the main connection method for high aspect ratio support wings involves setting up connection supports on the lower edge of the front / rear beams of the main wing box. These supports are fixed using two sets of high-shear bolts, and the main wing joint is connected to the supports via pins / lugs. This front-to-rear support configuration presents issues with load distribution during loading and load fluctuations during dynamic response. Summary of the Invention

[0004] The objective of this invention is to achieve simple and efficient load transfer through a single-point, two-force bar connection at the rear spars of the main wing. On one hand, this method utilizes internal wing reinforcing ribs to bear and transfer loads, resulting in a direct transfer path and high structural connection efficiency. On the other hand, placing the joint connection point within the trailing edge space of the wing minimizes the impact of local connections on the aerodynamic shape of the support wing configuration. The core of this invention's high-aspect-ratio support wing connection structure design lies in the high axial load at the support wing connection point, primarily tensile load, which manifests as compression on the inner section of the main wing, while reducing the bending moment load at the wing root. Due to factors such as load redistribution and the added mass of the connection structure, the selection of the support point location, the structural form of the main connection, and the load transfer method all affect the structural efficiency of the support wing configuration. The introduction of the support structure provides more design variables and greater design space for high-aspect-ratio wings, contributing to structural weight reduction and efficiency improvement.

[0005] This invention proposes a design method for a high aspect ratio supported wing connection structure, comprising the following steps:

[0006] Step S1: Determine the spanwise connection station A on the main wing 1. The vertical plane where the spanwise connection station A is located intersects the front spar 2 and the rear spar 3 of the wing at points B and C, respectively.

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

[0008] Step S3: Connect CD to form the longitudinal main force transmission reinforcing rib 11 of the support wing connection point. The perpendicular line of the reinforcing rib 11 intersects the front spar of the main wing at point E. Connect CE to form the auxiliary connecting rib 12 of the support wing connection point.

[0009] Step S4: The front end of the reinforcing rib 11 and the connecting rib 12 inside the wing is connected to the front spar 2, the rear end of the reinforcing rib 11 extends to the outside of the rear spar 3 to form the reinforcing rib joint lug 13, and the rear end of the connecting rib 12 extends to the outside of the rear spar 3 to form the connecting rib joint lug 14.

[0010] Step S5: The support wing is connected to the main wing through the connecting joint 15, the main joint is connected to the reinforcing rib joint lug 13 through the main mating lug 16 and the main joint is connected to the connecting rib joint lug 14 through the auxiliary mating lug 17.

[0011] Step S6: The support wing is connected to the main joint bolt hole 18 through the structural skin with multiple nails. The main joint and the support wing joint form an assembly and are connected to the main wing with pins.

[0012] Preferably, the connection structure between the support wing and the main wing is located at the rear spars of the wing, and the structure is connected by a two-force bar through a single-point load transfer of a large load.

[0013] Preferably, the connection structure between the support wing and the main wing is located in the trailing edge space outside the main wing box, reducing the impact of the connection structure on the main wing box structure.

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

[0015] Preferably, auxiliary ribs are used inside the main wing to strengthen the constraint stiffness between the support wing and the main wing, and to transmit the coupled load in the direction perpendicular to the main force transmission path.

[0016] Preferably, the main connector is designed in the space where the trailing edge of the main wing and the interior of the support wing are combined. The main connector is connected to the lugs of the reinforcing rib and the auxiliary rib by two sets of lugs.

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

[0018] Preferably, the connection structure between the support wing and the main wing is entirely contained within the geometric intersection space of the two, reducing changes in shape.

[0019] Beneficial effects of this invention:

[0020] 1. In the connection between the main wing and the support wing configuration, the connection point and connection form are determined by the design of the shortest path and direct force transmission. Reinforcing ribs and support ribs are used to transfer and distribute the connection load, thereby enhancing the local stiffness and strength of the wing connection structure.

[0021] 2. By designing 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 trailing edge space of the wing, achieving a compact structure, reasonable force transmission, and high structural efficiency.

[0022] 3. The design of reinforcing ribs for load transfer avoids the design of the underwing skin protruding from the transition support, reducing the interference of the support wing connection on the aerodynamic shape of the main wing.

[0023] In summary, this invention, through the design of a highly efficient load-transfer supporting wing main connection structure, balances high load transfer efficiency, high structural strength / stiffness, and low aerodynamic interference. This results in a supporting wing main connection structure design scheme that supports the design and verification of novel high-aspect-ratio airfoil configurations. Attached Figure Description

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

[0025] Figure 2 This is a schematic diagram of the rear beam connection point setting of the present invention.

[0026] Figure 3 This is a schematic diagram of the method for determining the main force transmission reinforcing rib and auxiliary rib of the present invention.

[0027] Figure 4 This is a schematic diagram of the arrangement of reinforcing ribs and auxiliary ribs and connecting lugs inside the main wing box of the present invention.

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

[0029] Figure 6 This is a schematic diagram of the overall shape of the main wing, support wing and connecting area of ​​the present invention.

[0030] The components are: 1. Main wing; 2. Front beam; 3. Rear beam; 4. Support wing; 5. Neutral axis of support wing; A. Spanning connection station; B. Intersection of station A and front beam; C. Intersection of station A and rear beam; D. Intersection of neutral axis of support wing and front beam; 11. Reinforcing rib; 12. Connecting rib; E. Intersection of connecting rib and front beam; 13. Reinforcing rib joint lug; 14. Connecting rib joint lug; 16. Main mating lug; 17. Secondary mating lug; 18. Main joint bolt hole. Detailed Implementation

[0031] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of the invention. Furthermore, 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 design method for a high aspect ratio supported wing connection structure includes the following steps:

[0033] Step S1: Determine the spanwise connection station A on the main wing 1. The vertical plane where the spanwise connection station A is located intersects the front spar 2 and the rear spar 3 of the wing at points B and C, respectively.

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

[0035] Step S3: Connect CD to form the longitudinal main force transmission reinforcing rib 11 of the support wing connection point. The perpendicular line of the reinforcing rib 11 intersects the front spar of the main wing at point E. Connect CE to form the auxiliary connecting rib 12 of the support wing connection point.

[0036] Step S4: The front end of the reinforcing rib 11 and the connecting rib 12 inside the wing is connected to the front spar 2, the rear end of the reinforcing rib 11 extends to the outside of the rear spar 3 to form the reinforcing rib joint lug 13, and the rear end of the connecting rib 12 extends to the outside of the rear spar 3 to form the connecting rib joint lug 14.

[0037] Step S5: The support wing is connected to the main wing through the connecting joint 15, the main joint is connected to the reinforcing rib joint lug 13 through the main mating lug 16 and the main joint is connected to the connecting rib joint lug 14 through the auxiliary mating lug 17.

[0038] Step S6: The support wing is connected to the main joint bolt hole 18 through the structural skin with multiple nails. The main joint and the support wing joint form an assembly and are connected to the main wing with pins.

[0039] The support wing and the main wing are connected by a two-force bar structure at the rear spars of the wing, which is achieved through a single-point load transfer of a large load.

[0040] The support wing and the main wing connection structure are located in the trailing edge space outside the main wing box, reducing the impact of the connection structure on the main wing box structure.

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

[0042] The constraint stiffness between the support wing and the main wing is enhanced by auxiliary ribs inside the main wing, and the coupled load in the direction perpendicular to the main force transmission path is transmitted.

[0043] The main connector is designed in the space where the trailing edge of the main wing and the interior of the support wing are combined. The main connector is connected to the reinforcing rib and auxiliary rib lugs by two sets of lugs.

[0044] The main connecting structure and the supporting wing skin are mechanically connected by multiple nails, which effectively disperses and distributes the load transfer during structural transitions, thereby improving the strength of the connecting structure.

[0045] The connection structure between the support wing and the main wing is entirely contained within the geometric intersection space of the two, reducing changes in shape.

[0046] like Figure 2 As shown, the present invention addresses the determination of connection point positions for a high aspect ratio supported wing connection structure. The implementation method is as follows: the trailing edge connection point of the main wing is determined based on the intersection of the longitudinal position of the main wing connection point and the horizontal plane of the main axis of the supporting wing; the main axis of the supporting wing is extended to intersect with the front beam of the main beam; and the geometric position of the reinforcing rib in the horizontal plane is determined.

[0047] like Figure 3 As shown, the geometric position of the auxiliary rib is determined perpendicular to the reinforcing rib and in the horizontal plane, passing through the connection point of the rear beam. The structural design of the reinforcing rib and auxiliary rib is determined within the envelope space between the main wing and the rear beam, as follows: Figure 4 As shown. Connecting lugs for reinforcing ribs and auxiliary ribs are designed on the outer side of the rear beam, and the geometric dimensions of the lugs are determined according to the magnitude of the load transmitted.

[0048] like Figure 5 As shown, the main connection structure is designed, using a diffuser box to connect the lugs of the main wing reinforcing ribs and auxiliary ribs, and the distributed bolt connections of the support wing. The main connection box joint is located inside the outer envelope of the main wing and support wing. The support wing connection and installation involves first bolting the support wing to the main connection structure, and then using installation operation holes on the trailing edge skin of the main wing to achieve the mechanical connection of the main connection pins. The configuration of the support wing for a high aspect ratio wing after the connection design and installation are as follows: Figure 6 As shown.

[0049] It should be noted that, depending on the implementation needs, the steps described in this embodiment can be broken down and combined into new steps to achieve the purpose of this invention. Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A design method for a high aspect ratio supported wing connection structure, characterized in that, Includes the following steps: Step S1: Determine the spanwise connection station A on the main wing (1). The vertical plane where the spanwise connection station A is located intersects the front spar (2) and rear spar (3) of the wing at points B and C, respectively. Step S2: The support wing (4) adopts a rear beam connection scheme, 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 intersect with the front beam of the main wing at point D. Step S3: Connect CD to form the longitudinal main force transmission reinforcing rib (11) of the support wing connection point, and the perpendicular line of the reinforcing rib (11) intersects the front beam of the main wing at point E. Connect CE to form the auxiliary connecting rib (12) of the support wing connection point. Step S4: Connect the front end of the reinforcing rib (11) and connecting rib (12) inside the wing to the front spar (2), extend the rear end of the reinforcing rib (11) to the outside of the rear spar (3) to form a reinforcing rib joint lug (13), and extend the rear end of the connecting rib (12) to the outside of the rear spar (3) to form a connecting rib joint lug (14). Step S5: The support wing is connected to the main wing through the connecting joint (15), the main joint is connected to the reinforcing rib joint lug (13) pin through the main docking lug (16), and the main joint is connected to the connecting rib joint lug (14) pin through the auxiliary docking lug (17). Step S6: The support wing is connected to the main joint bolt hole (18) through the structural skin with multiple nails. The main joint and the support wing joint form an assembly and are connected to the main wing with pins.

2. The design method for the high aspect ratio supported wing connection structure according to claim 1, characterized in that, The supporting wing and the main wing are connected by a structure located at the rear wing sparsity, which achieves a two-force member connection through a single-point load transfer of a large load.

3. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The connection structure between the support wing and the main wing is located in the trailing edge space outside the main wing box, reducing the impact of the connection structure on the main wing box structure.

4. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The location of the reinforcing rib is determined inside the main wing by using the shortest force transmission path. At the same time, the load transmission direction of the supporting wing is collinear with the reinforcing rib in the vertical plane, and the load of the main connection is distributed in the wing box through the reinforcing rib.

5. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The constraint stiffness between the support wing and the main wing is enhanced by auxiliary ribs inside the main wing, and the coupled load in the direction perpendicular to the main force transmission path is transmitted.

6. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The main connector is designed in the space where the trailing edge of the main wing and the interior of the support wing are combined. The main connector is connected to the reinforcing rib and auxiliary rib lugs by two sets of lugs.

7. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The main connecting structure and the supporting wing skin are mechanically connected by multiple nails.

8. The design method for a high aspect ratio supported wing connection structure according to claim 1, characterized in that, The connection structure between the support wing and the main wing is entirely contained within the geometric intersection space of the two, reducing changes in shape.

Images