A spanwise variable stiffness joint T-type seal structure and optimization method

Abstract

The application belongs to the technical field of aircraft wing strength design, and particularly relates to a spanwise variable stiffness connected T-shaped seal structure and an optimization method, which comprises a seal structure, a connecting angle box and a support structure; the support structure comprises a plurality of support partitions distributed along the spanwise direction, a wall plate fixedly installed above the support partitions, the wall plate being provided with a honeycomb sandwich at a position between adjacent support partitions, and a plurality of connecting angle boxes being fixedly connected to the rear edge of the wall plate along the spanwise direction; the seal structure comprises a seal plate and a stud, the seal plate is divided into a fixed section in the front section and a cantilever section in the rear section, and the stud is located between the fixed section and the cantilever section; the fixed section is fixedly connected to the upper surface of the connecting angle box and the support partition, and the stud is fixedly connected to the rear end vertical surface of the connecting angle box; the T-shaped seal structure and the wall plate form an overall structure, the relative deformation is reduced, the strain level of the seal structure is effectively reduced, and the service life of the seal structure is enhanced.

Description

Technical Field

[0001] This application belongs to the field of aircraft wing strength design technology, and specifically relates to a T-type sealing structure and optimization method for spanwise variable stiffness connection. Background Technology

[0002] Many aircraft incorporate sealing structures between the control surfaces and the fixed structure to meet aerodynamic sealing requirements. These sealing structures are often cantilever beam-plate structures, with the fixed end connected to the supporting structure via a strip, and the free end overlapping the control surface, closely adhering to it and rotating with it. During repeated large deformations, this type of sealing structure causes the connecting strip to bend repeatedly, making it prone to fatigue cracks. Simultaneously, the connecting bolts bear the loads from bending moments, resulting in high pull-out forces and large compressive loads at the hole edges, making both the bolts and bolt holes susceptible to damage. Summary of the Invention

[0003] To address the aforementioned problems, this application provides: 1. A T-type sealing structure for a spanwise variable stiffness connection, comprising:

[0004] Sealing structure, connecting corner boxes and supporting structure;

[0005] The support structure includes multiple support partitions distributed along the longitudinal direction, a wall panel fixedly installed above the support partitions, the wall panel having a honeycomb core between adjacent support partitions, and multiple connecting corner boxes fixedly connected along the longitudinal direction at the rear edge of the wall panel.

[0006] The sealing structure includes a sealing plate and vertical ribs. The sealing plate is divided into a fixed section at the front and a cantilever section at the rear. The vertical ribs are located between the fixed section and the cantilever section. The fixed section is fixedly connected to the upper surface of the connecting corner box and the supporting partition. The vertical ribs are fixedly connected to the rear vertical surface of the connecting corner box.

[0007] Preferably, the wall panel has a wall panel honeycomb core between adjacent support partitions, and the connecting corner box is fixed on the wall panel honeycomb core.

[0008] Preferably, the sealing structure is made of composite material.

[0009] Preferably, the cantilever section of the sealing structure overlaps with the aircraft control surface, and it is a curved plate structure with variable thickness.

[0010] Preferably, the supporting partition is an L-shaped partition or a T-shaped partition.

[0011] Preferably, the support partition is connected to the wall panel by bolts.

[0012] Preferably, the corner box and the wall panel are connected by bolts.

[0013] Preferably, the wall panel has a first mounting surface with the maximum thickness at the honeycomb core position, a second mounting surface with the minimum thickness near the edge, and a transition slope at the connection between the maximum and minimum thickness; the connecting corner box has a mounting surface that conforms to the shape of the first mounting surface, the second mounting surface, and the transition slope.

[0014] Preferably, the connecting corner box has bolts connecting it to the wall panel at both the first mounting surface and the second mounting surface.

[0015] Preferably, the sealing structure and the connecting corner box are connected by bolts.

[0016] A method for optimizing a T-type sealing structure is provided to optimize the T-type sealing structure with spanwise variable stiffness connection, and to establish a finite element analysis model of the T-type sealing structure and the rudder skin.

[0017] Motion conditions were created for the finite element analysis model and aerodynamic loads were applied to obtain the location where the contact force between the T-shaped sealing structure and the rudder skin was the greatest.

[0018] With the constraint that the contact force between the sealing structure at the location of the greatest contact force and the rudder skin is not greater than a set value, and with the goal of minimizing the strain of the T-shaped sealing structure, the design parameters of the cantilever section of the T-shaped sealing structure are obtained.

[0019] The material and shape of the sealing structure are selected based on the design parameters.

[0020] Preferably, the cantilever segment is divided into multiple sections along the chord direction. The design parameters include the thickness of each section. Based on the determined section thickness, and with the goal of minimizing weight, the layup ratio of a specific anisotropic fabric and unidirectional tape for each section is determined.

[0021] The advantages of this application include:

[0022] 1. The T-shaped sealing structure adds side bolts in the connection area, and the torque from the cantilever end is transmitted through two paths, reducing the risk of damage to the nail holes and bolt head breakage in the connection area of ​​the sealing plate;

[0023] 2. The T-shaped sealing structure and the wall panel form an integral structure, which reduces the relative deformation, effectively reduces the strain level of the sealing structure, and enhances its service life;

[0024] 3. The corner boxes are evenly distributed along the span, which reduces the connection stiffness. The bending moment brought by the sealing structure is transferred to the honeycomb core of the wall panel through the corner boxes, which effectively reduces the weight of the supporting structure.

[0025] 4. The connecting corner boxes are evenly distributed along the spanwise direction, and the spanwise stiffness is variable, which improves the ability to resist wing deformation and torsion;

[0026] 5. A balance was achieved between high strength and large deformation of the structural materials. Attached Figure Description

[0027] Figure 1 This is a cross-sectional view of a T-shaped sealing structure with spanwise variable stiffness connection according to a preferred embodiment of this application;

[0028] Figure 2 This is a perspective view of the T-shaped sealing structure with spanwise variable stiffness connection according to a preferred embodiment of this application, viewed from bottom to top. Detailed Implementation

[0029] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0030] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0031] like Figures 1-2 As shown, in order to solve the above problems, this application provides: 1. A T-type sealing structure for a spanwise variable stiffness connection, comprising:

[0032] Sealing structure, connecting corner box 3 and supporting structure;

[0033] The support structure includes multiple support partitions 1 distributed along the longitudinal direction, and a wall panel 2 fixedly installed above the support partitions 1. The wall panel 2 has a honeycomb core at the position between adjacent support partitions 1, and multiple connecting corner boxes 3 are fixedly connected along the longitudinal direction at the rear edge of the wall panel 2.

[0034] The sealing structure includes a sealing plate 4 and vertical ribs 41. The sealing plate 4 is divided into a fixed section at the front and a cantilever section at the rear. The vertical ribs 41 are located between the fixed section and the cantilever section. The fixed section is fixedly connected to the upper surface of the connecting corner box 3 and the supporting partition 1, and the vertical ribs 41 are fixedly connected to the vertical rear end of the connecting corner box 3. The supporting partition 1 is connected to the wall panel 2 by bolts, and the connecting corner box 3 is connected to the wall panel 2 by bolts. The wall panel 2 has a first mounting surface with the maximum thickness at the honeycomb core position, a second mounting surface with the minimum thickness near the edge, and a transition slope at the junction of the maximum and minimum thickness. The connecting corner box 3 has mounting surfaces that conform to the shapes of the first mounting surface, the second mounting surface, and the transition slope. The connecting corner box 3 is bolted to the wall panel 2 at both the first and second mounting surfaces. The sealing structure and the connecting corner box 3 are bolted together.

[0035] The bending moment of the sealing structure is transferred to the supporting structure through a dual force transmission path of bolts on the outer surface and several side bolts. This connection method converts a portion of the bolt tension into shear force on the inner bolts, reducing the risk of bolt hole failure and bolt head fracture in the sealing plate connection area. The free end is a curved plate with varying thickness, which, according to cantilever beam theory, ensures uniform stress distribution and reduces the risk of failure.

[0036] The spanwise uniformly distributed connecting corner boxes, on the one hand, result in variable spanwise stiffness in the connecting area, improving the ability to resist wing deformation and torsion; on the other hand...

[0037] It also reduces the connection stiffness, allowing the bending moment from the sealed structure to be transferred to the honeycomb core of the wall panel through the corner box, effectively reducing the weight of the supporting structure.

[0038] This spanwise variable stiffness connection sealing structure integrates the T-shaped sealing structure and the wall panel into a single structure. On the one hand, it reduces the relative deformation, effectively lowers the strain level of the sealing structure, and enhances its service life. On the other hand, it can be disassembled and installed together with the wall panel, reducing the difficulty of disassembly and assembly.

[0039] Preferably, the wall panel 2 has a wall panel honeycomb core between adjacent support partitions 1, and the connecting corner box 3 is fixed on the wall panel honeycomb core.

[0040] Preferably, the sealing structure is made of composite material.

[0041] Preferably, the cantilever section of the sealing structure overlaps with the aircraft control surface, and it is a curved plate structure with variable thickness.

[0042] Preferably, the supporting partition 1 is an L-shaped partition or a T-shaped partition.

[0043] A method for optimizing a T-type sealing structure is provided to optimize the T-type sealing structure with spanwise variable stiffness connection, and to establish a finite element analysis model of the T-type sealing structure and the rudder skin.

[0044] Motion conditions were created for the finite element analysis model and aerodynamic loads were applied to obtain the location where the contact force between the T-shaped sealing structure and the rudder skin was the greatest.

[0045] With the constraint that the contact force between the sealing structure at the location of the greatest contact force and the rudder skin is not greater than a set value, and with the goal of minimizing the strain of the T-shaped sealing structure, the design parameters of the cantilever section of the T-shaped sealing structure are obtained.

[0046] The material and shape of the sealing structure are selected based on the design parameters.

[0047] Preferably, the cantilever segment is divided into multiple sections along the chord direction. The design parameters include the thickness of each section. Based on the determined section thickness, and with the goal of minimizing weight, the layup ratio of a specific anisotropic fabric and unidirectional tape for each section is determined.

[0048] The advantages of this application include:

[0049] 1. The T-shaped sealing structure adds side bolts in the connection area, and the torque from the cantilever end is transmitted through two paths, reducing the risk of damage to the nail holes and bolt head breakage in the connection area of ​​the sealing plate;

[0050] 2. The T-shaped sealing structure and the wall panel form an integral structure, which reduces the relative deformation, effectively reduces the strain level of the sealing structure, and enhances its service life;

[0051] 3. The corner boxes are evenly distributed along the span, which reduces the connection stiffness. The bending moment brought by the sealing structure is transferred to the honeycomb core of the wall panel through the corner boxes, which effectively reduces the weight of the supporting structure.

[0052] 4. The connecting corner boxes are evenly distributed along the spanwise direction, and the spanwise stiffness is variable, which improves the ability to resist wing deformation and torsion;

[0053] 5. A balance was achieved between high strength and large deformation of the structural materials.

[0054] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A T-type sealing structure for spanwise variable stiffness connection, characterized in that, include: Sealing structure, connecting corner box (3) and supporting structure; The support structure includes multiple support partitions (1) distributed along the longitudinal direction, and a wall panel (2) fixedly installed above the support partitions (1). The wall panel (2) has a honeycomb core at the position between adjacent support partitions (1), and multiple connecting corner boxes (3) are fixedly connected along the longitudinal direction at the rear edge of the wall panel (2). The sealing structure includes a sealing plate (4) and a vertical rib (41). The sealing plate (4) is divided into a fixed section at the front and a cantilever section at the rear. The vertical rib (41) is located between the fixed section and the cantilever section. The fixed section is fixedly connected to the upper surface of the connecting corner box (3) and the supporting partition (1). The vertical rib (41) is fixedly connected to the vertical surface of the rear end of the connecting corner box (3).

2. The T-type sealing structure for spanwise variable stiffness connection as described in claim 1, characterized in that, The wall panel (2) has a wall panel honeycomb core between adjacent support partitions (1), and the connecting corner box (3) is fixed on the wall panel honeycomb core.

3. The T-type sealing structure for spanwise variable stiffness connection as described in claim 1, characterized in that, The sealing structure is made of composite materials.

4. The T-type sealing structure for spanwise variable stiffness connection as described in claim 3, characterized in that, The cantilever section of the sealing structure overlaps with the aircraft control surface, and it is a curved plate structure with varying thickness.

5. The T-type sealing structure for spanwise variable stiffness connection as described in claim 1, characterized in that, The supporting partition (1) is an L-shaped partition or a T-shaped partition.

6. The T-type sealing structure for spanwise variable stiffness connection as described in claim 5, characterized in that, The supporting partition (1) is connected to the wall panel (2) by bolts.

7. The T-type sealing structure for spanwise variable stiffness connection as described in claim 1, characterized in that, The corner box (3) and the wall panel (2) are connected by bolts.

8. The T-type sealing structure for spanwise variable stiffness connection as described in claim 2, characterized in that, The wall panel (2) has a first mounting surface with the maximum thickness at the honeycomb core position of the wall panel, a second mounting surface with the minimum thickness near the edge, and a transition slope at the connection between the maximum and minimum thickness. The connecting corner box (3) has a mounting surface that fits the shape of the first mounting surface, the second mounting surface and the transition slope surface.

9. The T-type sealing structure for spanwise variable stiffness connection as described in claim 2, characterized in that, The connecting corner box (3) has bolts connecting it to the wall panel (2) at both the first mounting surface and the second mounting surface.

10. The T-type sealing structure for spanwise variable stiffness connection as described in claim 9, characterized in that, The sealing structure and the connecting corner box (3) are connected by bolts.

11. A method for optimizing a T-type sealing structure, used to optimize the T-type sealing structure with spanwise variable stiffness connection as described in any one of claims 1-10, characterized in that, Establish a finite element analysis model of the T-shaped sealing structure and the rudder skin; Motion conditions were created for the finite element analysis model and aerodynamic loads were applied to obtain the location where the contact force between the T-shaped sealing structure and the rudder skin was the greatest. With the constraint that the contact force between the sealing structure at the location of the greatest contact force and the rudder skin is not greater than a set value, and with the goal of minimizing the strain of the T-shaped sealing structure, the design parameters of the cantilever section of the T-shaped sealing structure are obtained. The material and shape of the sealing structure are selected based on the design parameters.

12. The T-type sealing structure optimization method as described in claim 11, characterized in that, The cantilever segment is divided into multiple sections along the chord direction. The design parameters include the thickness of each section. Based on the determined section thickness, and with the goal of minimizing weight, the layup ratio of the anisotropic fabric and unidirectional tape for each section is determined.

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