Integral spar structure with inflection characteristic

Abstract

The utility model belongs to the field of aircraft wing structure design, and particularly relates to an integral spar structure with an inflection characteristic, the spar structure can be divided into an inner section plane structure area, an outer section plane structure area and an inflection plane area located above the outer section plane structure area from the wing root side to the wing tip side, the transition area structure is connected with the outer section plane structure area and the inflection plane area, and a first included angle is formed between the outer section plane structure area and the inner section plane structure area; and a second included angle is formed between the inflection plane area and the inner section plane structure area, so that the stress of the spar structure is improved, and the additional weight increment of the structure is avoided.

Description

Technical Field

[0001] The present application belongs to the field of aircraft wing structure design, and in particular relates to an integral wing beam structure with a bending feature. Background Art

[0002] In order to realize the system function of a certain type of aircraft, its hydraulic actuator is arranged obliquely in space, and is connected to the wing spar through upper and lower hinge joints to realize load transfer. This makes the axis of the hinge shaft connected to the wing spar a spatial oblique line, that is, the axis of the oblique hinge shaft 2 in the figure, which cannot be close to the vertical beam plane at the same time. The intersection position of the upper hinge joint is far away from the wing spar plane, that is, the intersection point 3 on the oblique hinge axis in the figure, about 330mm. Specifically, the wing hydraulic motion cylinder is connected to the wing spar through upper and lower hinge joints, which are divided into two upper and lower intersections, and are a single-ear joint structure. Among them, the upper and lower hinge joints are connected to the web of the wing spar through fasteners. The upper hinge joint is connected to the inflection feature area 103, and the lower hinge joint is connected to the outer section plane structure area 102. The straight line connecting the upper and lower intersections is the axis of the oblique hinge shaft.

[0003] If the wing spar adopts the traditional straight beam form perpendicular to the wing reference plane, it will inevitably produce a large out-of-plane load on the wing spar structure, which is not conducive to structural stress. If the local thickening method is used to increase the local stiffness, the structural weight will increase significantly. Utility Model Content

[0004] In order to solve the above problems, the present application provides an integral wing beam structure with a turning feature, wherein the wing beam structure can be divided from the wing root side to the wing tip side into an inner section plane structure area, an outer section plane structure area, a turning plane area located above the outer section plane structure area, and a transition area structure connecting the outer section plane structure area and the turning plane area, wherein a first angle is formed between the outer section plane structure area and the inner section plane structure area, and a second angle is formed between the turning plane area and the inner section plane structure area.

[0005] Preferably, a large rounded transition feature is provided between the outer section planar structure area and the transition area structure.

[0006] Preferably, the transition zone structure gradually expands from the wing root side to the wing tip side to form a triangular shape.

[0007] Preferably, the second angle is greater than the first angle.

[0008] Preferably, the spar structure reference planes are all planes.

[0009] Preferably, the inflection plane area is a groove-shaped structure, a spanwise reinforcing rib is provided on the lower side of the inflection plane area, and a plurality of vertical reinforcing ribs are provided in the groove of the inflection plane area.

[0010] Preferably, the axis of the oblique hinge shaft and the inflection plane area have a third angle, and a preset distance is set between the intersection point 3 on the axis of the oblique hinge shaft and the inflection plane area.

[0011] Preferably, a wing spar docking area is provided on the wing root side of the inner section planar structure area, and the wing spar docking area is a plate-like structure without reinforcing ribs.

[0012] The advantages of this application include: This application solves the problem that the hinge joint on a certain type of aircraft cannot be arranged close to the straight beam structure perpendicular to the wing reference plane, and designs the traditional straight wing beam into a structure with local inflection features, so that the distance between the intersection of the upper hinge joint and the wing beam connection area is as small as possible, avoiding the generation of a large out-of-plane load in the connection area between the upper hinge joint and the wing beam web, improving the stress of the wing beam structure, and avoiding additional weight gain of the structure. The designed integral wing beam structure with inflection features has been applied to the wing structure design of a certain type of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a preferred embodiment of the present application that the integral spar structure with inflection features does not have ribbed sides;

[0014] Figure 2 It is a preferred embodiment of the present application that the integral spar structure with an inflection feature has a rib side surface;

[0015] Figure 3 It is a stereoscopic diagram of an integral wing beam structure with a bending feature according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0017] The present application provides an integral wing beam structure with a bending feature, as shown in the figure, in which 1 is an integral beam with a bending feature, 2 is the axis of the oblique hinge axis, and 3 is an intersection point on the oblique hinge axis. The wing beam structure can be divided from the wing root side to the wing tip side into an inner section plane structure area 101, an outer section plane structure area 102, a bending plane area 103 located above the outer section plane structure area 102, and a transition zone structure 104 connecting the outer section plane structure area 102 and the bending plane area 103. There is a first angle between the outer section plane structure area 102 and the inner section plane structure area 101; there is a second angle between the bending plane area 103 and the inner section plane structure area 101. The wing hydraulic motion cylinder is connected to the wing spar through upper and lower hinge joints, which are divided into two upper and lower intersections, and are single-ear and double-ear joint structures. Among them, the upper and lower hinge joints are connected to the spar web through fasteners. The upper hinge joint is connected to the inflection feature area 103 , and the lower hinge joint is connected to the outer section planar structure area 102 .

[0018] Preferably, a large-radius transition feature 108 is provided between the outer section planar structure area 102 and the transition area structure 104 .

[0019] Preferably, the transition zone structure 104 gradually expands from the wing root side to the wing tip side to form a triangular shape.

[0020] Preferably, the second angle is greater than the first angle, wherein the first angle is preferably 6.5° and the second angle is preferably 14.1°.

[0021] Preferably, the spar structure reference planes are all planes.

[0022] Preferably, the turning plane area 103 is a groove-shaped structure, a spanwise stiffener 107 is provided on the lower side of the turning plane area 103, a plurality of vertical stiffeners 106 are provided in the groove of the turning plane area 103, and the thickness of each lattice web in the groove of the turning plane area 103 is different.

[0023] Preferably, the axis line 2 of the oblique hinge axis has a third angle with the inflection plane area 103, and a preset distance is set between the intersection point 3 on the axis line 2 of the oblique hinge axis and the inflection plane area 103, and the preset distance is preferably 60 mm, which is used to connect with the joint at the intersection point 3 on the oblique hinge axis on the inflection plane area 103 for load transfer.

[0024] Preferably, a spar docking area 105 is provided on the wing root side of the inner section plane structure area 101. The spar docking area 105 is a plate-like structure without reinforcing ribs, and the spar is an integral aluminum alloy machined structure. The spar raw material is a thick aluminum alloy forging. In order to save raw material, improve material utilization and reduce costs, the spar is segmented in the inner section plane area on the wing root side, and docked with the inner spar at the spar docking area 105.

[0025] This patent solves the problem that the hinge joint on a certain type of aircraft cannot be arranged close to the straight beam structure perpendicular to the wing reference plane. The traditional straight wing beam is designed into a structure with partial inflection features, so that the distance between the intersection of the upper hinge joint and the wing beam connection area is as small as possible, avoiding the generation of large out-of-plane loads in the connection area between the upper hinge joint and the wing beam web, improving the stress of the wing beam structure, and avoiding additional weight gain of the structure. The designed integral wing beam structure with inflection features has been applied to the wing structure design of a certain type of aircraft.

[0026] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An integral spar structure with an inflection feature, characterized in that: The wing beam structure can be divided into an inner section plane structure area (101), an outer section plane structure area (102), a bending plane area (103) located above the outer section plane structure area (102), and a transition area structure (104) connecting the outer section plane structure area (102) and the bending plane area (103) from the wing root side to the wing tip side. A first angle is formed between the outer section plane structure area (102) and the inner section plane structure area (101); and a second angle is formed between the bending plane area (103) and the inner section plane structure area (101).

2. The integral spar structure with inflection feature according to claim 1, characterized in that: A large rounded transition feature (108) is provided between the outer section planar structure area (102) and the transition area structure (104).

3. The integral spar structure with inflection feature according to claim 1, characterized in that: The transition zone structure (104) gradually expands from the wing root side to the wing tip side to form a triangular shape.

4. The integral spar structure with inflection feature according to claim 1, characterized in that: The second angle is greater than the first angle.

5. The integral spar structure with inflection feature according to claim 1, characterized in that: The spar structure reference surfaces are all planes.

6. The integral spar structure with inflection feature according to claim 1, characterized in that: The inflection plane area (103) is a groove-shaped structure, a span-wise reinforcing rib (107) is provided on the lower side of the inflection plane area (103), and a plurality of vertical reinforcing ribs (106) are provided in the groove of the inflection plane area (103).

7. The integral spar structure with inflection feature according to claim 1, characterized in that: The oblique hinge axis (2) and the inflection plane area (103) have a third included angle, and a preset distance is set between the intersection point (3) on the oblique hinge axis (2) and the inflection plane area (103).

8. The integral spar structure with inflection feature according to claim 1, characterized in that: A wing beam docking area (105) is arranged on the wing root side of the inner section plane structure area (101), and the wing beam docking area (105) is a plate-like structure without reinforcing ribs.

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