CN113734418A

CN113734418A - Lug joint structure capable of avoiding bearing axial load

Info

Publication number: CN113734418A
Application number: CN202111173719.1A
Authority: CN
Inventors: 王焜; 张颖; 王亚楠; 马律; 周昌成; 李荣杰; 曾俊
Original assignee: Guizhou Guifei Aircraft Design And Research Institute Co ltd
Current assignee: AVIC Guizhou Aircraft Co Ltd
Priority date: 2021-10-09
Filing date: 2021-10-09
Publication date: 2021-12-03

Abstract

The invention provides an ear joint structure capable of avoiding bearing axial load, which comprises an ear flap, a wing, a limiting ear joint and a stress release ear joint, wherein the wing flap is movably connected with the wing through the limiting ear joint and the stress release ear joint, the limiting ear joint comprises a front limiting ear and a rear limiting ear, the stress release ear joint comprises a front stress release ear and a rear stress release ear, the front limiting ear and the rear limiting ear are mutually attached, a structural gap exists between the front stress release ear and the rear stress release ear, and the ear joint structure is composed of one limiting ear joint and a plurality of stress release ear joints. The lug joint structure provided by the invention has simple and efficient structure, and can avoid axial extrusion deformation between lugs without changing the existing structure and increasing the structural strength of the lugs, thereby avoiding the defects of increased structural weight and occupied space of the lugs.

Description

Lug joint structure capable of avoiding bearing axial load

Technical Field

The invention belongs to the field of wing connecting structures, and particularly relates to a joint of a wing flap and a wing lug.

Background

A leading edge flap is designed on the leading edge of a wing of a certain airplane, the leading edge flap is hung on a wing beam body through a plurality of groups of lugs, and the leading edge flap is pushed to rotate around a rotating shaft of the leading edge flap through an actuating cylinder. The lugs are designed to bear radial load mainly in the use process, but because the wing deformation and the leading edge flap deformation are asynchronous (namely the wing and the flap are different in expansion and contraction in the axial direction), the wing rigidity is generally higher than that of the leading edge flap, the load and deformation are both larger than that of the leading edge flap, a plurality of groups of lugs for suspending the leading edge flap are subjected to axial load extruded among the lugs due to the asynchronous deformation, and the additional axial load easily causes the lugs to be extruded and damaged. In the prior art, structural gaps are not reserved among a plurality of groups of lugs, although the degree of freedom of linear motion of the leading edge flap in the axial direction of a rotating shaft is eliminated, the leading edge flap is intrinsically over-constrained, and the over-constraint can bring additional axial load when the wing deformation and the flap deformation are asynchronous. There is a need to eliminate this crushing failure due to the asynchronous deformation of the two parts without changing the existing structural form and without excessively reinforcing the ear.

Disclosure of Invention

The invention aims to provide an ear joint structure capable of avoiding bearing axial load, which solves the technical problems by designing one of a plurality of groups of ears to eliminate the axial movement of a flap (no gap is left between a single group of ears) and adopting a large-gap fit mode between the other plurality of groups of ears.

An ear joint structure for avoiding bearing axial load comprises a wing flap, a wing, a limiting ear joint and a stress release ear joint, wherein the wing flap is movably connected with the wing through the limiting ear joint and the stress release ear joint; the stress release lug joint comprises a front stress release lug and a rear stress release lug, the front stress release lug is fixed on the flap, the rear stress release lug is fixed on the wing, the front stress release lug and the rear stress release lug are movably connected through a shaft pin, the front limiting lug and the rear limiting lug are mutually attached, and a structural gap is formed between the front stress release lug and the rear stress release lug.

Preferably, the structural gap distance between the front stress release lug and the rear stress release lug is L, the value of L is calculated according to the difference value of the deformation of the wing and the wing flap under aerodynamic load, and the front stress release lug and the rear stress release lug are ensured not to be contacted and extruded with each other due to asynchronous deformation of the wing flap and the wing.

Preferably, the number of the limiting lug joints is 1.

Preferably, the front restraining tab, the rear restraining tab, the front stress releasing tab and the rear stress releasing tab are single tabs or multiple tabs.

The lug joint structure provided by the invention has simple and efficient structure, and can avoid axial extrusion deformation between lugs without changing the existing structure and increasing the structural strength of the lugs, thereby avoiding the defects of increased structural weight and occupied space of the lugs.

Drawings

FIG. 1 is a schematic structural view of a tab junction structure;

FIG. 2 is an enlarged view of part A of FIG. 1;

fig. 3 is a partially enlarged structural diagram of part B in fig. 1.

Shown in the figure: 1-a flap; 2-an airfoil; 3-limiting lug joints; 4-stress relief tab joint; 31-a front restraining tab; 32-rear restraining tab; 41-front stress relief tab; 42-rear stress relief tab.

Detailed Description

The present invention will be described in further detail with reference to specific examples.

It should be understood that the terms "upper", "lower", "left", "right", "middle", and the like used herein are for descriptive convenience only and are not intended to limit the scope of the invention, and that changes and modifications in the relative relationship thereof are also considered to be within the scope of the invention without substantial technical changes.

The lug joint structure for avoiding bearing axial load as shown in fig. 1 comprises a flap 1, a wing 2, a limiting lug joint 3 and a stress release lug joint 4, wherein the flap 1 and the wing 2 are movably connected through the limiting lug joint 3 and the stress release lug joint 4, the limiting lug joint 3 comprises a front limiting lug 31 and a rear limiting lug 32, the front limiting lug 31 is fixed on the flap 1, the rear limiting lug 32 is fixed on the wing 2, and the front limiting lug 31 and the rear limiting lug 32 are movably connected through a shaft pin; the stress release lug joint 4 comprises a front stress release lug 41 and a rear stress release lug 42, the front stress release lug 41 is fixed on the flap 1, the rear stress release lug 42 is fixed on the wing 2, the front stress release lug 41 and the rear stress release lug 42 are movably connected through a shaft pin, and the flap 1 can rotate around a rotating shaft of the limit lug joint 3 and the stress release lug joint 4 under the pushing of the flap actuator cylinder. In order to reduce the weight and the occupied space range of the lug structure, the front limiting lug 31 and the rear limiting lug 32 are mutually attached, and the front limiting lug 31 and the rear limiting lug 32 can relatively rotate in the direction of the rotating shaft of the pin shaft; structural gaps exist between the front stress release lugs 41 and the rear stress release lugs 42, and the front stress release lugs 41 and the rear stress release lugs 42 are contacted and extruded with each other to cause structural damage when the wing flap 1 and the wing 2 are not deformed synchronously through the structural gaps. As a person skilled in the art will appreciate, the flap 1 and the wing 2 are connected by a plurality of limiting tab joints 3 and stress relief tab joints 4.

Fig. 2 and fig. 3 are partially enlarged structural schematic diagrams of the parts 1A, B in fig. 1, namely, the limiting lug joint 3 and the stress releasing lug joint 4, and no structural gap exists between the front limiting lug 31 and the rear limiting lug 32, so that the relative displacement in the direction of the rotation axis of the flap 1 and the wing 2 is effectively limited while the rotation of the axis is ensured; a larger structural gap is arranged between the front stress release lug 41 and the rear stress release lug 42, the distance of the gap is L, the numerical value of L is determined by calculating the difference value of the deformation of the wing 2 and the wing flap 1, when asynchronous deformation of the wing flap 1 and the wing 2 needs to be ensured, the front stress release lug 41 and the rear stress release lug 42 cannot be contacted and extruded with each other, and the stress release lug joint 4 does not need to provide the function of limiting the rotation axis direction of the wing flap 1 and the wing 2. Through dividing into two kinds with the auricle joint design, one kind provides the ascending position restriction function of axis of rotation direction, and another kind is through setting up the auricle extrusion phenomenon that the deformation of structure clearance avoiding flight in-process wing flap 1 and wing 2 brought, has reduced the demand to auricle joint design intensity, and then reduces its structure weight and occupation space, has simplified aircraft structure complexity.

As the best scheme, the number of the limiting lug joints 3 is only required to be set to 1, so that the relative displacement of the flap 1 and the wing 2 in the direction of the rotation axis can be limited, the setting position can be freely selected, and the required technical effect can be achieved. The spacing tab joint 3 serves as a component that is more functional than the stress relief tab joint 4, and may suitably increase its structural strength.

As a structure reinforcing scheme of the limiting lug joint 3 and the stress releasing lug joint 4, the front limiting lug 31, the rear limiting lug 32, the front stress releasing lug 41 and the rear stress releasing lug 42 can be single lugs or multiple lugs, and can be selected according to the bearing condition of each part so as to achieve the optimal selection scheme of structural strength and structural simplicity.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims

1. The tab joint structure capable of avoiding bearing axial load comprises a flap (1), a wing (2), a limiting tab joint (3) and a stress release tab joint (4), wherein the flap (1) and the wing (2) are movably connected through the limiting tab joint (3) and the stress release tab joint (4), the limiting tab joint (3) comprises a front limiting tab (31) and a rear limiting tab (32), the front limiting tab (31) is fixed on the flap (1), the rear limiting tab (32) is fixed on the wing (2), and the front limiting tab (31) and the rear limiting tab (32) are movably connected through a shaft pin; stress release lug joint (4) are including preceding stress release lug (41) and back stress release lug (42), and preceding stress release lug (41) are fixed on flap (1), and back stress release lug (42) are fixed on wing (2), and preceding stress release lug (41) and back stress release lug (42) pass through pivot swing joint, its characterized in that: the front limiting lug (31) and the rear limiting lug (32) are mutually attached, and a structural gap exists between the front stress releasing lug (41) and the rear stress releasing lug (42).

2. The tab joint structure of claim 1, wherein: the structural gap distance between the front stress release lug (41) and the rear stress release lug (42) is L, the value of L is calculated according to the deformation difference value when the wing (2) and the flap (1) are subjected to aerodynamic load, and the front stress release lug (41) and the rear stress release lug (42) are required to be ensured not to be mutually contacted and extruded due to asynchronous deformation of the flap (1) and the wing (2).

3. The tab joint structure of claim 1, wherein: the number of the limiting lug joints (3) is 1.

4. The tab joint structure of claim 1, wherein: the front limiting lug (31), the rear limiting lug (32), the front stress releasing lug (41) and the rear stress releasing lug (42) are single lugs or multiple lugs.