CN212243789U

CN212243789U - Suspension device for trailing edge flap of airplane

Info

Publication number: CN212243789U
Application number: CN202020716751.4U
Authority: CN
Inventors: 李云鹏; 王俊朋; 李刚; 姜立峰
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2020-04-30
Filing date: 2020-04-30
Publication date: 2020-12-29
Anticipated expiration: 2030-04-30

Abstract

The application provides a suspension device of aircraft trailing edge flap, the device includes bearing 1, suspension joint 2, backing plate 3, roof beam 4, inboard stiffening rib 6, outside stiffening rib 7, lower skin 8, reinforcing plate 9, wherein: the suspension joint 2 is of a single-lug structure in the vertical direction, the connecting area of the suspension joint 2 comprises a vertical surface and a bottom surface, the vertical surface of the suspension joint 2 is respectively connected with an inner reinforcing rib 6 and an outer reinforcing rib 7 through a backing plate 3 and a beam 4, the bottom surface of the suspension joint 2 is respectively connected with the inner reinforcing rib 6 and the outer reinforcing rib 7 through a lower skin 8 and a reinforcing plate 9, the upper end of the suspension joint 2 is provided with a structure optimization hole, the lower end of the suspension joint 2 is provided with a bearing hole, and the thickness of a web area of the suspension joint 2 is reduced from the bearing hole to the far end; the bearing 1 is built in a bearing hole of the suspension joint 2.

Description

Suspension device for trailing edge flap of airplane

Technical Field

The utility model relates to an aircraft design technical field, in particular to linkage of aircraft trailing edge flap.

Background

The suspension technology of the flap relates to the transmission of aerodynamic load and the guarantee of structural safety, and due to the diversity of the structural form and the function of the flap, the suspension joint plays an important role in the use of the flap.

The main suspension form of the conventional airplane flap structure is single-lug and double-lug butt joint, the connection of a single-lug joint and a beam web plate is effective for small airplanes, the flap load is high for large airplanes, the control of the rigidity stability of a control surface has high requirements, and structural reinforcement needs to be carried out through the combined form of a flap beam and a lower wing surface, so that new design requirements are provided for specific joint design and arrangement of ribs in a flap box section.

SUMMERY OF THE UTILITY MODEL

The utility model aims at newly designing out the suspension joint device of a wing flap, satisfy and make succinct, fix a position accurate, pass and carry the efficient needs.

The application provides a suspension device of aircraft trailing edge flap, the device includes bearing 1, suspension joint 2, backing plate 3, roof beam 4, inboard stiffening rib 6, outside stiffening rib 7, lower skin 8, reinforcing plate 9, wherein:

the suspension joint 2 is of a single-lug structure in the vertical direction, the connecting area of the suspension joint 2 comprises a vertical surface and a bottom surface, the vertical surface of the suspension joint 2 is respectively connected with an inner reinforcing rib 6 and an outer reinforcing rib 7 through a backing plate 3 and a beam 4, the bottom surface of the suspension joint 2 is respectively connected with the inner reinforcing rib 6 and the outer reinforcing rib 7 through a lower skin 8 and a reinforcing plate 9, the upper end of the suspension joint 2 is provided with a structure optimization hole, the lower end of the suspension joint 2 is provided with a bearing hole, and the thickness of a web area of the suspension joint 2 is sequentially reduced from the bearing hole to the far end;

the bearing 1 is built in a bearing hole of the suspension joint 2.

Preferably, the arrangement direction of the inner reinforcing ribs 6 and the arrangement direction of the outer reinforcing ribs 7 in the box section are set according to the load direction.

Preferably, the form of connection of the suspension joint 2 to the lower skin 8 is made with a gradient thickness, varying according to the load distribution.

Preferably, the bearing 1 is a joint bearing in a detachable form.

Preferably, the lubrication of the bearing 1 comprises a self-lubricating or oiling form.

Preferably, the device further comprises an upper skin 5, the upper skin 5 being provided at the upper end faces of the beam 4, the inboard stiffener 6 and the outboard stiffener 7.

Preferably, the suspension joints 2 include titanium joints, aluminum joints, steel alloy joints, and composite material joints.

The utility model has the advantages that: 1. the structure form is simple; 2. the force transmission route is clear; 3. the joint bearing is detachable; 4. the joint is subjected to weight reduction optimization design according to load distribution; 5. the support ribs are oriented in accordance with the load path.

Drawings

FIG. 1 is a schematic exterior view of a suspension for a trailing edge flap of an aircraft according to the present application;

FIG. 2 is a diagram illustrating the effect of the mounting of a suspension for a trailing edge flap of an aircraft according to the present application;

FIG. 3 is a schematic view of details of a suspension arrangement for a trailing edge flap of an aircraft according to the present application;

the numbering in the figures illustrates: 1-bearing, 2-suspension joint, 3-backing plate, 4-beam, 5-upper skin, 6-inner reinforcing rib, 7-outer reinforcing rib, 8-lower skin and 9-reinforcing plate.

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

A suspension device for a trailing edge flap of an airplane comprises a bearing, a suspension joint, a base plate, a beam, an upper skin, an inner reinforcing rib, an outer reinforcing rib, a lower skin and a reinforcing plate;

the suspension joint 2 can be made of titanium, aluminum or steel alloy materials according to the requirement; or carbon fiber composite material is selected and cured at high temperature according to the requirement.

A suspension joint 2 of a suspension device for a trailing edge flap of an aircraft is a double-sided connection structure, which is connected with a beam 4 and a lower skin 8 of the flap.

The suspension joint 2 is combined with an airfoil comprising an upper skin 5 and a lower skin 8.

The connection to the beam 4 controls the position of the mounting with the tie plate 3.

The connection with the lower skin 8 takes the reinforcing plate 9 as an intermediate transition and reinforces the structure of the lower skin 8

The single lug of the suspension joint 2 is internally provided with a bearing 1, the bearing 1 is a joint bearing in a detachable mode, and the lubrication mode of the bearing 1 can be a self-lubricating mode or an oil injection mode.

The web region of the suspension joint 2 takes a structurally optimized gradient form and reduces the weight to a local area.

The connection form of the suspension joint 2 and the lower skin 8 adopts gradient thickness and changes according to load distribution.

The suspension joint 2 and the ribs in the box section are load-spreading in the form of a double rib combination of an inner rib 6 and an outer rib 7.

The utility model discloses a to the design of flap linkage, realized hanging the connection that connects and bear the weight of needs to the flap leading edge. The structural part is a main suspension device of the flap, is connected with a front beam web plate of the flap and the appearance of a lower wing surface in a contact surface mode, and is connected with a wing end through a single-lug loading bearing for use.

1) The material of the structural part can be titanium, aluminum or steel alloy material according to the requirement;

2) the material of the structural member can be selected from composite materials according to the requirement;

3) the structural member is connected with ribs in the box section according to the load direction;

4) the connecting area of the structural part is subjected to structural optimization weight reduction according to the load requirement;

5) the strength of the structural part can meet the working condition load requirement of the flap;

6) the structural part is connected with the fixed end in a bearing mode and is suitable for installation of a wing structure.

Claims

1. Suspension arrangement for an aircraft trailing edge flap, characterized in that the arrangement comprises a bearing (1), a suspension joint (2), a shim plate (3), a beam (4), an inboard stiffener (6), an outboard stiffener (7), a lower skin (8), a stiffener plate (9), wherein:

the suspension joint (2) is of a single-lug structure in the vertical direction, a connecting area of the suspension joint (2) comprises a vertical surface and a bottom surface, the vertical surface of the suspension joint (2) is respectively connected with the inner reinforcing rib (6) and the outer reinforcing rib (7) through the backing plate (3) and the beam (4), the bottom surface of the suspension joint (2) is respectively connected with the inner reinforcing rib (6) and the outer reinforcing rib (7) through a lower skin (8) and a reinforcing plate (9), the upper end of the suspension joint (2) is provided with a structure optimization hole, the lower end of the suspension joint (2) is provided with a bearing hole, and the thickness of a web plate area of the suspension joint (2) is sequentially thinned from the bearing hole to the far end;

the bearing (1) is arranged in a bearing hole of the suspension joint (2).

2. Suspension arrangement of an aircraft trailing edge flap according to claim 1, characterized in that the orientation of the placement of the inboard stiffening rib (6) and the orientation of the outboard stiffening rib (7) in the box section are set according to the load direction.

3. Suspension arrangement for an aircraft trailing edge flap according to claim 1, characterized in that the form of the connection of the suspension joint (2) to the lower skin (8) is of gradient thickness, varying according to the load distribution.

4. Suspension arrangement for an aircraft trailing edge flap according to claim 1, characterized in that the bearing (1) is a joint bearing in the form of a removable joint.

5. Suspension arrangement for an aircraft trailing edge flap according to claim 1, characterized in that the manner of lubrication of the bearing (1) comprises a self-lubricating or oiling form.

6. Suspension arrangement for an aircraft trailing edge flap according to claim 1, characterized in that the arrangement further comprises an upper skin (5), the upper skin (5) being arranged on the upper end faces of the spar (4), the inboard stiffening rib (6) and the outboard stiffening rib (7).

7. Suspension arrangement for an aircraft trailing edge flap according to claim 1, characterized in that the suspension joint (2) comprises a titanium joint, an aluminum joint, a steel joint and a composite joint.