CN216443777U

CN216443777U - Aircraft radome fairing registrates motion structure

Info

Publication number: CN216443777U
Application number: CN202122952424.6U
Authority: CN
Inventors: 王翔宇; 朱天文; 郑伟; 黄金昌
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2021-11-29
Filing date: 2021-11-29
Publication date: 2022-05-06
Anticipated expiration: 2031-11-29

Abstract

The application provides an aircraft radome registrates motion structure, registrate motion structure is including the outer sleeve spare and the interior external member of mutual parallel arrangement, one side that outer sleeve spare is towards interior external member is equipped with the spout, interior external member is equipped with the slider towards one side of outer sleeve spare, the slider sets up in the spout, just the static setting of outer sleeve spare, interior external member can realize the motion for outer sleeve spare under the exogenic action. The aircraft radome nesting mechanism is simple in form, controllable in gap and stroke, high in structural stability, low in process manufacturing and assembling difficulty, capable of saving internal space and effectively avoiding collision of nested parts.

Description

Aircraft radome fairing registrates motion structure

Technical Field

The application belongs to the technical field of aircraft maintenance, and particularly relates to an aircraft fairing nesting motion structure.

Background

The fairing nesting mechanism is a moving mechanism for laying a fairing on a framework structure, and a gap is reserved between nesting parts in the existing aircraft fairing nesting moving structure so as to ensure that the nesting part does not generate interference during movement. However, because the sleeved end lacks support, under the action of pneumatic load, rigidity deformation is easy to occur, and collision friction is inevitably generated between the sleeved parts, an anti-abrasion base plate is usually arranged at the sleeved part to reduce friction influence.

However, the method needs to ensure that the anti-abrasion base plate completely covers the whole stroke of the nesting motion, but the range of motion of the nesting part is large, the arrangement of a reinforcing structure in the stroke is difficult, the deformation of the end head cannot be controlled, and the structural stability of the nesting part has a risk.

Disclosure of Invention

It is an object of the present application to provide an aircraft fairing nesting movement structure that addresses or mitigates at least one of the problems of the background art.

The technical scheme of the application is as follows: the utility model provides an aircraft radome registrates moving structure, its characterized in that, registrate moving structure includes outer sleeve spare and the interior external member of mutual parallel arrangement, one side that outer sleeve spare faced interior external member is equipped with the spout, one side that interior external member faced outer sleeve spare is equipped with the slider, the slider sets up in the spout, just the static setting of outer sleeve spare, interior external member can realize the motion for outer sleeve spare under the exogenic action.

Further, the sliding groove is fixed on the outer sleeve piece through integrated machining, welding, bonding or connecting pieces.

Further, the sliding block is fixed on the inner sleeve piece through integrated machining, welding, bonding or connecting pieces.

Furthermore, the number of the sliding grooves and the number of the sliding blocks are two, and the two sliding grooves and the two sliding blocks are symmetrically arranged.

Furthermore, the sliding groove and the sliding block are in a dovetail shape.

The aircraft radome nesting mechanism is simple in form, controllable in gap and stroke, high in structural stability, low in process manufacturing and assembling difficulty, capable of saving internal space and effectively avoiding collision of nested parts.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a top view of an aircraft fairing nesting movement of the present application.

FIG. 2 is a cross-sectional view of an aircraft fairing nesting movement of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to solve the problems in the background art, the application provides an aircraft fairing nesting motion structure to avoid collision friction of nesting parts, improve the rigidity performance of the nesting parts and ensure the structural stability.

As shown in fig. 1 and 2, the aircraft fairing motion registration structure provided in the application comprises an outer sleeve member 1 and an inner sleeve member 2, wherein the outer sleeve member 1 and the inner sleeve member 2 are similar in shape and are formed by an upper semicircular shape and a straight section extending from the end of the semicircular shape, and the gaps between the outer sleeve member 1 and the inner sleeve member 2 are the same, so that a state of being always parallel is formed.

At the straight section part between the external member 1 and the internal member 2, one side of the external member 1 facing the internal member 2 is provided with a sliding groove 11, one side of the internal member 2 facing the external member 1 is provided with a sliding block 12, the sliding groove 11 and the sliding block 12 are arranged oppositely, and the sliding groove 11 and the sliding block 12 are matched to realize the support of the gap.

Meanwhile, the sliding groove 11 is fixedly connected with the outer sleeve member 1, and the sliding block 12 is fixedly connected with the inner sleeve member 2, in a preferred embodiment, the sliding groove 11 and the sliding block 12 can be respectively fixed with the outer sleeve member 1 or the inner sleeve member 2 by integral machining, welding, bonding or connecting members.

When the outer sleeve member 1 and the inner sleeve member 2 need to move relatively, the outer sleeve member 1 is a fixed member, the inner sleeve member 2 is a moving member, the inner sleeve member 2 starts to move under the action of external force, the sliding block 12 fixed relatively to the inner sleeve member is driven to slide in the sliding groove 11, and the outer sleeve member 1 keeps static, so that the sheathing movement of the inner sleeve member 2 and the outer sleeve member 1 is realized.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The utility model provides an aircraft radome fairing registrates moving structure, its characterized in that, registrate moving structure includes outer sleeve (1) and interior external member (2) that mutual parallel arrangement, one side that outer sleeve (1) is towards interior external member (2) is equipped with spout (11), one side that interior external member (2) are towards outer sleeve (1) is equipped with slider (12), slider (12) set up in spout (11), just outer sleeve (1) is static to be set up, interior external member (2) can realize the motion for outer sleeve (1) under the exogenic action.

2. The aircraft fairing telescoping motion arrangement as claimed in claim 1, characterised in that the runner (11) is fixed to the outer casing part (1) by means of an integral machining, welding, gluing or connecting piece.

3. The aircraft fairing telescoping motion arrangement of claim 1, wherein said slider (12) is secured to said inner member (2) by integral machining, welding, adhesive or attachment.

4. The aircraft fairing nesting movement structure of claim 1, wherein said sliding groove (11) and said sliding block (12) are two, and said two sliding grooves (11) and said sliding block (12) are symmetrically arranged.

5. The aircraft fairing nesting movement structure of claim 1, wherein said runner (11) and slider (12) are dovetail-shaped.