CN101791761A

CN101791761A - Method for compensating for matching surface gap of skeleton and skin of aircraft structure

Info

Publication number: CN101791761A
Application number: CN 201010139845
Authority: CN
Inventors: 梁宪珠; 孙占红; 薛向晨; 刘天舒; 张西伟; 常海峰
Original assignee: AVIC Beijing Aeronautical Manufacturing Technology Research Institute
Current assignee: AVIC Beijing Aeronautical Manufacturing Technology Research Institute
Priority date: 2010-04-07
Filing date: 2010-04-07
Publication date: 2010-08-04

Abstract

The invention discloses a method for compensating for a matching surface gap of a skeleton and a skin of an aircraft structure, which comprises the steps that: (1) the skeleton is firstly fixed, the gap between an actual matching surface and a theoretical matching surface of the skeleton is measured by using a clamping board or an instrument in order to obtain the thickness of gaskets to be filled; (2) the gaskets are manufactured by uncured prepreg, and the gaskets with different thicknesses are bonded to the matching surface of the skeleton; and (3) a vacuum bag is packaged after insulation is performed by means of insulating material, the skin is then buckled and pressed on the skeleton, the skin and the skeleton are clamped by the clamping board, and the gaskets are cured. Compared with the prior art, the technical proposal of the invention achieves the purpose of tight bonding of the matching surface gap of the skeleton and the skin of the structure, settles the problem of difficult allowance assignment in structural assembly of composite material, and simultaneously solves the difficult problems that assembly of complex structure in narrow space have in the process of measuring the gap and installing the gaskets.

Description

The compensation method in a kind of skeleton of Flight Vehicle Structure and covering mating surface gap

Technical field

The present invention is a kind of skeleton of Flight Vehicle Structure and the compensation method in covering mating surface gap, belongs to the forming processing technology field of product.

Background technology

There are manufacturing tolerance during fabrication in the skeleton of aircraft and covering, and the external surface of skeleton need fit tightly with the interior profile of covering, also will guarantee the profile of covering up and down simultaneously.For covering and skeleton simultaneously or a certain side when being composite, because composite can not be polished to mating surface, therefore, need a kind of method that covering and skeleton are fitted tightly.

Existing technology is to increase pad according to gap length between mating surface when assembling, and then utilizes securing member to be fixed.The assembling meeting of narrow and small for the space in labyrinth brings difficulty in the installation process of the measurement in gap and pad.

Summary of the invention

The present invention designs the skeleton that a kind of Flight Vehicle Structure is provided and the compensation method in covering mating surface gap just at the shortcoming that exists in the present technology, its objective is the skeleton that makes structure and the tight applying in covering mating surface gap, solve the problem of Tolerance Allocation difficulty in the composite structure assembling simultaneously.

Technical solution of the present invention is:

The covering profile is processed according to theoretical profile; The skeleton profile adopts negative common difference processing according to mating surface, and this negative common difference should make the clearance control of covering and skeleton mating surface in 0～6mm scope.

At first with skeletal fixation, the mating surface of skeleton and covering is divided into grid, the zone that each grid surrounded is made marks respectively.Adopt clamp or the external surface of apparatus measures skeleton and the difference of theoretical mating surface, thereby calculate the thickness of the pad that will fill, then pad is affixed on the mating surface on the skeleton, isolate back encapsulated vacuum bag with isolated material.At last covering is buckled on the skeleton, the clamp that closes on the external surface of covering solidifies pad.

Pad is to be made by uncured prepreg.The principle of pad utilization is can flow out resin because prepreg is under pressure before uncured, reduces thickness.So be filled in prepreg in the gap will adapt to the gap when being under pressure thickness.The maximum compressibility of making the prepreg of pad is 25% of its thickness.Joint sheet thickness should be bigger by 5～25% than its gap that will fill.According to each regional gap on the mating surface, select the required prepreg of pad, according to the thickness of each regional institute laying prepreg of THICKNESS CALCULATION in the gap that will fill, then the prepreg overlay of different-thickness is affixed on the mating surface on the skeleton by the zone, the surface pastes one deck isolated material.

Description of drawings

Structural representation when Fig. 1 implements for technical solution of the present invention

The specific embodiment

Shown in accompanying drawing 1, the compensation method in the skeleton of this kind Flight Vehicle Structure and covering mating surface gap, it is characterized in that: the step of this method is:

(1) at first that skeleton 1 is fixing, adopt clamp or the actual matching surface of apparatus measures skeleton 1 and the gap of theoretical mating surface, obtain the thickness of the pad 2 that will fill, generally the gap is 1mm;

(2) pad 2 is to be made by uncured prepreg, the maximum compressibility of making the prepreg of pad 2 is 25% of its thickness, and the thin layer of making the different-thickness specification uses with convenient, according to above-mentioned gap, the pad of making is thickness 1.2mm before curing, pad 2 is attached on the mating surface of skeleton 1, the thickness of joint sheet 2 should be bigger by 25% than its gap that will fill;

(3) isolate back encapsulated vacuum bag 3 with isolated material, again covering 4 is withheld on skeleton 1,, solidify pad 2 covering 4 and skeleton 1 usefulness clamp 5 chuckings.

After curing is finished, separate skeleton 1 and covering 4, clear up surplus glue.Afterwards, return covering 4 according to the design attitude button.

Compared with prior art, technical solution of the present invention has reached the purpose of the tight applying in the skeleton of structure and covering mating surface gap; Solve Tolerance Allocation hard problem in the composite structure assembling, the difficulty of the assembling meeting that has solved simultaneously narrow space and labyrinth in the installation process of the measurement in gap and pad.

Claims

1. the compensation method in the skeleton of a Flight Vehicle Structure and covering mating surface gap, it is characterized in that: the step of this method is:

(1) at first that skeleton (1) is fixing, adopt clamp or the actual matching surface of apparatus measures skeleton (1) and the gap of theoretical mating surface, obtain the thickness of the pad (2) that will fill;

(2) pad (2) is to be made by uncured prepreg, according to different gaps, the pad (2) of different-thickness is attached on the mating surface of skeleton (1);

(3) isolate back encapsulated vacuum bag (3) with isolated material, again covering (4) is withheld on skeleton (1), covering (4) and skeleton (1) are tightened with clamp (5), solidify pad (2).

2. the compensation method in the skeleton of Flight Vehicle Structure according to claim 1 and covering mating surface gap is characterized in that: the maximum compressibility of making the prepreg of pad (2) is 25% of its thickness.

3. the compensation method in the skeleton of Flight Vehicle Structure according to claim 1 and 2 and covering mating surface gap is characterized in that: the thickness of joint sheet (2) should be bigger by 5～25% than its gap that will fill.