Upper wall end and wallboard connecting integral corner box assembly

A corner box and integral technology is applied in the field of integral corner box assemblies connecting the upper wall end and the wall plate, which can solve the problems of uneven load transmission, large stiffness changes, debonding, etc., so as to avoid sudden changes in stiffness and excessive stiffness changes. The effect of reducing the difficulty of assembly

Pending Publication Date: 2019-03-19
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing integral corner box at the upper wall has a simple structure design and is easy to manufacture, but it has the following disadvantages: First, the existing metal integral corner box is designed to be of equal thickness, so that the metal corner box is connected with the composite material wallboard after assembly The rigidity change at the cut-off position of the regional corner box is too large, which may easily cause the adjacent long truss to be debonded. The sudden change in stiffness of the composite material test piece at this position is more prone to delamination, debonding, etc.
[0003] In addition, the traditional design of the clamping end of the upper wall considers it to be a non-examination area, and the design details of the corner box are usually not optimized, that is, the corner box structure of equal thickness and length mentioned above is likely to cause the test piece to be close to the clamping area. Uneven regional load transmission at the end, distortion of load level and real working conditions, etc.

Method used

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  • Upper wall end and wallboard connecting integral corner box assembly
  • Upper wall end and wallboard connecting integral corner box assembly
  • Upper wall end and wallboard connecting integral corner box assembly

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0047] This embodiment proposes an integral corner box assembly connecting the upper wall end and the wall panel, such as Figure 4 As shown, the connected integral corner box assembly is used for the composite box section test, and the connected integral corner box assembly includes:

[0048] - an external corner box for securing composite test pieces;

[0049] A number of internal independent small corner boxes for fixing the composite material test piece in cooperation with the external corner box;

[0050] The external corner box is arranged on the outside of the composite material test piece wall panel;

[0051] Several internal independent small corner boxes are symmetrically arranged on the inner side of the composite material test piece wall;

[0052] The external corner box is arranged symmetrically with several of the internal independent small corner boxes.

[0053] The first cut-off area of ​​the external corner box on the composite material test piece is set as a...

Embodiment 2

[0072] This embodiment provides a test method for connecting composite material box segments using the connecting integral corner box assembly described in Embodiment 1.

Embodiment 3

[0074] An integral corner box assembly for connecting the upper wall end and the wall panel provided in this embodiment is basically the same as that in Embodiment 1, except that:

[0075] The material of the external corner box is 45# steel.

[0076] The internal independent small corner box is 45# steel.

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Abstract

The invention belongs to the field of aircraft strength tests, and particularly relates to an upper wall end and wallboard connecting integral corner box assembly which comprises an outer corner box and a plurality of inner independent small corner boxes. The outer corner box is used for fixing composite material test articles; the inner independent small corner boxes are used for being matched with the outer corner box, so that the composite material test articles can be fixed; the outer corner box is arranged on the outer sides of composite material test article wallboards; the inner independent small corner boxes are symmetrically arranged on the inner sides of the composite material test article wallboards; the outer corner box and the inner independent small corner boxes are symmetrically arranged. The upper wall end and wallboard connecting integral corner box assembly has the advantages that structural details of upper wall end and wallboard connecting corner boxes are improvedby the upper wall end and wallboard connecting integral corner box assembly according to the performance difference between composite materials and metal materials, effects of transferring force between metal corner boxes and composite material wallboards can be improved, and accordingly potential risks of damage to test articles can be eliminated; two notches are formed at two ends of each cornerbox, and accordingly effects of reducing the weights and coordinating front and rear beam corner box assembling can be realized.

Description

technical field [0001] The invention belongs to the field of aircraft strength tests, and in particular relates to an integral corner box assembly connecting an upper wall end and a wall plate. Background technique [0002] The typical box-section test piece and the full-scale box-section test piece of the composite wing are connected through the upper wall end, the test support tooling and the bearing wall. The metal corner boxes at the upper wall end are installed on the inside and outside of the four sides of the upper and lower wall panels and the front and rear beams at the clamping end of the test piece. The outside is four integral large corner boxes, and the inside is a separate independent small corner box. At present, the two integral metal corner boxes installed on the outside of the upper and lower wall panels are designed to be of equal thickness in the span direction, reinforced by vertical ribs in the span direction, and the position of each vertical rib corre...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 廖杰翠高举斌石林谷斌孙见卓肖志鹏王栋刘传军
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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