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Composite material turning beam structure

A technology of composite materials and turning beams, applied in multi-layer structures, chords/longitudinal beams, aircraft parts, etc., can solve problems affecting the mechanical properties of beams and deal with complex problems, and achieve the effect of ensuring design and manufacturing requirements and improving design levels

Pending Publication Date: 2020-02-07
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The beam is made of unidirectional carbon fiber composite material. Each layer will have a gap or overlap at the turning point, and the notch must be designed. The angle and area of ​​the notch are related to the sweep angle of the beam and the width of the edge. The treatment of laying layers and notch-to-joint joints is complicated, and it will also affect the mechanical properties of the beam
At present, the web parts with turning parts are generally made of carbon cloth, and the turning parts made of unidirectional carbon fiber composite materials are still blank in China.

Method used

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  • Composite material turning beam structure
  • Composite material turning beam structure
  • Composite material turning beam structure

Examples

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Embodiment 1

[0023] As a preferred embodiment of the application, refer to the attached figure 1 , this example discloses:

[0024] A composite turning beam structure, comprising a straight section and a left-right symmetrical sweep, the straight section and the sweep both include an upper edge layup, a web and a lower edge layup;

[0025] The upper edge layup is made of several layers of unidirectional carbon fiber composite materials stacked together for upper edge layup, and the overlapping angles of the several layers of unidirectional carbon fiber composite materials are 0º, -45º, +45º and 90º ; The web is a web formed by stacking several layers of unidirectional tape carbon fiber composite materials, and the overlapping angles are 0º, -45º, +45º and 90º; the lower edge layer is composed of several layers of single Lay layers towards the lower edge formed by stacking carbon fiber composite materials at angles of 0º, -45º, +45º and 90º.

Embodiment 2

[0027] As another preferred embodiment of the present application, refer to the attached figure 1 , this example discloses:

[0028] A composite turning beam structure, comprising a straight section and a left-right symmetrical sweep, the straight section and the sweep both include an upper edge layup, a web and a lower edge layup;

[0029] The upper edge layup is made of several layers of unidirectional carbon fiber composite materials stacked together for upper edge layup, and the overlapping angles of the several layers of unidirectional carbon fiber composite materials are 0º, -45º, +45º and 90º ; The web is a web formed by stacking several layers of unidirectional tape carbon fiber composite materials, and the overlapping angles are 0º, -45º, +45º and 90º; the lower edge layer is composed of several layers of single Lay layers to the lower edge formed by stacking carbon fiber composite materials, the stacking angles are 0º, -45º, +45º and 90º;

[0030] The upper edge la...

Embodiment 3

[0032] As another preferred embodiment of the present application, refer to the attached figure 2 , this example discloses:

[0033] A composite turning beam structure, comprising a straight section and a left-right symmetrical sweep, the straight section and the sweep both include an upper edge layup, a web and a lower edge layup;

[0034] The upper edge layup is made of several layers of unidirectional carbon fiber composite materials stacked together for upper edge layup, and the overlapping angles of the several layers of unidirectional carbon fiber composite materials are 0º, -45º, +45º and 90º ; The web is a web formed by stacking several layers of unidirectional tape carbon fiber composite materials, and the overlapping angles are 0º, -45º, +45º and 90º; the lower edge layer is composed of several layers of single Lay layers to the lower edge formed by stacking carbon fiber composite materials, the stacking angles are 0º, -45º, +45º and 90º;

[0035] The upper edge l...

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Abstract

The invention discloses a composite material turning beam structure and relates to the technical field of aircraft wing machinery. The composite material turning beam structure comprises a straight section and a left-right symmetrical sweepback, wherein the straight section and the sweepback each comprise an upper edge laying layer, a web plate and a lower edge laying layer; and the upper edge laying layer, the web plate and the lower edge laying layer are all formed by stacking a plurality of layers of unidirectional carbon fiber composite materials, and the stacking angles are 0 degree, -45degrees, +45 degrees and 90 degrees. A laying mode of a composite material turning beam is reasonable, can meet the mechanical properties of the beam, and also can meet the requirements of the process.

Description

technical field [0001] The present application relates to the technical field of aircraft wing machinery, and more specifically relates to a composite turning beam structure. Background technique [0002] The weight of the aircraft affects the performance of the aircraft, and the structural weight control of the UAV is getting stricter, accounting for only 25% of the total weight of the aircraft. In order to meet the requirements of structural weight, the application of composite materials in aircraft is becoming more and more prominent. [0003] The beam is an important longitudinal force-transmitting component of the aircraft wing surface, and participates in the transmission of bending moment, torque and shear force on the wing surface. The design and manufacture of straight composite material beams is relatively mature now, and there is no successful precedent for the layup design of composite material turning beams at the turning point. A composite turning beam is 910...

Claims

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Application Information

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IPC IPC(8): B64C3/18B64C3/20
CPCB64C3/182B64C3/20B64C2001/0072
Inventor 巫大秀林荣欣张世全
Owner CHENGDU AIRCRAFT INDUSTRY GROUP