Preparation device of aircraft composite material fuselage wall panels and preparation method thereof

A fuselage wall panel and preparation device technology, which is applied in the field of aviation manufacturing, can solve the problems of poor positioning accuracy, difficult positioning and precision control of hat-shaped long truss combined positioning, and achieves reliable layout, is beneficial to laying operations, and reduces overshadowing. The effect of horn rich ester

Active Publication Date: 2014-09-10
AVIC COMPOSITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since molds are usually made of metal materials, the thermal expansion effect of molds leads to poor positioning accuracy, and the combined positioning and precision control of hat-shaped stringers on large wall panels are also more difficult

Method used

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  • Preparation device of aircraft composite material fuselage wall panels and preparation method thereof
  • Preparation device of aircraft composite material fuselage wall panels and preparation method thereof
  • Preparation device of aircraft composite material fuselage wall panels and preparation method thereof

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Embodiment Construction

[0022] The present invention will be described in detail below in conjunction with the accompanying drawings. The preparation device includes a skin mold ( figure 1 ), hat-shaped stringer mold ( figure 2 ) and truss positioning tooling ( image 3 ), skin mold ( figure 1 ) is the negative mold, and the skin mold ( figure 1 ) is the curved surface 1 corresponding to the outer surface of the fuselage, and the skin mold ( figure 1 ) a row of ventilation holes 2 are uniformly opened along the side of the vertical stringer direction, and a row of ventilation holes 3 are evenly opened in the height direction of the skin mold along the side of the stringer direction, and the side surfaces of the skin mold along the stringer direction are Ventilation holes 3 are evenly opened in the length direction, and the skin mold ( figure 1 ) is provided with a positioning hole 4 at the position of each long stringer on both sides of the wall plate along the stringer direction; the hat-shape...

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PUM

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Abstract

The invention belongs to the aerospace manufacturing technology, and relates to a preparation device of an aircraft composite material fuselage wall panels and a preparation method thereof. Cap-shaped stringers are formed through solid male molds; large opening frame type female molds are adopted to lay skins to form the wall panels; and cap-shaped stringer positioning tools are adopted to control gaps of the stringers so as to realize precise positioning of the cap-shaped stringers and to finish the production of the fuselage wall panels. In the preparation method of the aircraft composite material fuselage wall panels, the phenomenon of internal corner ester enrichment and external corner attenuation of the cap-shaped stringers can be effectively reduced by adopting an atmosphere feeding manner and a rubber soft mold process, so that the part thickness uniformity is improved; and one-way prepreg is required to be filled in cementing R areas in cementing assembly, and +- 45-degree laying layers are added, so that the stress concentration caused by the R areas, formed between the cap-shaped stringers and the skins, structurally bearing external loads can be relieved. Air bags in the cementing formation process are used as pressure transfer mediums in the cap-shaped stringers and cavities of the skins, and are capable of effectively guaranteeing the formation quality of the skins and cementing surfaces of the R areas.

Description

technical field [0001] The invention belongs to the aviation manufacturing technology, and relates to a preparation device and a preparation method of aircraft composite material fuselage panels. Background technique [0002] Because composite materials have many excellent characteristics such as specific strength and high specific modulus, fatigue resistance, corrosion resistance and overall formability, their panel structures have been more and more widely used in modern aircraft structures. Composite hat-shaped truss-reinforced panel can withstand the tension, compression and shear loads of the fuselage. has great advantages. When it is used in the aircraft structure, it can reduce the weight by 25%-30% compared with the conventional metal structure, and it can improve the overall performance of the aircraft such as stealth / aeroelasticity. Foreign B787 aircraft and A350 aircraft use positive molds to form fuselage panels, and the cured hat-shaped stringers are pre-embed...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/54B29C33/00
CPCB29C33/10B29C70/342B29C70/543
Inventor 程文礼徐洪波邱启艳
Owner AVIC COMPOSITES
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