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Bidirectional reinforcing structure of composite material of aircraft control surface and forming method

A composite material and reinforcing structure technology, which is applied in the field of aircraft rudder surface composite material bidirectional reinforcing structure and molding, can solve problems such as low overall strength, and achieve the effects of improving molding efficiency, optimizing design, and reducing manufacturing costs.

Inactive Publication Date: 2021-06-04
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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Problems solved by technology

[0006] The purpose of the present invention is to solve the deficiencies of the prior art, and provide a two-way reinforced structure and forming method of composite materials for aircraft rudder surfaces. Technical Problems with Low Overall Strength in Structures Controlled by Global Buckling

Method used

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  • Bidirectional reinforcing structure of composite material of aircraft control surface and forming method
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  • Bidirectional reinforcing structure of composite material of aircraft control surface and forming method

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Embodiment Construction

[0035] Specific embodiments of the present invention will be described in detail below in conjunction with specific drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as isolated, and they can be combined with each other to achieve better technical effects.

[0036] Such as figure 1 As shown, the embodiment of the present invention is an aircraft rudder surface composite material two-way reinforcement structure, including an intermediate laminate 1, a first reinforcing layer arranged on one side of the intermediate laminate 1, and a first reinforcing layer arranged on the other side of the intermediate laminate 1. The second reinforcement layer on one side; the first reinforcement layer is composed of a plurality of first stringers 2 arranged side by side, and the second reinforcement layer is composed of a plurality of second stringers 3 arranged side by side. The long g...

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Abstract

The invention relates to the field of large-size secondary bearing wall plates of aircraft structures, and provides a bidirectional reinforcing structure of a composite material of an aircraft control surface and a forming method. The bidirectional reinforcing structure comprises a middle layer plate, a first reinforcing layer arranged on one side of the middle layer plate, and a second reinforcing layer arranged on the other side of the middle layer plate; the first reinforcing layer and the second reinforcing layer are respectively composed of a plurality of first long trusses and a plurality of second long trusses which are arranged side by side; and a set included angle between each long truss web and the middle layer plate is 85-90 degrees. The forming method comprises the following steps of preparing a metal hard mold, preparing a silicone rubber soft mold, forming a carbon fiber preform, injecting glue and carrying out curing and demolding. According to the bidirectional reinforcing structure, optimization of a force transmission path of the control surface structure can be realized by changing parameters such as the form of the bidirectional reinforcing integral structure and the spatial arrangement included angle of the bidirectional reinforcing integral structure; and the forming process method can be suitable for various composite material integral structures, the forming efficiency of the composite material workpiece structure is improved, and the manufacturing cost is reduced.

Description

technical field [0001] The invention relates to the field of large-size secondary load-bearing wall panels of aircraft structures, in particular to a bidirectional reinforcement structure and a forming method of aircraft rudder surface composite materials. Background technique [0002] There are mainly two types of two-way reinforced structures for aircraft rudder composite materials. One is the reinforced panel structure formed by co-bonding or co-curing of long trusses such as "T" and "工" with the skin of the composite material; the other is One is a sandwich panel structure formed by co-curing of honeycomb core material and composite material skin. In the form of force on the rudder surface, the structure mainly bears the aerodynamic load and transfers the joint load, and the bearing direction is in the heading direction. The design of the panel structure is mainly to prevent the stability failure mode. [0003] Patent 1 "Composite stringer and method of manufacturing a ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/68B29B11/04
CPCB29C70/68B29C70/682B29B11/04
Inventor 丛晶洁刘磊李星
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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