Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Interlaminar reinforcement process of composite laminates for UAV fuselage and wing

A composite material and interlayer reinforcement technology, which is applied in the field of composite laminates, can solve problems such as weak impact resistance, fiber misalignment, micro cracks, etc., and achieve the effect of improving low-speed impact resistance

Active Publication Date: 2015-12-09
AEROSPACE SHENZHOU AIRCRAFT
View PDF4 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this process can cause the following damage to the preform: fiber breakage, fiber misalignment, fiber bending, resin-rich areas, twisted stitches, microcracks, compaction
In addition, there are obvious deficiencies in the composite material laminated structural parts used in the existing drones, such as weak impact resistance, delamination at the reinforcement-wall board interface, etc.

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Interlaminar reinforcement process of composite laminates for UAV fuselage and wing
  • Interlaminar reinforcement process of composite laminates for UAV fuselage and wing
  • Interlaminar reinforcement process of composite laminates for UAV fuselage and wing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0026] Specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0027] In the present invention, the process for interlayer reinforcement of composite material laminates for unmanned fuselage and wing includes the following steps:

[0028] 1) Preparation of materials and equipment

[0029] This step mainly involves the purchase of unidirectional carbon fiber tow, the purchase of mold materials, the construction of pultrusion process equipment, the manufacture of forming molds, the matrix resin system, and the determination of process parameters. The carbon-fiber-reinforced resin-based composite pin in the present invention is a pin with a very small diameter (usually between 0.15mm and 1.5mm in diameter). The diameters are: Ф0.4mm, Ф0.6mm, Ф0.8mm, Ф1.0mm, Ф1.2mm. In the follow-up process, different composite material pins are made by controlling the amount of carbon fiber, and the glue content of the com...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

PropertyMeasurementUnit
diameteraaaaaaaaaa
Login to View More

Abstract

The invention discloses an interlaminar enhancement process for a composite laminated plate for a fuselage and airfoils of an unmanned plane. The interlaminar enhancement process comprises the following steps of: (1) preparing carbon fiber-reinforced resin matrix composite pins by utilizing a pultrusion molding process; (2) preparing a foam preform containing the carbon fiber-reinforced resin matrix composite pins; (3) implanting the carbon fiber-reinforced resin matrix composite pins in the foam preform into the composite laminated plate for the fuselage and the airfoils of the unmanned plane; and (4) testing mechanical properties of the composite laminated plate after the carbon fiber-reinforced resin matrix composite pins are implanted. By utilizing the process, the anti-low speed impact capability of the structure of the composite laminated plate for the unmanned plane, in particular the anti-interlaminar shearing strength of a stiffened structure of the composite laminated plate can be improved, and a solid foundation is laid for realizing light weight and low cost of the composite laminated plate.

Description

technical field [0001] The present invention relates to a kind of composite material laminated plate for unmanned aircraft fuselage and wing, more specifically, relates to a kind of composite material laminated plate for unmanned aerial vehicle fuselage and aircraft wing which is more resistant to low-speed impact and interlaminar shear strength. Wing composite laminates and interlaminar reinforcement process. Background technique [0002] In recent years, with the deepening of applied research and the development of molding technology, fiber reinforced resin matrix composites (Fiber reinforced resin matrix composites) have been widely used in aerospace structural parts. However, due to the limitation of the structure of the traditional classic composite laminate (Classic composite laminate) and the process of bonding, co-curing, etc., the interlamina of the composite laminate is weak, so the interlaminar fracture toughness of the composite laminate (Interlaminar fracture to...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/44B29C70/54
Inventor 曹可乐周洪王红州刘晓刚
Owner AEROSPACE SHENZHOU AIRCRAFT
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com