AIRCRAFT STRUCTURE - TOPIC 5.2.pptx - AIRCRAFT STRUCTURES Topic 5.2 Composites and Non-Metallics AIRCRAFTSTRUCTURE/REVISION2 1 INTRODUCTION On

AIRCRAFT STRUCTURE - TOPIC 5.2.pptx - AIRCRAFT STRUCTURES...

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AIRCRAFT STRUCTURES AIRCRAFT STRUCTURES Topic 5.2: Composites and Non-Metallics Topic 5.2: Composites and Non-Metallics 1 AIRCRAFTSTRUCTURE/REVISION2
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AIRCRAFTSTRUCTURE/REVISION2 On completion of this topic you should be able to: 5.2.1 Describe basic composite terminology and explain their interaction in typical composite structures . 5.2.2 Describe accepted practices for cutting, sanding or drilling of FRP composite structure identifying the appropriate tool combinations for different FRP materials and state special precautions and handling relating to their use . 5.2.3 Identify the advantages/ disadvantages of matrix/fibre combinations and describe the methods of laminations of FRP materials 5.2.4 Describe hot and cold bonding methods and demonstrate metal to metal / metal composite bonding . 5.2.5 Explain FRP repair schemes including associated curing methods 5.2.6 Identify applicable environmental conditions that apply to composite and non- metallic materials structures and describe the methods of protection used INTRODUCTION 2
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AIRCRAFTSTRUCTURE/REVISION2 Thread Count The number of yarns (threads) per inch or centimetre in either the lengthwise (warp) or crosswise (fill or weft) direction of woven cloth. TERMINOLOGY 3
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AIRCRAFTSTRUCTURE/REVISION2 Fibre – Content The amount of fibre present in a composite. This is usually expressed as a percentage volume fraction or weight fraction of the composite. Fibre – Direction The orientation or alignment of the longitudinal axis of the Fibre with respect to a stated reference axis. Resin Content The amount of resin in a laminate expressed as either a percentage of total weight or total volume. TERMINOLOGY 4
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AIRCRAFTSTRUCTURE/REVISION2 Fibre dominated properties: Tensile strength, and to a certain extent, bending in the fibre direction, are fibre dominated properties. Ply orientations and type of fibre reinforcement used have a strong effect. MATRIX/FIBRE PROPERTIES Matrix damage, or other matrix problems, may have a small effect on tensile strength of a composite structure While matrix damage will have a very large effect on compressive strength. 5
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AIRCRAFTSTRUCTURE/REVISION2 Matrix dominated properties are: compressive strength bending in the off axis direction shear loading MATRIX/FIBRE PROPERTIES Damage to matrix system such as De-lamination porosity, or too low a resin/fibre ratio,. will cause these properties to degrade rapidly eg Ply orientations and type of matrix system used also have a strong effect on these properties. 6
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AIRCRAFTSTRUCTURE/REVISION2 Solid laminate panels and composite repairs are typically fabricated using woven cloth or unidirectional tape. The loads which these structures can take is heavily dependant on details of the ply orientations, especially in unidirectional tape.
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