INTRODUCTION TO ADVANCED COMPOSITE MATERIALS Dr ZAFFAR M

INTRODUCTION TO ADVANCED COMPOSITE MATERIALS Dr. ZAFFAR M. KHAN 1

Fabrication Introduction Processing/NDT INDUSTRIAL COMPOSITES Design Analysis 2 Industrial Application

Scope Historical background, nature and advantages of composites Types of matrices Fibers and their characterization Physical and mechanical properties of composites Application in aircraft, sports goods, medical, civil engineering and automobile industries 3

First Composite Solo Flight 4

Relative importance of Engineering Materials with respect to time period 5

Trends of Carbon Fiber Composite Growth 6

Carbon Composites for Defence Systems 7

Composite Materials Composite materials are macroscopic combination of two or more materials each having distinct properties. It is composed of: 1. 2. 3. 8 Matrix (Black) Reinforcement (White) Iinterphase

Advantages of Composite Materials Significant weight saving which increases payload and/or range along with fuel saving. Maximum specific strength and stiffness make them lighter than aluminum, stronger than steel. Permits aero-elastic tailoring of structural components. Flexibility of Design Integrated structures diminishes application of rivets. Enhanced fatigue life. Absence of corrosion. Reduced operational, manufacturing and maintenance cost. 9

Comparison of Composites with Metals 10

Aero-elastic Composite The composite structure is tailored to meet varying aerodynamic requirements in aircrafts, cars wind and rotor blades. It reduces drag and enhances energy conservation. 11 Structure

Flexibility of Composite Design

Influence of Vibrations on Composites The vibration damping characteristics of composites are far superior as Compared to metals for following reasons; 1. Matrix visco-elastic effects and 2. micro-cracking 2. Blunting of crack by in fibers 3. transverse direction 3. Debonding and sliding of fibers 4. in axial direction. 13

Integrated Structure Integrated composite structure reduces rivets and associated weight which leads to integrated structure of aircraft, automobiles and other engineering systems. 14

Matrix Constituent Roles: Binds and holds reinforcemaent together Determines composite shape and geometry Transfers stresses to reinforcement 15 Types: Ceramic (Temp < 6000°F) Metallic (Temp < 4000°F) Polymeric (Temp < 600°F) Determine: Environmental resistance Shelf Life Compressive & transverse mechanical properties of composite

Ceramic Matrix Oxides, carbides, nitrides, borides and silicates characterizes high degree of thermal and dimensional stability. Manufacturing Process: Cast from slurries or processed into shape with organic binder and then fired/ sintered/ cured at very high temperature. Examples: Silicon carbide filament in Silicate matrix Boron carbide in Alumina matrix Aluminum oxide in Alumina matrix Metal particles in ceramic matrix CERMETS Applications: Rocket nose cone and Nozzle Combustion Chamber Skin of space plane/ spacecraft Problem Areas: Interface problem 16

Metal Matrix Relatively lower densities of aluminum, titanium and magnesium are reinforced by high strength/ stiffness fibers. Organic fibers are not used due to high processing temperatures. Most common fibers are; Metal fibers of beryllium, molybdenum, steel and tungsten Boron, silicon carbide, silicon boride coated fine wires Whiskers of aluminum oxide, boron carbide or silicon carbide Manufacturing Process: Metal matrix may be coated onto fibers by electro deposition, vapor deposition or plasma spray followed by hot pressing Fibers can be infiltrated with liquid metal under high process Fiber pressed between metal foils and sintered with powder metals Examples: Aluminum, titanium alloys, silver, magnesium, cobalt and copper matrices Applications: Space shuttle, piston ring, connecting rods, suspension components 17

Polymeric Matrix Composed of long chains of hydro carbons Thermoplastics: Softens when heated and hardens when cooled. Can be recycled. Relatively tough Low dimensional stability. Styrenes, Vinyls, Acrylics, 18 Thermosets: Hardens when heated. Composed of long molecular cross links. Cannot be recycled. Relatively brittle. Relatively greater dimensional tolerance. Epoxies, urathanes, phenolics.

Comparison of Thermoset Versus Thermoplastic PROPERTY Melt Viscosity Fiber Impregnation Prepreg Tack Prepreg Drape Prepreg Stability at 0° F Processing Cycle Processing Temperature Mechanical Properties Environmental Durability Damage Tolerance Database 19 THERMOSET THERMOPLASTIC (FIBERITE 931 EPOXY) (ICI APC-2 PEEK) Low High Easy Difficult Good None Good Poor 6 mos. -1 yr. Indefinite 1 -6 Hrs 15 sec 6 hr 350° F 700° F Good Exceptional Average Good Large Average

Structural Performance Ranking of Materials 20

Temperature Response of Ceramic, Metallic & Polymeric Composites 21 Polymeric composites have maximum specific strength but has poor strength at elevated temperatures. Metal and ceramic composites retain their lower mechanical properties at elevated temperature. Selection of composites is determined by environmental temperatures.

Properties of Polymeric Matrices EPOXY (THERMOSET) § § § Most widely used matrix in hi-tech applications Outstanding adhesion Low shrinkage during cure Easy to process forgiving Strong, tough Extensive, reliable data base POLYESTER (THERMOSET) § § § Most widely used matrix for less demanding applications High shrinkage during cure Poorer adhesion than epoxy Very easy to process ; lower pressures and temperatures and shorter cure cycles than epoxy. Lower cost than epoxy In general, poorer properties than epoxy (and less expensive) POLYIMIDE (THERMOSET) § § § Primarily for service at high temperature i. e. 600 F Higher cost than epoxy More difficult to process than epoxy ; more complex cure cycles, requires higher temperatures are pressures Dark colours only High brittleness Propreg does not drape well ( tends to be a little shiff) BISMALEIMIDE (THERMOSET) § § 22 Proposed to fill the gap between polyimide and high temperature epoxies i. e. 450 – 500 degrees F Better strength than epoxy at high temperature It has relatively simple are cycles more like epoxy than polyimide (Thus it is relatively easy to process Application in X-wing vertical take off/landing sibors by Aircraft /copter.

PHENOLIC (THERMOSET) §Expensive and difficult to process; requires high cure pressure §Good electrical resistance • Self extinguishing and not toxic, thus it has received interest for aircraft interiors (for example : graphite fabric reinforced phenolic facings for honeycomb floor panels ) URETHANE (THERMOPLASTIC) §Good toughness and abrasion resistance §Easily foamed and low heat transfer (thus, a common use is insulation ) §Limited in service temperature §Commonly used in Reuction Injection Molding (RIM) to produce strong, stiff, light weight “Self-skinned” structures §Reinforced with carbon fiber Ejection seats PEEK (THERMOPLASTIC) §Tough, high impact resistance, high fracture toughness §Excellent abrasion resistance §Excellent solvent resistance §Low moisture absorption §Very high cost §New, not much data available §Requires very high processing temperature (600 degrees F) which complicates manufacturing §Prepregs are stiff (no drape); thus, flat laminates must first be made, then laminates must be formed to shape with high temp and pressure. Manufacturing with prepregs is still in development stage. 23

Thermoset Composites 24

Thermoplastic Composites 25

Thermoplastic Composites 26

Evolution of Epoxy Resin Poly functional epoxy resin contains more than two epoxide group FIRST GENERATION EPOXIES: Example: NARMCO 5208, CIBA GEIGY – 914 Better dimensional stabile but inherently brittle. Composed of: Tetra Glycidyl Derivative (Wt Fraction : 38. 2 %) Triglycidyl Ether (33. 4%) Dicyandiamide (5. 0%) Poly Ether Sul Phone (23. 4) SECOND GENERATION EPOXIES: Example: NARMCO 5245, CIBA GEIGY-924 Addition of CTBN to original formulation Better damage tolerance, reduced hot /wet performance. Lead to phase separation which imparts desired toughness. 27

Reinforcement Constituent 1. 2. 3. 4. 28 Particulate: Good compression strength but poor tensile properties, and particles in cement. Flakes: Effective solvent resistant but difficult fabrication. Whiskers: High degree of strength but poor crack stopping properties. Fibers: Better structural properties, crack stopping properties, flexibility of design requirement by changing orientation of fibers 0°, +45°, 90° Stacking sequence Types of fibers i. e. glass, carbon, kevlar & carbon

29 Milled Carbon Fibers Carbon Fiber Pellets Chopped Carbon Fibers Carbon Fiber Mat

Micrographs of Carbon, Kevlar and Glass Fibers 30

Properties of High Performance Synthetic Fibers ADVANTAGES DISADVANTAGES APPLICATIONS COST INDEX 31 CARBON (2 -Dimension) KEVLAR (1 Dimension) GLASS (3 Dimension) l Max specific strength l Tough l High temp resistance l Max specific modulus l Light weight l No galvanic corrosion l High temp resistance l No galvanic corrosion l Low notch sensitivity l Expensive l Poor compression l High density l Low impact resistance l Absorbs moisture l Low stiffness l Promotes oxidation l Difficult machining l Poor coupling to resin l Rocket motors l Leading edges, ropes l Water tank, bathroom l Aircrafts members l Ballistic protection accessories, shelters High (6 -7) Intermediate (3) Low (1 -2)

Microstructure of Carbon Fibers The covalently bonded aromatic chains of carbon fiber in the axial direction are held together by weak Wander wall bonds in transverse direction. The alignment of chains in axial direction determines their outstanding strength. 32

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Fabrication of Carbon Fiber Carbonization: 200 -250°F Oxidation: 1000°C Graphitization: 2500 -3000°C Etching of fiber surface 34

Processing Temperature The higher degree of temperature and tension during graphitization process leads to greater alignment of carbon chains and superior mechanical properties of carbon fibers, T-300 (Boeing-727, 737, 747 and Airbus 310) and T-800 (Boeing-777, Airbus 380, Osprey V 22 and JSF). 35

Variation of Mechanical Properties of Carbon Fiber With Respect to Temperature 36

Chemical Kinetics of during Curing of CFRP 37

Kevlar Fibers Kevlar: Aromatic carbon chains are held together by amide group (-CH-NH-). Concentrated solution in strong mineral acid is processed through spinnerets into neutralizing bath. The fibers are washed, dried and heated in nitrogen at high temperature under tension. 38

Properties of Kevlar Fibers 39

Glass Fibers 40

Weave Architecture 41

Through Thickness Stitching 42

Fiber Architecture 43

Prepreg: The resin is impregnated in fibers by passing fibers through resin bath, oven and driers. The resin is advanced from A to B stage. The ready to mold material is stored for application. 44

Unidirectional and Fabric Prepreg 45

Composite Materials Summary Composite Materials Matrix Ceramic Metalic Interphase Polymers Particulate Thermoset Phenolics 46 Polyester Reinforcment Flakes Thermoplastic Epoxy Acrylics PEEK Fibers Carbonates Kevlar Glass

THANK YOU 47