Material Selection for Aerospace Applications Darren Pyfer, P.E. Engineering Specialist Senior October 16, 2001 Agenda • Vought Aircraft Industries Corporate Overview • Material Selection Criteria • Material Types • Material Forms • Examples 10/16/01 2 Vought Aircraft Industries Corporate Overview Vought Company Overview • Largest Single Supplier of Aerostructures to Boeing: - Producing More of the 747 Structure Than Any Other Commercial Supplier for Boeing - Producing More of the C-17 Structure Than Any Other Military Supplier for Boeing 10/16/01 4 Vought Company Overview (cont.) • Largest Single Supplier of Aerostructures to Gulfstream Aerospace – Designed and Build Integrated Wing System for the Gulfstream GV As a Risk-sharing Team Member 10/16/01 5 Vought Company Overview (cont.) • Largest Single Supplier of Aerostructures to Northrop on the B-2 Stealth Bomber Program – Designed and Built the Intermediate Wing Section of the B-2 Bomber including the Engine and Landing Gear Bays 10/16/01 6 Vought Commercial Products 737 747 GV 777 757 CFM56 CF6 GIV 10/16/01 767 HAWKER 800 CF34 7 Vought Military Products C-17 S-3 F/A-18E/F F-14 E-8C/JSTARS E-2C EA-6B V-22 Global Hawk 10/16/01 8 P-3 T-38 Vought Product Line Summary Empennage Fuselage Doors 737 747 757 767 777 GV C-17 10/16/01 9 Wings Nacelle Control Comp Surfaces Material Selection Criteria Static Strength • Material Must Support Ultimate Loads Without Failure. Material Must Support Limit Loads Without Permanent Deformation. – Initial Evaluation for Each Component – Usually Aluminum Is the Initial Material Selection – If Aluminum Cannot Support the Applied Load Within the Size Limitation of the Component, Higher Strength Materials Must Be Considered (Titanium or Steel) – If Aluminum Is Too Heavy to Meet the Performance Requirements, Graphite/Epoxy or Next Generation Materials Should Be Considered 10/16/01 11 Stiffness • Deformation of Material at Limit Loads Must Not Interfere With Safe Operation – There Are Cases Where Meeting the Static Strength Requirement Results in a Component That Has Unacceptable Deflections – If That Is the Case, The Component Is Said to Be a ‘Stiffness’ Design 10/16/01 12 Fatigue (Crack Initiation) • The Ability of a Material to Resist Cracking Under Cyclical Loading – Spectrum Dependant – Stress Concentration Factors – Component Is Limited to a Certain Stress Level Based on the Required Life of the Airframe – Further Processing May Improve Fatigue Properties Such As Shot Peening or Cold Working 10/16/01 13 Damage Tolerance (Crack Growth) • The Ability of a Material to Resist Crack Propagation Under Cyclical Loading – Slow Crack Growth Design – Use of Alloys With Increased Fracture Toughness 10/16/01 14 Weight • Low Weight Is Critical to Meeting Aircraft Performance Goals – Materials Are Tailored for Specific Requirements to Minimize Weight – Materials With Higher Strength to Weight Ratios Typically Have Higher Acquisition Costs but Lower Life Cycle Costs (i.e. Lower Fuel Consumption) 10/16/01 15 Corrosion • Surface Corrosion – Galvanic Corrosion of Dissimilar Metals (see Chart) – Surface Treatments – Proper Drainage • Stress Corrosion Cracking – Certain Alloys Are More Susceptible to Stress Corrosion Cracking (see Chart) – Especially Severe in the Short Transverse Grain Direction 10/16/01 16 Dissimilar Metal Chart 10/16/01 17 Stress Corrosion Cracking (SCC) Chart 10/16/01 18 Producibility • Commercial Availability • Lead Times • Fabrication Alternatives – Built Up – Machined From Plate – Machined From Forging – Casting 10/16/01 19 Cost • Raw Material Cost Comparisons – Aluminum Plate = $2 - $3 / lb. – Steel Plate = $5 - $10 / lb. – Titanium Plate = $15 - $25 / lb. – Fiberglass/Epoxy Prepreg = $15 - $25 / lb. – Graphite/Epoxy Prepreg = $50 - $100 / lb. • Detail Fabrication Costs • Assembly Costs • Life Cycle Costs – Cost of Weight (Loss of Payload, Increased Fuel Consumption) – Cost of Maintenance 10/16/01 20 Specialized Requirements • Temperature • Lightning and Static Electricity Dissipation • Erosion and Abrasion • Marine Environment • Impact Resistance • Fire Zones • Electrical Transparency 10/16/01 21 Performance vs. Cost Dilemma • Highest Performance For The Lowest Cost Is the Goal of Every Airplane Material Selection. – Mutually Exclusive – Compromise Is Required – Define the Cost of Weight to the Aircraft 10/16/01 22 Material Types Aluminum • Aluminum Accounts for ~80% of the Structural Material of Most Commercial and Military Transport Aircraft • Inexpensive and Easy to Form and Machine • Alloys Are Tailored to Specific Needs • 2000 Series Alloys (Aluminum-copper-magnesium) Are Medium to High Strength With Good Fatigue Resistance but Low Stress Corrosion Cracking Resistance. – 2024-T3 Is the Yardstick for Fatigue Properties • 5000 and 6000 Series Alloys Are Low to Medium Strength but Easily Welded 10/16/01 24 Aluminum (cont.) • 7000 Series Alloys (Aluminum-zinc-magnesiumcopper) Are High Strength With Improved Stress Corrosion Cracking Resistance but Most Have No Better Fatigue Properties Than 2000 Series – 7050 and 7075 Alloys Are Widely Used – 7475 Alloy Provides Higher Fatigue Resistance Similar to 2024-T3 10/16/01 25 Aluminum Tempers 10/16/01 26 Aluminum Tempers (cont.) 10/16/01 27 Aluminum Tempers (cont.) 10/16/01 28 Aluminum Comparison Chart Material 2024-T3, T351, T42 Typical Application High Strength Tension Applications. Best Fracture Toughness/Slow Crack Growth Rate and Good Fatigue life. Thick Forms Have Low Short Transverse Properties including Stress Corrosion Cracking. 2324-T3 8% Improvement In Strength Over 2024-T3 With Increased Fatigue And Toughness Properties. 7075-T6, High Strength Compression Applications. T651, Higher Strength Than 2024-T3, But Lower T7351 Fracture Toughness. T7351 has Excellent Stress Corrosion Cracking Resistance and Better Fracture Toughness Than T6. 7050-T7451 Better Properties Than 7075-T7351 In Thicker Sections. 10/16/01 29 Titanium • Better Strength To Weight Ratio Than Aluminum or Steel • Typically Comprises ~5% By Weight in Commercial Aircraft and Up To ~25% By Weight For High Performance Military Aircraft • Good Corrosion Resistance • Good Temperature Resistance • Good Fatigue And Damage Tolerance Properties In The Annealed Form • Typical Alloy Is Ti 6Al-4V Either Annealed or Solution Treated and Aged • High Cost For Metals 10/16/01 30 Steel • Steel May Be Selected When Tensile Strengths Greater Than Titanium Are Necessary • Steel Is Usually Limited to a Few Highly Loaded Components Such As Landing Gear • There Are Many Steel Alloys to Choose From (See Chart); Select the One That Is Tailored for Your Application. 10/16/01 31 Steel (cont.) Mil-Hdbk-5 List of Aerospace Steel Alloys: 10/16/01 32 Composite • The Embedding of Small Diameter High Strength High Modulus Fibers in a Homogeneous Matrix Material • Material Is Orthotropic (Much Stronger in the Fiber Oriented Directions) • Fibers – Graphite (High Strength, Stiffness) – Fiberglass (Fair Strength, Low Cost, Secondary Structure) – Kevlar (Damage Tolerant) • Matrix – Epoxy (Primary Matrix Material) to 250° F – Bismaleimide (High Temp Applications) to 350° F 10/16/01 33 Material Properties Comparison Material 2024-T3 Aluminum 7075-T6 Aluminum 6Al-4V Titanium Annealed 6Al-4V Titanium Solution Treated and Aged 15-5PH Stainless Steel (H1025) Fiberglass Epoxy (Unidirectional) Graphite Epoxy (Unidirectional) Ftu Fty (ksi) (ksi) 64 47 78 71 134 126 Fcy (ksi) 39 70 132 E Density 6 3 (10 psi) (lb/in ) 10.5 .101 10.3 .101 16.0 .160 150 140 145 16.0 .160 154 145 152 28.5 .283 80 60 5 .065 170 140 22 .056 10/16/01 34 Next Generation Materials • Aluminum Lithium • GLARE (Fiberglass Reinforced Aluminum) • TiGr (Graphite Reinforced Titanium) • Thermoplastics • Resin Transfer Molding (RTM) • Stitched Resin Fusion Injected (Stitched RFI) 10/16/01 35 Mil-Hnbk-5 Overview • Document Contains Design Information On The Strength Properties of Metallic Materials and Elements for Aerospace Vehicle Structures. All Information and Data Contained in This Handbook Have Been Coordinated With the Air Force, Army, Navy, Federal Aviation Administration and Industry Prior to Publication and Are Being Maintained As a Joint Effort of the Department of Defense and the Federal Aviation Administration. 10/16/01 36 Basis of Properties • Material Property Selection Is Dependant on the Criticality of the Structural Component – Critical Single Load Path Structure – A Basis (99% Probability of Exceeding) – S Basis (Agency Assured Minimum Value) – Other Primary Structure With Redundant Load Paths – B Basis (90% Probability of Exceeding) – Without a Test, A or S Basis May Be Required – Secondary Structure – B Basis (90% Probability of Exceeding) 10/16/01 37 Grain Direction 10/16/01 38 Material Properties (Mil-Hdbk-5) Example • Type 10/16/01 39 Material Forms Sheet • Rolled Flat Metal Thickness Less Than .25” – Fuselage Skin – Fuselage Frames – Rib and Spar Webs – Control Surfaces – Pressure Domes • Good Grain Orientation • Many Parts and Fasteners • Fit Problems – Straighten Operations – Shims – Warpage 10/16/01 41 Plate • Rolled Flat Metal Thickness Greater Than .25” – Wing and Tail Skins – Monolithic Spars and Ribs – Fittings • Unitized Structure; Fewer Fasteners • Grain Orientation Can Be a Problem • High Speed Machining Has Lowered Fab Costs 10/16/01 42 Extrusion • Produced By Forcing Metal Through a Forming Die At Elevated Temperature To Achieve The Desired Shape – Stringers – Rib and Spar Caps – Stiffeners • Grain Is Aligned in The Lengthwise Direction • Additional Forming and Machining Required • Used In Conjunction With Sheet Metal Webs 10/16/01 43 Forging • Produced by Impacting or Pressing The Material Into The Desired Shape – Large Fittings – Large Frames/Ribs – Odd Shapes • Control Grain Orientation • Residual Stresses Can Cause Warpage • Tooling Can Be Difficult 10/16/01 44 Casting • Produced By Pouring Molten Metal Into A Die To Achieve The Desired Shape – Nacelle/Engine Components – Complex Geometry • Dramatically Lowers Part and Fastener Counts • Poor Fatigue And Damage Tolerance Properties • High Tooling Costs 10/16/01 45 Composite • Produced By Laying Fabric, Laying Tape, Winding, Tow Placement and 3D Weaving or Stitching – Skins – Trailing Edge Surfaces – Interiors and Floors • Properties Can be Oriented To Load Direction • Excellent Strength To Weight Ratio • High Cost Of Material and Processes • Poor Bearing Strength 10/16/01 46 Examples Upper Wing Cover • Skin - 7075-T651 Aluminum Plate • Stringers - 7075-T6511 Aluminum Extrusion • After Machining; Age Creep Formed To -T7351/-T73511 • Compression Dominated • Reduces Compressive Yield Strength • Greatly Increases Stress Corrosion Resistance 10/16/01 48 Lower Wing Cover • Skin - 2024-T351 Aluminum Plate • Tension Dominated • Good Ultimate Tensile Strength • Very Good Fatigue and Damage Tolerance Properties • Stringers - 7075-T73511 Aluminum Extrusion • High Ultimate Tensile Strength • Good Damage Tolerance Properties 10/16/01 49 Spars • 7050-T7451 Aluminum Plate • High Tensile and Compressive Strength in Thick Sections • Good Stress Corrosion Resistance 10/16/01 50 Fixed Trailing Edge Surface • Graphite/Epoxy Fabric • Aramid/Phenolic Honeycomb • Fiberglass/Epoxy Fabric Corrosion Barrier • Secondary Structure • Stiffness Design 10/16/01 51 Leading Edge • 2024-0 Clad Aluminum • Heat Treated to -T62 After Stretch Forming to Shape • Clad For Corrosion Resistance • Polished For Appearance • De-icing by Hot Air/Bird Strike Resistance 10/16/01 52 Landing Gear Support Beam • Titanium 6Al-4V Annealed Forging • High Strength and Stiffness • Critical Lug Design • Height is Limited By Wing Contours • Annealed Form Is Good For Fatigue And Damage Tolerance 10/16/01 53 Wing to Body Attachments • PH13-8Mo Cres Steel Bar • Critical Lug Design • High Strength Requirement • Good Corrosion Resistance 10/16/01 54 Flap Tracks • PH13-8Mo Cres Steel Bar • Geometry Is Very Limited By Requirement To Be Internal To The Wing • Results In Very High Stress Levels • High Stiffness Is Required To Meet Flutter and Flap Geometry Criteria • Good Corrosion Resistance 10/16/01 55