Characterization of Advanced Composite Materials MSE 597 Junior Senior Graduate

Characterization of Advanced Composite Materials MSE 597 Junior/Senior/Graduate Students Lecture-Laboratory Course

Today: R&T delivery to A 380. Some examples of successful research Carbon Composite Section 19 Flap vortex generators Horizontal tail plane designed for relaxed stability Automated wing assembly High Re (Reynolds Number) Wing Design Upper fuselage skin in GLARE Extensive use of Knowledge Based Engineering New front Fuselage concept Full double deck fuselage Electro-hydraulic actuators Variable frequency power Bonded generation metallic outwing box Dual air conditioning pack concept Integrated and modular avionics architecture (IMA) On board maintenance system Centre wing box in CFRP 2 hydraulic (5000 ) + 2 electrical psi channel architecture for flight controls and landing gear New four post main landing gear (4 -6 -6 -4 wheels configuration) Skin to Stringer Welding (first on A 318) Technologies have to be developed generally and then applied on products

Today’s Test and Certification Methodology Plus (3) D 4 Improved Concepts Plus Added Environmental Coupons (C 4) Test Locations: Long Beach Seattle NASA (5) Plus (2) C 2 Environmental Compression (2+DSD Panels) DDTA 3 Stringer Runout Panel (8) DDTA D 2 Postbuckling Specimen Tension DDTA 16 Spar Cap Longitudinal Shear Panel DDTA 1 Upper Cover Splice Specimen (1) DDTA 20 Rib Clip Pull-off Specimen DDTA E 2 Hi-Load Panels (1) DDTA A 2 Repair Panel DDTA F 1 Substructure Shear Specimen (2) Plus (2) C 1 Environmental Plus (12) G 1 Darted Spar Caps (5) (7+4) Plus (4) D 1 Buckling Elements (13+3) DDTA 6 Upper Cover Compression Panel DDTA 5 Flap Support Box DDTA 9 Bulkhead Shear Clip Specimen DDTA 19 Skin Ply Drop-off (2) (4) (7+2) (1) ( ) - Number of Tests - Testing Complete - Work Stopped

Unidirectional Fiber Prepreg Laminates Fibers appear as ovals because they were cut at an angle to the 0º direction. 0. 0003 In. Diameter Carbon Fiber 0. 005 In. Thick Ply Figure 4 - Laminate Construction

Composite Principal Coordinate System

Characterization with electrical resistance stain gages

Composite Laminate Tensile Tests

Course Description The characterization of advanced composite materials is a combined lecture/laboratory course in which polymeric composite laminates will be fabricated of carbon fiber epoxy and subjected to classical test methods appropriate to the determination of the anisotropic, thermoelastic properties. Properties measured will include thermal expansion coefficients, anisotropic elastic constants, biaxial strength properties and interlaminar fracture strengths. The autoclave processing of composite laminates will be discussed and the consolidation, degree of cure and glass transition temperature of the polymeric matrix will be modeled. Microscopic analysis of the composite will be carried out to observe microstructure and measure composition fractions. Lectures will precede each experiment.

Laboratory Experiments • • • Fabricate Graphite Epoxy Laminates Microscopic Determination of Volume Fractions Uniaxial Tension Test: Strength and Modulus Off-Axis Tension Test: Biaxial Strength Shearing Property Test Thermal Expansion Properties: Anisotropic Laminate Tension Test: Strength and Modulus Mode I Interlaminar Fracture Mode II Interlaminar Fracture

Course Format • • Wednesday –Lecture (1 hour) Thursday- Laboratory Prep (1 hour) Friday Morning Laboratory (3 hours) Laboratory Reports and Final Exam