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Objective — Design and validate CFRP panels with stringers, minimizing weight while meeting buckling and damage-tolerance requirements under the defined load cases.
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Objective — Simulate a UD laminate under tension and compression using Hashin damage initiation to identify ply-by-ply failure and compare tensile vs compressive capacity.
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Objective — Define composite skin and stringer concept, reinforcements, drop-offs, and frame joints (clips, Ø4.8 mm) for a fuselage bay between Frames A–B.
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Objective — Design the lightest possible rear saddle frame within the boundary envelope, load-case compliant (static + fatigue), manufacturable by SLM (AlSi10Mg).
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Objective — Define laminate schedule and thicknesses to minimize weight while maintaining stiffness and strength on a composite drone frame, with harmonic and impact checks on critical members.
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