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aircraft-structures-expert

Expert-level aircraft structures covering structural design philosophy, wing and fuselage analysis, fatigue and damage tolerance, composite structures, and certification.

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SKILL.md(원문)

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Aircraft Structures Expert

Before Starting

  1. Which structural component? (wing, fuselage, empennage, landing gear)
  2. Metallic or composite structure?
  3. Static strength or fatigue and damage tolerance?

Core Expertise Areas

Structural Design Philosophy

Safe life: retire structure before fatigue failure with safety factor on life. Fail safe: multiple load paths, single failure does not cause catastrophic failure. Damage tolerant: assume crack exists, inspect before crack reaches critical size. Limit load: maximum load expected in service, no permanent deformation. Ultimate load: limit load times 1.5 factor of safety, no failure.

Wing Structural Analysis

Box beam: front and rear spars with upper and lower skins carry bending and torsion. Bending: spars and skin carry span bending moment as axial loads. Torsion: closed section resists torque, shear flow q = T over 2A. Shear: spars carry vertical shear force. Idealized section: lumped flange areas and shear-only webs for analysis.

Fatigue and Damage Tolerance

S-N curve: stress amplitude vs cycles to failure, endurance limit for steel. Stress concentration: Kt amplifies nominal stress at holes and fillets. Miner rule: cumulative damage, sum of ni over Ni equals 1 at failure. Crack growth: Paris law da over dN = C times delta K to the m power. Critical crack size: fracture toughness KIc = sigma sqrt pi a times geometry factor.

Composite Structures

Laminate theory: stiffness from fiber orientation and stacking sequence. Failure modes: fiber failure, matrix cracking, delamination, buckling. First ply failure: weakest ply fails first, progressive damage to final failure. Impact damage: BVID barely visible impact damage, strength reduction allowed. Lightning strike: conductive mesh or expanded foil protection required.

Best Practices

  • Design for damage tolerance not just static strength
  • Establish inspection intervals before entering service
  • Test representative coupons and elements before full scale testing
  • Use conservative material allowables from statistically valid data

Common Pitfalls

PitfallFix
Ignoring stress concentration at fastener holesApply Kt in fatigue analysis at every hole
Wrong laminate stacking for fatigueAvoid grouping same-angle plies, interleave
Underestimating composite impact sensitivityTest impact damage tolerance explicitly
Missing combined load interactionCheck all load combinations not just individual peaks

Related Skills

  • aerodynamics-expert
  • mechanics-of-materials-expert
  • manufacturing-processes-expert

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