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Aerospace Structures

The design and analysis of airframes, spacecraft, and launch vehicle structures. Aerospace structures must withstand extreme loads while minimizing weight - a challenge met through advanced materials like composites, titanium alloys, and innovative structural design.

Key Facts

  • Aerospace structures prioritize high strength-to-weight ratio above all else
  • Carbon fiber reinforced polymers (CFRP) can be 5x stronger than steel at 1/5th the weight
  • Titanium alloys (Ti-6Al-4V) are used for high-temperature areas: engine mounts, leading edges, and landing gear
  • Fatigue failure accounts for the majority of structural failures in aircraft - cracks grow under cyclic loading
  • Monocoque and semi-monocoque designs use the skin as a primary load-bearing structure
  • Wing structures use spars (bending loads), ribs (shape maintenance), and stringers (buckling resistance)
  • Thermal protection systems for re-entry must handle temperatures exceeding 1,600°C
  • Damage tolerance design philosophy assumes cracks exist and ensures they grow slowly enough to be detected

Fundamental Equations

Stress

σ=FA\sigma = \frac{F}{A}

Normal stress: force per unit cross-sectional area.

Strain

ε=ΔLL0\varepsilon = \frac{\Delta L}{L_0}

Engineering strain: change in length divided by original length.

Hooke's Law

σ=Eε\sigma = E \varepsilon

Linear elastic stress-strain relationship, where E is Young's modulus.

Euler Buckling Load

Pcr=π2EI(KL)2P_{cr} = \frac{\pi^2 E I}{(KL)^2}

Critical compressive load at which a column buckles, dependent on material, geometry, and end conditions.

Paris Law (Fatigue)

dadN=C(ΔK)m\frac{da}{dN} = C (\Delta K)^m

Crack growth rate per load cycle as a function of stress intensity factor range.

Stress Intensity Factor

K=YσπaK = Y \sigma \sqrt{\pi a}

Characterizes the stress field near a crack tip; Y is a geometry factor, a is crack length.

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