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ISS Pressurized Station Module
Free-free orbital vibration modes, internal atmospheric pressure containment, and launch trunnion g-load stress verification.
Pressurized orbital habitat modules (such as Destiny or Columbus) must withstand 101.3 kPa internal atmospheric pressure, survive 6g longitudinal and 3g lateral launch loads on shuttle/fairing trunnions, and maintain orbital dynamic stiffness when coupled to external truss segments. The model incorporates conical bulkheads, Common Berthing Mechanism (CBM) rings, internal equipment racks with 4.8 t payload, and an external 16-meter square truss. WebCAE computes unconstrained free-free natural frequencies and localized stresses around docking interfaces.
1. Geometry & FEA Mesh
- •Pressure hull: cylindrical barrel R = 2.1 m, length 6.0 m, t = 4 mm aluminum shell, capped by forward/aft truncated cones (2.1 → 1.0 m, t = 5 mm).
- •Docking & hatch closures: CBM annular rings (ruled, t = 12 mm) with box ring stiffeners (100 × 80 × 10 mm) and transfinite quad mesh end hatch covers (t = 30 mm).
- •Framing & interior: 24 longitudinal stringers, ring frames at 1.0 m pitch, suspended honeycomb equipment floor (t = 30 mm), and 14 equipment racks totaling 4,800 kg.
- •External structure: 16-meter square tubular truss (4 bays × 4 m) directly integrated with forward hatch bulkhead nodes on shared mesh vertices.
2. Loads & Boundary Conditions
- •Internal pressurization p = 101.3 kPa applied to barrel, cones, and end hatches with self-equilibrating axial force on end closures.
- •Launch acceleration: 6g axial inertia combined with 3g lateral load applied to 9.46 t system mass supported on 3-point trunnion/keel mounts.
- •Unconstrained free-free orbital vibration mode extraction (free=on) filtering out 6 rigid-body space mechanics translations/rotations.
3. Simulation Results & Findings
- ✓Orbital free-free elastic natural frequencies: f₁ = 3.916 Hz and f₂ = 4.139 Hz (coupled module-truss bending with 14 lumped rack masses).
- ✓Barrel membrane hoop stress σ_θ = 53.15 MPa and axial stress σ_x = 26.58 MPa match thin-shell analytical reference within 0.05%.
- ✓Zero topology gaps verified across all conic-to-barrel transitions and hatch disc boundaries (shellcheck = 0).
Space hardware developers leverage WebCAE to rapidly assess module primary structure frequencies, rack payload placement, and trunnion peak launch stresses in an ultra-responsive web environment. Fully solved .caeweb orbital cases enable international space consortium partners to examine dynamic modes and local stresses without specialized software licenses.
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