Inspect pre-solved models in your browser in 2 seconds (up to 300k DOF) or solve 1.5M+ DOF assemblies 100% offline on Windows and macOS.
Machined Dual-Lug Wing Attachment Fitting
Limit flight load pin bearing and pocket stress concentration validation for primary airframe wing-to-fuselage attachment.
Primary wing-to-fuselage attachment fittings transfer immense cantilever wing root shear and bending moments through shear pin joints and bolt patterns into heavy fuselage ring frames. High contact bearing stresses inside the pin holes combined with stress concentrations around CNC weight-relief pocket fillets govern the static strength and damage tolerance margins. This simulation evaluates the multi-axial stress tensor and pin bearing distribution under 225 kN design ultimate flight limit tension.
1. Geometry & FEA Mesh
- •Aerospace aluminum-zinc alloy 7050-T7451 plate (E = 71.7 GPa, ν = 0.33, yield strength 469 MPa).
- •High-precision 5-axis CNC-machined monolithic fitting with dual Ø35 mm pin clevis lugs and 18 mm lug thickness.
- •Four thin-walled milled weight-reduction pockets with 3.5 mm web thickness and 8 countersunk Hi-Lok fastener holes.
- •Tetrahedral mesh featuring 104,200 elements and 78,300 active degrees of freedom, refined at pin contact boundaries.
2. Loads & Boundary Conditions
- •Fixed constraint on the seating faces and cylindrical walls of the 8 base flange Hi-Lok fastener holes.
- •Bearing cosine pressure distribution with resultant tension force F = 225 kN applied across the forward semicircles of both Ø35 mm pin bores.
- •Auxiliary transverse shear stabilizing force of 12 kN applied to the side flange.
3. Simulation Results & Findings
- ✓Peak von Mises stress σ_vm = 237.1 MPa located at the inner tang blend radius between the dual lugs and the pocket base.
- ✓Maximum displacement magnitude |u| = 0.176 mm at the extreme tips of the dual attachment lugs.
- ✓Safety factor SF = 1.98 against material yield, ensuring complete compliance with aerospace FAR / CS-25 structural requirements.
Aerospace structural engineers evaluate weight-critical milled parts in WebCAE in real time right during CAD drafting sessions. Instant stress feedback inside the browser eliminates iterative simulation ticketing queues and speeds up airframe weight optimization.
14 days of full Pro access. The first charge occurs only after 14 days unless canceled beforehand.
- ✓14-Day Trial ($0 Today) (cancel anytime)
- ✓Up to 1.5M+ DOFs (direct sparse solver)
- ✓Native Windows & macOS Apps (100% offline)
- ✓Nonlinear Contact & Buckling (Kσ, MITC4, RBE2/RBE3)
Ask an Engineer About Your Model
Describe your part, load case, or CAD format — we reply within 2 business hours.
Want an instant answer on FEA theory or this model?
Click the AI chat button in the bottom-right corner to ask about boundary conditions, stress criteria, mesh convergence, or DSL scripting.
More Engineering Simulation Cases
Transport Aircraft Airframe
Fuselage Barrel Section with Door Cutout
ISS Pressurized Station Module
