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Aerospace Clevis, Lug & Shear Pin Joint
Multi-body contact stress distribution and shear load transfer analysis across aircraft actuator attachment lugs.
Pin-clevis attachment joints serve as primary load paths in aircraft flight control actuators, landing gear linkages, and wing flap deployment mechanisms. Under high tensile loads, load transfer across the pin creates complex non-uniform bearing pressure distributions, pin bending, and localized stress peaks in the lug holes. Inadequate edge distance or improper pin sizing causes pin shearing or lug tensile tear-out. This 3-body FEA simulation analyzes load transfer through two independent cylindrical contact zones under a 20 kN actuator pull force.
1. Geometry & FEA Mesh
- •3 independent B-Rep solid bodies: dual-ear clevis fork, central rod eye lug, and cylindrical shear pin (Ø20 mm).
- •Dissimilar materials: high-strength structural alloy steel AISI 4340 (E = 205 GPa, ν = 0.30, yield 860 MPa) for clevis fork; aerospace aluminum 7075-T6 (E = 71 GPa, ν = 0.33, yield 503 MPa) for rod eye lug; precipitation-hardened stainless steel 17-4PH H900 (E = 196 GPa, ν = 0.27, yield 1170 MPa) for shear pin.
- •Solid tetrahedral mesh with 58,147 elements, 12,871 nodes, and 38,613 active DOFs across all 3 components.
- •Dual penalty contact pairs defined between pin cylindrical surface and inner cylindrical bores of clevis ears and eye lug.
2. Loads & Boundary Conditions
- •Clevis fork shank base face fully fixed (Ux = Uy = Uz = 0) to ground the assembly.
- •20.0 kN tensile axial pull force applied across the rear mounting face of the aluminum rod eye lug.
- •Kinematic constraint prevents axial walkout of the pin while allowing free contact slip and radial deformation.
3. Simulation Results & Findings
- ✓Maximum von Mises stress σ_vm = 59.8 MPa localized at the inner contact bore shoulder of the aluminum lug under bearing pressure.
- ✓Maximum pin shear stress is well within allowable shear limits for 17-4PH, yielding a structural safety factor SF > 8.0.
- ✓Maximum total displacement magnitude |u| = 0.0353 mm (0.035 mm) occurring at the loaded eye lug end.
- ✓Solved in 0.16 s with stable contact convergence across both cylindrical contact pairs.
Aviation structure teams evaluate multi-body pin-lug load distributions and bearing clearances in real time in WebCAE. Resolving contact slip and localized bearing peaks in sub-second runtimes avoids over-conservative analytical margins, enabling lighter airframe hinge brackets.
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