AI and Parametric Finite Element Modeling for future Aerospace Engineering

HelixCS generates structured and unstructured hex/tet topologies from parametric geometry definitions. Mesh density is driven by curvature, load path criticality, and user-defined refinement zones — producing analysis-ready models without manual mesh editing.

Multi-body contact modeling supports bolted joints, bonded interfaces, and sliding contact pairs. Composite laminate layup is defined at the ply level, with automatic orientation mapping to curved shell elements.

Export targets include NASTRAN (BDF), ABAQUS (INP), and ANSYS (CDB) formats. Model quality metrics — aspect ratio, Jacobian, skewness — are reported automatically with flagged elements highlighted for review.

Surrogate models are trained on parametric sweeps of the full-order FEM, learning the mapping from design parameters and boundary conditions to stress tensor fields, modal frequencies, and displacement responses.

Transfer learning enables rapid adaptation across configuration variants — a surrogate trained on a baseline wing can be fine-tuned for a modified planform in hours rather than days.

At runtime, the surrogate screens thousands of load cases in seconds, flagging critical cases for full-order verification. This reduces the number of expensive FEM solves by 95–99% while maintaining certification-grade accuracy on the cases that matter.

FAR 25 / CS-25 flight envelope: maneuver loads, gust loads, ground loads, pressurization, and emergency landing conditions. Cases are generated parametrically from aircraft weight, CG, and flight condition inputs.

Stress outputs include Von Mises, principal stresses, and shear stress distributions across all structural members. Margin of safety is computed automatically for metallic and composite elements, with reserve factors.

Fatigue and damage tolerance analysis follows MIL-HDBK-5 / MMPDS for metallic structure and MIL-HDBK-17 for composites. Crack growth predictions use NASGRO and AFGROW-compatible material databases.

VTOL airframes present unique structural challenges: distributed propulsion systems introduce multiple simultaneous load paths, rotor-induced vibration creates high-cycle fatigue conditions, and multi-modal flight envelopes (hover, transition, cruise) require envelope-spanning load case coverage.

HelixCS includes dedicated VTOL load case libraries covering hover thrust asymmetry, transition maneuvers, emergency autorotation, and hard landing conditions. Rotor hub loads are imported directly from flight dynamics models in FLIGHTLAB or CAMRAD II format.

Lightweight composite optimization targets minimum weight subject to strength, stiffness, and aeroelastic stability constraints. Topology optimization identifies efficient load paths for novel VTOL configurations where no historical precedent exists.