The emergency slides in modern transport aircraft must always deploy in an emergency but must never deploy in flight. CRM Engineering Services was tasked with validating the advanced composite structure containing the emergency slide off the wing.
The structure supporting electronics modules in aircraft and spacecraft must be carefully designed to withstand a harsh shock and vibration environment.
The vibration environment for airborne structures can often be characterized by a random vibration of the attach points, the inertial loads, and acoustic pressure.
Fastening designs for laminated composites must be examined carefully to prevent cracks from propagating. In this engagement, CRM Engineering Services performed a parametric study of countersunk hole for a SHCS in a laminated composite plate. We determined the stress concentration factors for assumed crack sizes, shapes, and plate thicknesses using the Extended Finite Element Method (XFEM).