Airframe Structural Sizing Automation

Abstract:
Determining the optimum cross section for each primary structural member of an airframe structure has always been an iterative process since changing the stiffness of one member redistributes loads. Each iteration of internal loads calculations with a global aircraft finite element model (GFEM) followed by strength and stability checks results in further cross section changes (sizings) to reduce weight or regain positive margins of safety. The handoffs between tools and the update process for the next iteration is time consuming and has many opportunities for errors. This paper will describe a tool developed at Sikorsky to automatically iterate sizings saving development time and executing more sizing iterations than historically possible which saves weight. The tool can operate on metallic and composite structures. The development time and weight savings is critical to support ever shrinking time to fielding/market for commercial and military models.

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