Structural evaluation of a vertical tail for a supersonic vehicle: architecture, boundary conditions and material system influence

Supersonic aircraft are defined as aircraft that can travel at speeds above the speed of sound (M>1). For these aircraft, correct dimensioning is essential to enable them to withstand the high aerodynamic loads they face. This study evaluates the impact of internal architecture, boundary conditions and material on the dimensioning of the vertical tailplane when subjected to a gust load. The optimal configuration is the one that achieves a balance between weight and structural performance. Titanium alloy Ti 6AI-4V and carbon/carbon composites are selected as the most suitable materials for this application due to their known high temperature resistance. The best configuration, although it weighs 20% times more than the composite configuration, manages to achieve a reduction in tip displacement of 80%, significantly improving strength and instability performance.