Analysis of aspect and taper ratio on aeroelastic stability of composite shells

Abstract

In the present paper, the dynamic and static stability of composite shells for different aerodynamic configurations is investigated. Based on the existing models for flutter and torsional divergence, modified to include material anisotropy, stability parameters have been calculated for different aspects and taper ratios of the lifting (control) surface configurations. It was found that the methodology presented is a very effective method for stability analysis in preliminary design phases when a large number of cases have to be analyzed from the aspect of aerodynamics and flight conditions.

Keywords

• static stability
• divergence
• flutter
• dynamic stability
• computational flutter analysis
• composites