Dynamic and aeroelastic analysis of a trasnport aircraft

Abstract

The dynamic and aeroelastic characteristic of a transport aircraft has been established using MSC/NASTRAN. Correlation of the dynamic characteristics of the aircraft obtained from analysis with the Ground Vibration Test results of the aircraft is studied. The doublet lattice method has been used to estimate the appropriate unsteady air loads generated on the lifting surfaces of the aircraft. In an attempt to realize the realistic flutter margins, the analysis results of the aircraft for the control surfaces rotational modes have been tuned to the Ground Vibration Test results after establishing the first cut analysis results. Flutter analysis of the complete aircraft has been carried out by both PK and KE methods and the critical flutter velocities have been evaluated. The flutter margins for the aircraft are established with respect to the FAR 25 requirements. All the considered aircraft configurations have been found to satisfy the FAR 25 requirements and have been subsequently cleared from flutter criteria with substantial flutter margins