Structural dynamic and aeroelastic analyses are based on a finite element model of the aircraft. This model is used to compute flexible maneuver loads, flutter and divergence speeds and response due to gusts.
Response to pilot inputs when the closed loop control system is in operation are obtained from aeroservoelastic (ASE) analyses based a combination of aircraft and control system models.
The above analyses also play an important role during preliminary
design of the aircraft by providing design data at various levels of integration.
Copyright @ 2001-2003, Aeronautical Development Agency, Bangalore
Aeronautical Development Agency, Ministry of Defence, Govt. of India, P.B.No: 1718, Vimanapura Post, Bangalore 560017, India
