چكيده لاتين :
This paper is concerned with the mathematical model development issues necessary
for better prediction of dynamic responses of articulated rotor helicopters.
The methodology is laid out based on mathematical model development for
articulated rotor helicopters, using the theories of aeroelastisity, finite element
and the time domain compressible unsteady aerodynamics. The helicopter
is represented by a set of coupled nonlinear partial differential equations for
the main rotor within nonlinear first order ordinary differential equations
representation, describing the dynamics of the rest of the helicopter. The
complexity of the formulation imposes the use of numerical solution techniques
for dynamic response calculations. The validation is performed by comparing
simulated responses to flight test data for a known configuration. The results
show improvement in dynamic response prediction of both on-axis and crosscoupled
responses of helicopter to pilot inputs.
