This paper outlines the development of a mathematical model that is expected to be useful for rotorcraft flying qualities research. A computer model is presented that can be applied to a range of different rotorcraft configurations. The algorithm computes vehicle trim and a linear state-space model of the aircraft. The trim algorithm uses non linear optimization theory to solve the nonlinear algebraic trim equations. The linear aircraft equations consist of an airframe model and a flight control system dynamic model. The airframe model includes coupled rotor and fuselage rigid body dynamics and aerodynamics. The aerodynamic model for the rotors utilizes blade element theory and a three state dynamic inflow model. Aerodynamics of the fuselage and fuselage empennages are included. The linear state-space description for the flight control system is developed using standard block diagram data.
Model for Rotorcraft Flying Qualities Studies
1993
16 pages
Report
Keine Angabe
Englisch
Aircraft , Aeronautics , Aerodynamics , Computerized simulation , Flight characteristics , Helicopter performance , Mathematical models , Aerodynamic characteristics , Dynamic models , Helicopter control , Rotary wing aircraft , Aerodynamic forces , Algorithms , Flight control , Fuselages , Rotor dynamics , Tail assemblies
A model for rotorcraft flying qualities studies
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