A New Heuristic Approach to Rotorcraft System Identification

High-fidelity rotorcraft flight simulation relies on the availability of a quality model that further demands good level understanding complexities arising from aerodynamic couplings and interference effects. This paper explores dynamics in low-speed regime where such abound presents new heuristic approach time domain to aid identification nonlinear fidelity assessment. The identifies parameters "additively," based their contribution local dynamic response system, contrast with conventional approaches parameter values are identified minimize errors over whole maneuver. In these early investigations, low-order, rigid-body, linear models show comparison flight-test data. is extended explore nonlinearities attributed so-called maneuver wake distortion skew effects emerging larger maneuvers. results correlation for proposed structure, demonstrated by its capability capture variations stability control derivatives magnitude.