An identification methodology is presented for identifying rotor parameters from nonlinear transient response. The identification model is developed using finite elements in space with approximation of distributed parameters and finite elements in time. Response sensitivities are efficiently calculated from the resulting mulit-stage model and used in a quasilinearization identification scheme. It is assumed that modal responses are obtained using multiple sensors in a kinematic filtering scheme to permit modal reduction. The method is validated via numerical simulations of coupled flap and lag bending motion of a rotating blade in vacuum. It a was found to be effective in identifying unknown parameters. The method also efficiently accommodates multiple erroneous initial conditions when using several sets of transient responses.
Identification of nonlinear helicopter rotor structural dynamics
Identifizierung nichtlinearer Strukturdynamik von Hubschrauberrotoren
1994
7 Seiten, 5 Bilder, 3 Tabellen, 20 Quellen
Conference paper
English
Structural dynamics of a helicopter rotor blade system
Tema Archive | 1990
|Linear and Nonlinear Damping Identification in Helicopter Rotor Systems
British Library Conference Proceedings | 1998
|Identification of Structural Damping of a Helicopter Rotor Blade
British Library Conference Proceedings | 1993
|