The application of system identification methods to high-bandwidth rotorcraft flight control system design is examined. Flight test and modeling requirements are illustrated using flight test data from a BO-105 hingeless rotor helicopter. The proposed approach involves the identification of nonparametric (transfer function and state space) model identification. Results for the BO-105 show the need for including coupled body/rotor flapping and lead-lag dynamics in the identification model structure to allow the accurate prediction of control ssytem bandwidth limitations.
System identification requirements for high-bandwidth rotorcraft flight control system design
1991 American Control Conference ; 1991 ; Boston, MA, United States
1991-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Flight requirements for operation of rotorcraft
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