A technique is investigated for the optimal design of helicopter control inputs, in order to provide the most accurate parameter estimates. An existing software package for optimal input design for fixed wing aircraft was modified to design control inputs for rotary wing aircraft. The design issues are discussed with some inherent problems of helicopter dynamics in mind. Helicopters differ from fixed wing aircraft by being typically unstable, and have more dynamic modes (translation, rotation, blade modes plus inflow dynamics). A high degree of coupling also exists between the blades, longitudinal and lateral forces/moments. The design technique encompasses the salient features of Mehra's design technique in the frequency domain (using convex analysis) with the two step method for decoupling state and parameter estimation. The input design is performed for power constrained inputs by optimizing a norm of Fisher's information matrix. The results are presented for the BO-105 helicopter, using data supplied by DLR (Deutsche Luft- Raumfahrttechnik), Braunschweig Germany. This work was undertaken during an ERASMUS exchange with the Stability & Control Group, Faculty of Aerospace Engineering, Delft University of Technology in The Netherlands.
Experience with optimal input design for helicopter parameter identification
Versuchsplanung für die Identifikation eines Hubschraubermodells
1997
13 Seiten, 7 Bilder, 3 Tabellen, 12 Quellen
Aufsatz (Konferenz)
Englisch
Experience with Optimal Input Design for Helicopter Paramater Indetification
British Library Conference Proceedings | 1997
|Practical aspects of helicopter parameter identification
AIAA | 1984
|Optimal input design for aircraft parameter estimation
Elsevier | 2005
|Helicopter Aerodynamic Parameter Identification via Flight Dynamics
Tema Archiv | 2013
|Helicopter Aerodynamic Parameter Identification via Flight Dynamics
Trans Tech Publications | 2013
|