This paper investigates a technique 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. The design technique encompasses the salient features of Mehra's design technique in the frequency domain (using Convex Analysis) with Mulder's technique 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, Germany.
Experience with Optimal Input Design for Helicopter Paramenter Identification
1996
28 pages
Report
No indication
English
Aircraft , Avionics , Aerodynamics , Helicopter control , Control systems design , Dynamical control , Parameter identification , BO-105 helicopter , Rotary wing aircraft , Frequency domain , State estimation , Moments , Maneuverability , MIMO(Control systems) , Dynamical systems , Foreign technology , Optimal design
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