Results are presented on the design of aircraft inputs (i.e. elevator, rudder and aeleron deflection time histories) to identify aircraft stability and control derivatives from flight test data. The problem is first reduced to an optimization problem with differential and integral constraints. The criteria used are either expressed in terms of the Cramer-Rao lower bound on the covariance matrix of the parameter estimates or in terms of the maximum prediction error variance. Both time-domain longitudinal and lateral dynamics of C-8 and Jet Star aircrafts and comparison with doublet type inputs are made.
Status of input design for aircraft parameter identification
1975-05-01
Conference paper
No indication
English
Application of optimal input synthesis to aircraft parameter identification
Tema Archive | 1976
|British Library Conference Proceedings | 1994
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