Aircraft Parameter Estimation: Successive Steps
Résumé
System identification based on physical laws often involves parameter estimation. Before performing estimation problem, it is necessary to investigate its identifiability. A signifiant increase in accuracy of the parameter estimation may be obtained by a suitable choice of experimental conditions.
This paper considers a model describing aircraft dynamics. Our contribution consists in solving the problem of optimal design. Then two successive steps are used to solve this problem. The first one is based on dynamic programming and the second one solves an optimization problem by a gradient algorithm using the results of the previous method.