Design and Evaluation of Dynamic Flight Test Maneuvers

摘要

Longitudinal and lateral control input signals were evaluated in flight using an automatic control system. Significant differences between the performance of different types of control input signals are shown to exist. A technique for the optimization of control input signals with respect to norms of the information matrix is described. It is shown that in linear systems the computational effort required for the optimization can be significantly reduced by computing and storing a set of so-called elementary information matrices. The parameter-state estimation problem of dynamic flight tests is discussed in the linear and in the nonlinear case. It is shown that under certain conditions the parameter-state estimation problem can be solved in two consecutive steps pertaining to the reconstruction of the state and the estimation of the aerodynamic model parameters respectively.