Flight dynamics helicopter model validation based on flight test data

In the current paper, a new technique for a helicopter model estimation based on flight test data is presented. The state space helicopter models, for different flight conditions, are computed. The method is automatic and is applied when one knows the motion parameters types x, y, and u of a real helicopter and in the absence of any seed matrices. The method is highly convergent, and very good results are obtained for all flight cases. In the introductory part, a bibliographic research is carried on, and the necessary data collection is presented. In the next step, the preliminary estimation of seed matrices, for state-space representation is performed using a non-linear model and small perturbation theory. The last paragraph deals with the seed optimization with respect to different flight conditions. In the end, the model validation and the conclusion on possibilities to further develop and use the present methodology is investigated.