Abstract
Longitudinal stability and tontrol derivatives of a fightlfr aircraft are estimated by output error method for different types of input excitation. The uncertainties in the parameters are computed by cortfcting Cramer-Ra(j) bounds using fudge factor. In general, the step input response data is not usedfor estimating the derivatives. Therefore, step response time history trajectories were cross-validated using tIle estimated derivatives for standard inputs like doublet and 3211. This proves that the model parameters are estimated with high confidence. By appropriately choosing the mathematical modeland using the corrected flight data for bias and scale factor errors by compatability check for parameter estimation proves beyond doubt that such a procedure can be adopted for estimating stability and control derivatives of any aircraft.
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