Abstract
The high-precision correction problem of navigation information for a small unmanned aerial vehicle flying with altitude changes over a wide range is studied. Numerical criteria of parametric identifiability degreefor one class of nonlinear systems represented by the SDC method are considered. Error models for inertial navigation system of various detail levels are studied and the results of mathematical and semi-natural modeling of a nonlinear Kalman filter with different models are presented. Keywords small unmanned aerial vehicle, inertial navigation system, errors, correction, degree of parametric identifiability, nonlinear Kalman filter, SDC method
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