Abstract
The basic operation principles of the strapdown inertial navigation systems (SINS) without platform and models of the measuring sensors errors, including offsets of zero signals, errors of scale factors and cross-links connections, are considered. The influence of various components of these errors and their linear combinations on the numeration accuracy of coordinates, velocity and orientation angles is investigated by the method of mathematical modeling of the SINS operation at one and a half hour intervals. To assess the linear properties of SINS algorithms, a quantitative measure is introduced — the value of the numeration error deviation, caused by a linear combination of input errors, relative linear combination of errors caused by separate input errors, as a percentage is expressed. Numerical estimates for typical trajectories of a maneuverable aircraft are obtained for this value. The obtained results can serve as the basis for the formation of technical requirements, used at the design and testing of aviation navigation systems and complexes. Keywords strapdown inertial navigation system, potential of the gravity field, gravitational acceleration, apparent acceleration, numeration errors, math modeling
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