Analytical Solution of Linear Differential Error Equations of Strapdown Inertial Navigation System, Functioning in the Normal Geographic Reference Frame, for the Case of an Object, Following the Geographical Equator

Analytical solution of linear differential error equations of the strapdown inertial navigation system, functioning in the normal geographic reference frame, for the object, following the Earth equator with constant speed and on the constant height, is derived. The solution is represented in the form, which is convenient for the analysis. The roots of the auxiliary equation are derived in the explicit form. Obtained results can be used, for example, for analysis of the accuracy of strapdown inertial navigation system.