Inertial Measurement Unit and External Influence Duration

Abstract

After a short discussion of the main specific points of existing air navigation schemes with relation to external disturbing influences, some new approach to analyze in the view of admissible temporal and spatial frames basic principle on which the simplest accelerometer may be constructed is proposed. It is shown that a strict successive analysis of accelerometer measurement procedure makes it possible to understand probable new source of errors in the value estimation of the disturbing force magnitude. If do not take into account these new possible errors any self-adjusting system of an airplane may be functionally unreliable. These errors arise only when temporal duration of disturbing force is less than some critical time τ, which depends on the given characteristics of an aircraft Inertial Navigation System and aircraft itself. The method of finding τ is proposed.