Abstract

The main specific points of existing air navigation schemes with relation to external disturbing influences are discussed. 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 don’t take into account these new possible errors any self-adjusting system of an airplane may be functionally damaged or at least 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 discussed.

Highlights

  • Introduction to InertialNavigation http://www.navlab.net/Publications/Introduction_to_Inerti al_Navigation.pdf [7] D

  • Inertial Navigation System play anxiously position the terrorist incidents in civil aviation which important role in the modern aviation

  • Inertial sensors comprise within one theoretical framework and elaborate accelerometers, which measure specific force and mathematical tools to construct admissible gyroscopes commonly abbreviated to gyros, which diagnostic procedures

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Summary

INTRODUCTION

Because of plethora of as mentioned and omitted anxiously important. The problems of navigation accuracy whose roots problems we should restrict ourselves to the analysis lay back in the mid-twentieth century should be the most widespread inescapable external disturbing extended to meet the new challenges. Amongst influences which of them differs of each other in the these well-known challenges we would mention temporal duration. Enormously high frequency of flights, continuously disproving environmental conditions, problems with

INERTIAL NAVIGATION SYSTEM airport landing and we should place in the first
INERTIAL MEASUREMENT UNIT ACCELEROMETERS AND INFLUENCE DURATION
CONCLUSIONS
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