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  • Author: Pjotrs Trifonovs-Bogdanovs x
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Analysis of the Strapdown Inertial Navigation System (SINS) Error Genesis

Abstract

Analysis and simulation of the Strapdown Inertial Navigation System (SINS) error genesis revealed that the East Feedback Contour has the greatest influence on the development of an error in this model, and angular velocity sensor Δω𝒚 is the critical element. In order to prevent the development of an error, structural correction in the East Feedback Contour, and elements that are more critical, namely in angular velocity measurement sensors is the best option.

Open access
Algorithm of Analytical Bank-And-Climb Gyro Unit Without a Heading Gyro

Abstract

An analytical bank-and-climb gyro unit supplies the flight crew with information about aircraft angular movement relative to the local vertical. This article describes the particular principles of unit operation providing a step by step explanation of principles governing the operation of the analytical bank-and-climb gyro unit and provides a kinematic scheme of the unit. The article also gives an insight into the occurrence of errors in the bank-and-climb gyro unit as well as explains their significance.

Open access
Structural Correction of Inertial System Circuit

Abstract

Inertial system errors in case of using the new structural correction method have been determined. Inertial system errors, which determine the kinematic parameters of aircraft movement, are finally generated in the computing circuit. This is the part of inertial system structure which is presented as a closed loop with a feedback. The forward circuit of the main loop consists of several velocity and distance integrators connected in series. Accelerometer signal corrections are calculated in the feedback loop. New corrective circuits have been introduced to the inertial system structure. And the errors of the changed system have been determined. The structural corrective circuits got signals from exterior onboard navigation systems. The conducted research has shown that the use of structural corrective circuits in some cases leads to a considerable decrease of inertial system errors. It means that the new structural method of inertial system correction provides positive results. Further research of inertial system errors should be conducted for the case of its full structure.

Open access
Dynamic Model of Aircraft Landing

Abstract

This manuscript presents a research method that will be used in the development process of avionics equipment. A special device predicting braking and take-off distances will help pilots and provide a complex increase of flight safety and decrease of some types of charges.

Open access