A Novel Method of In-Motion Gyrocompass Alignment for a Marine Fiber Optic Gyro Strapdown Inertial Navigation System

2016 ◽  
Vol 13 (8) ◽  
pp. 5499-5512
Author(s):  
Qian Li ◽  
Wei Gao ◽  
Guochen Wang ◽  
Jiubin Tan
Keyword(s):  
Navigation System ◽  
Inertial Navigation System ◽  
Fiber Optic ◽  
Inertial Navigation ◽  
Strapdown Inertial Navigation System ◽  
Fiber Optic Gyro ◽  
Novel Method ◽  
Strapdown Inertial Navigation

scholarly journals Evaluation of permissible amplitudes of external impact on free-of-platform inertial navigation systems

2021 ◽  
pp. 38-43
Author(s):  
Sergii Pogorilov ◽  
Valerij Havin
Keyword(s):  
Navigation System ◽  
Ring Laser ◽  
Inertial Navigation System ◽  
Fiber Optic ◽  
Natural Frequencies ◽  
Inertial Navigation ◽  
Strapdown Inertial Navigation System ◽  
Navigation Systems ◽  
Inertial Navigation Systems ◽  
Strapdown Inertial Navigation

In modern aerospace technology, strapdown inertial navigation systems (SINS) are widely used, using fiber-optic (FOG) or ring laser (CLG) gyroscopes. During the operation of such systems, the sensitivity axes are rotated relative to the basic coordinate system. The resulting angles between the axes of the base coordinate system and the axes of sensitivity of the navigation system (non-orthogonality) are one of the factors leading to an increase in the measurement errors of the device, which affects the measurement accuracy. During operation, the system is affected by vibrations of various nature, the impact of which can contribute to the appearance of non-orthogonality. The purpose of this work is to determine the maximum permissible vibration amplitudes affecting the SINS body according to the permissible values ​​of the deviation of the FOG sensitivity axes for two variants of the SINS layout. An approach to determining the permissible amplitudes of an external harmonic impact on the unit of a strapdown inertial navigation system based on fiber-optic or ring laser gyroscopes is considered. A design scheme, mathematical and finite element models for calculating natural frequencies and forced oscillations of a strapdown inertial navigation system unit have been developed. In various frequency ranges, numerical calculations have determined the boundary values ​​of the amplitudes of the external harmonic impact on the base of specific configurations of the SINS assembly. It has been established that dangerous states take place in the region of the 1st natural frequency of the system, as well as near higher frequencies. Comparison of the results for design options 1 and 2 allows us to conclude that in order to weaken the effect of vibrations on the accuracy of the SINS unit, it is advisable that the lowest natural vibration frequencies for the SINS assembly be as high as possible (more than 1000 Hz). Key words: vibration; fiber optic gyroscope; strapdown inertial navigation system; finite element method; natural frequencies and modes of vibration.

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