FIELD: instrument making.
SUBSTANCE: for that purpose, in the course of determination of parameters of a measurement error model of accelerometers of inertial navigation systems (INS) as per measurements of satellite navigation that includes measurements of a vector of apparent acceleration of an object moving in inertial space, as per measurements of INS accelerometers and corrections to a speed vector at different time moments, which are obtained as per measurements of navigation space vehicles of GLONASS and GPS systems, there determined are errors of moduli of vectors of apparent speed, which are accumulated at several movement intervals of controlled moving objects differing by mutually noncollinear directions of vectors of apparent speed.
EFFECT: enlarging functional capabilities.
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|---|---|---|---|
| METHOD FOR DETERMINING PARAMETERS OF MODEL OF MEASUREMENT ERRORS OF ACCELEROMETERS OF DRIVEN INERTIAL NAVIGATION SYSTEM AS PER MEASUREMENTS OF REFERENCE INERTIAL NAVIGATION SYSTEM | 2012 |
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| ADAPTIVE ATTITUDE ANGLE CORRECTOR FOR STRAPDOWN INERTIAL NAVIGATION SYSTEM | 2020 |
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| INERTIAL RADIO NAVIGATION SYSTEM | 2013 |
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| METHOD OF DETERMINATION OF INSTRUMENT ERROR OF INERTIAL NAVIGATION SYSTEM METERS AT INITIAL ALIGNMENT STAGE | 2005 |
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RU2646954C2 |
| METHOD OF CORRECTION OF INERTIAL NAVIGATIONAL SYSTEM OF SPACE VEHICLE AT EXOATMOSPHERIC MOTION | 1993 |
|
RU2062989C1 |
