FIELD: physics.
SUBSTANCE: proposed method comprises obtaining data on coordinates of moving object from onboard inertial navigation system, receiving signals from satellite radio navigation system by three navigation receiver antennas A0, A1, A2 fixed on moving object and not located on one straight line, data processing to define angular orientation parameters. Note here that data processing comprises correcting errors in angular orientation parameters received from inertial navigation system using signals from one available satellite and their phase difference received by spaced apart antennas A0 and A1 to define angle β1 between antenna datum d1 and direction to satellite. Data received from onboard inertial navigation system about coordinates and orientation parameters and that from satellite navigation system on satellite coordinates are used to define angle β1* between antenna datum d1 and direction to satellite by phase difference of signals received from satellite by spaced apart antennas A0 and A2. Angle β2 between antenna datum d2 and direction to satellite is defined. Data received from onboard inertial navigation system about coordinates and orientation parameters and that from satellite navigation system on satellite coordinates are used to define angle β2* between antenna datum d2 and direction to satellite is defined. In case magnitudes β1 and β1*, β2 and β2* differ by quantity exceeding preset one, error is corrected in angular orientation parameters received from onboard inertial navigation system.
EFFECT: determination of angular orientation in limited visibility of satellites.
1 dwg
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Authors
Dates
2011-06-27—Published
2009-01-11—Filed