| Inertial / Stellar navigation system using inertial navigation reference system as,with stellar observation information as an auxiliary means to modify,at the end of flight to observe the navigation star by star sensor,according to the measured data correction of the inertial coordinate datum,reduce the inertial coordinate system relative to the deviation of launch inertial coordinate system.As a sensitive device for astronomical observation of the inertia/stellar integrated navigation system,a star sensor is mounted on an inertial system stage for measuring a star's vector in a star sensor's measurement coordinate system,thereby solving its own three-dimensionality in an inertial coordinate system,and the calibration of the inertial attitude correction,realize the guidance precision of inertial system.Therefore,the installation error of star sensor in inertial platform system calibration correction accuracy of stellar guidance precision and inertial system has very important significance.The establishment of inertial / Stellar navigation system inertial coordinate system is based on the standard for platform hexahedral datum,so the installation error of star sensor is compared to the standard platform for hexahedral inertial system.In the past,there are many defects in the installation error measurement of star sensor,such as large error,large measurement error,manual operation,complex computation and low test efficiency,which can not meet the high accuracy and high efficiency test requirements.In view of this,this paper studies an automatic test method for installation errors of star sensor in assembly stage.This method first establishes the coordinate definition of star sensor installation error,gives the optical measurement principle,and establishes the error measurement model of azimuth and elevation angle.A complete set of automatic precision testing system is developed by measuring optical path design,hardware system integration,data acquisition and processing by using high precision photoelectric goniometer and photoelectric auto collimator combination.After test and data analysis,the test results can reach 5 "internal stability of the test,which proves that the method is stable and accurate.At present,it has been successfully applied to practical product testing,and has high engineering application value for precise assembly and measurement of inertial / Starlight navigation system.First,the coordinate definition of the installation error of star sensor is established.A new optical measurement principle is proposed,and the error measurement model of azimuth and elevation angle is created.The use of photoelectric goniometer,high-precision autocollimator combination,by measuring the optical path design,hardware system integration,data acquisition and processing,to form a complete set of automatic precision measurement system.After test and data analysis,the test results can reach 5" internal stability of the test,which proves that the method is stable and accurate.At present,it has been successfully applied to practical product testing,and has high engineering application value for precise assembly and measurement of inertial / Starlight navigation system. |
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