ATTITUDE SYSTEM CORRECTED BY ACCELERATIONS CALCULATED USING SATELLITE NAVIGATION SYSTEM PHASE MEASUREMENTS IN STANDARD MODE

摘要

This paper describes the algorithms of a corrected strapped down inertial attitude system that uses fiber-optic angular velocity sensors and microelectromechanical accelerometers. A simplified method of inertial and satellite navigation system integration is realized The method is based on estimation of orientation angles and difference of accelerations measured by accelerometers and the satellite navigation system (SNS) is used for their correction. In the second case SNS carrier phase measurements are used to calculate the acceleration. The correction problem is formulated as a standard linear estimation problem. The solution uses Kalman filter and smoothing. An example of the algorithms implementation is given. The results of application of the described attitude system for the aircraft-mounted high-frequency scanner are presented.