ПОДДЕРЖКА ПЕТЕЛЬ СЛЕЖЕНИЯ ЗА ФАЗОЙ В ПРИЕМНИКЕ СПУТНИКОВОЙ НАВИГАЦИИ С ПОМОЩЬЮ ИЗМЕРЕНИЙ ИНЕРЦИАЛЬНОЙ НАВИГАЦИОННОЙ СИСТЕМЫ

Abstract

Satellite radio navigation systems make it possible to evaluate the user's state vector, usecoordinates, user speed and time relative to the system scale. The requirements for the characteristicsof these systems constantly depend on the fact that they have application features in theiralgorithms for processing radio navigation signals. One of the main characteristics of satelliteradio navigation systems is the accuracy of estimating the user's state vector. This characteristiccan be improved by the presence of estimates of the phase of the received radio navigation signals.In a satellite radio navigation system, phase estimation errors in the tracking loop have two components:dynamic and noise. To compensate for the noise error, it is necessary to reduce theequivalent noise band of the anti-aliasing filter of the phase tracking loop. However, the minimumpossible bandwidth of the smoothing filter is limited by the presence of consumer dynamics and thequality of the reference oscillator. As a result, in the presence of consumer dynamics, the sensitivityand reliability of phase tracking deteriorates. To compensate for the dynamic error in the phasetracking loop, information from an inertial navigation system can be used. The satellite radio navigationsystem and the inertial navigation system have complementary characteristics. The use ofsupport for phase tracking loops from an inertial navigation system makes it possible to increasethe sensitivity and reliability of its operation in the presence of consumer dynamics. It is assumedthat with such an implementation, the sensitivity of the phase tracking loops will be limited only bythe instability of the reference oscillator and the error of inertial measurements. To improve thecharacteristics of accuracy, sensitivity and reliability of the coherent mode of operation of the enddevice, an algorithm was developed to support phase tracking loops with measurements from aninertial navigation system. A study of the developed algorithm was carried out on a model thatuses real measurements of satellite and inertial navigation systems as input data. The developedalgorithm is implemented in the software of the NV216C-IMU inertial satellite navigation systemprototype. Experimental studies were carried out in the conditions of automobile dynamics in openareas. The research results are presented in the work.