gyroscopyГироскопия и навигацияGiroskopiya i Navigatsiya / Gyroscopy and Navigation0869-70352075-0927AO «Концерн «ЦНИИ «Электроприбор»621.398.694.4-531.4gyroscopy-578Research ArticleСтатьиКалибровка датчиков угловой ориентации пикоспутников* в полетеСокенХ. Э.

Стамбульский технический университет, факультет аэронавтики и астронавтики

ГаджиевЧ.

Гаджиев Чингиз, профессор. Действительный член общественного объединения «Академия навигации и управления движением».    

Сокен Халиль Эрскин, студент. Стамбульский технический университет, факультет аэронавтики и астронавтики ТурцияTurkeyСтамбульский технический университет, факультет аэронавтики и астронавтикиTurkey2011200320261933445Copyright © Сокен Х., Гаджиев Ч., 20262026Сокен Х., Гаджиев Ч.Сокен Х., Гаджиев Ч.Данная работа распространяется под лицензией Creative Commons Attribution 4.0.This work is licensed under a Creative Commons Attribution 4.0 License.https://www.gyroscopy.ru/jour/article/view/578

Предлагается методика оценивания смещения нулей датчиков угловой ориентации пикоспутника, основанная на использовании фильтра UKF**. В качестве датчиков используются трехосные магнитометры и скоростные гироскопы. На начальном этапе оцениваются смещения нулей трех ортогонально расположенных магнитометров, а также угловая ориентация и угловые скорости спутника. Считается, что сразу после выведения спутника на орбиту погрешностями в выходных сигналах гироскопов можно пренебречь. На втором этапе учитываются оцененные постоянные составляющие смещения нулей магнитометров и подключается алгоритм оценивания смещения нулей гироскопов, которые являются причиной нарастания погрешностей во времени. В результате оцениваются шесть значений смещения нулей двух групп датчиков на двух этапах с регулярной оценкой угловой ориентации и угловых скоростей. В предлагаемой процедуре UKF используется в качестве алгоритма оценивания для обеих стадий решения задачи.Статья по докладу на XVII Санкт-Петербургской международной конференции по интегрированным навигационным системам.

In this paper an Unscented Kalman filter based procedure is proposed for the bias estimation of attitude sensors of a pico satellite. As attitude sensors three axis magnetometers and the rate gyros are used. At the initial phase, biases of three orthogonally located magnetometers are estimated as well as the attitude and attitude rates of the satellite. During initial period after the orbit injection, gyro measurements are accepted as bias free since the precise gyros are working accurately and the accumulated gyro biases are negligible. At the second phase, estimated constant magnetometer bias components are taken into account and the algorithm is run for the estimation of the gyro biases that are cumulatively increased by time. As a result, six different bias terms for two different sensors are obtained in two stages where attitude and attitude rates are estimated regularly. For both estimation phases of the procedure Unscented Kalman Filter is used as the estimation algorithm.

 

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The authors declare that there are no conflicts of interest present.