TY - JOUR
AU - Sidorov, I.
AU - Manoilenko, А.
PY - 2021/11/20
Y2 - 2022/05/19
TI - MATHEMATICAL MODEL FOR CALCULATION OF ERRORS FOR ESTIMATING ANGULAR VELOCITY OF THE SPACECRAFT
JF - Journal of Rocket-Space Technology
JA - Rocket-Sp. Tech.
VL - 28
IS - 4
SE - Applied mechanics and mathematical methods
DO - 10.15421/452017
UR - http://rocketspace.dp.ua/index.php/rst/article/view/88
SP - 123-128
AB - At present, there is an increased interest in the creation of platform-free inertial navigation systems (SINS), which constitute the information core of modern on-board orientation and navigation systems for spacecraft (SC). SINS can include magnetometers, astro sensors, angular rate sensors (ARS). The accuracy of determining the spacecraft orientation largely depends on the SINS composition. The presence of ARS in the SINS provides the best accuracy. In this regard, the tasks associated with filtering "noisy" data from the control system, estimating and calculating the estimation errors, and calibrating the SINS sensors are relevant. In this paper, a mathematical model is proposed for solving the problem of calculating the errors in estimating the angular velocities of the spacecraft taking into account the filtering of the "noisy" data of the ARS. The model includes: a discrete model of the object of observation - the ARS and the model of the measurement process, which takes into account such parameters of the ARS as the instability of the pulse price, the non-orthogonality of the sensitivity axes, the instability of the zero shift, and the random drift of the sensor. The optimal recurrent Kalman filter is used as a filtering algorithm for the ARS data on the components of the spacecraft angular velocity vector, which makes it possible to minimize the root-mean-square error in estimating the object's state vector and to isolate the useful signal against the background of random noise. Such a filter for discrete models of the object of observation and the measurement process allows for optimal estimation in real time of the spacecraft flight. The parameters of the ADIS-16350 type ARS, which is made using MEMS - technology, were taken as the initial data. The results of numerical modeling of the dynamic processes of filtering the ARS data and the estimation of the angular velocities of the spacecraft are presented.
ER -