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Determining the dynamics of spacecraft rotational motion with the use of information provided by global navigation satellite systems
- Authors: Belokonov I.V.1, Kramlikh A.V.1, Lomaka I.A.1
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Affiliations:
- Samara National Research University
- Issue: Vol 18, No 2 (2019)
- Pages: 41-51
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/6740
- DOI: https://doi.org/10.18287/2541-7533-2019-18-2-41-51
- ID: 6740
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Abstract
The paper shows the possibility of using navigation user equipment in the task of determining the dynamics of spacecraft rotational motion. An approach is proposed that makes it possible to estimate the parameters of the rotational motion of a spacecraft by analyzing the geometric visibility of navigational spacecraft of global navigation satellite systems. The proposed approach consists in approximation of the accumulated information on the position of the spacecraft longitudinal axis using the angular motion model and the measurement model. The approximation is made on the basis of minimizing the sum of squared deviations between the calculated coordinates of the vector of the longitudinal axis and their simulated values. The minimization procedure is based on the algorithm of differential evolution. The proposed approach allows us to estimate the angular velocity of the nanosatellite with an accuracy of at least 0.3 deg/s and orientation angles with an accuracy of at least 15 degrees.
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About the authors
I. V. Belokonov
Samara National Research University
Author for correspondence.
Email: ibelokonov@mail.ru
Doctor of Science (Engineering), Professor
Head of Inter-University Department of Space Research
A. V. Kramlikh
Samara National Research University
Email: kramlikh@mail.ru
Candidate of Science (Engineering), Associate Professor
Inter-University Department of Space Research
I. A. Lomaka
Samara National Research University
Email: igorlomaka63@gmail.com
Postgraduate Student
Russian FederationReferences
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