Development of the methodological approaches for the attitude control system of the Earth remote sensing satellite in the conditions of the onboard equipment partial failures

Keywords: attitude and orbit control system, actuators partial failures, energy saving

Abstract

The spacecraft controllability of the angular motion is possible only with operability of the attitude and orbit control system (AOCS) of the spacecraft, sensors, actuators and the spacecraft power system. However, there is a rather significant probability of failure of this equipment during the operation of the spacecraft. This is especially observed after half of the spacecraft's lifetime or because of emergency situations. There is a problem which is connected with providing the maximum performance of the AOCS in case of partial failures of their actuators (reaction wheels (RW), magnetorquer rods (MGTR), etc.).

Thus, the purpose of this work is the development and synthesis of special algorithms for spacecraft angular motion control in the emergency situations which are connected with RWs partial failures and restrictions of onboard electricity consumption. The approach of synthesis of this control algorithms is based on using mobile control methods which allow to reserve RWs by MGTRs. There are different variants of control loops depending on MGTRs turning on combinations. There were proposed two types of control switching functions: time-periodic and switching by deviation. Also was proposed a methodology of controller synthesis using these switching functions.

Using this methodology and computer simulation, it was shown the possibility of providing angular nadir orientation and stabilization of the spacecraft with maximum 1−1.5 deg error in case of time-periodic switching functions implementation. Switching by deviation allows to reduce onboard electricity consumption for 25−30 % comparing with using time-periodic switching. However, the accuracy of stabilization significantly lower in case of switching by deviation. Considering these estimates, the corresponding methodological recommendations were formulated for use switching functions depending on emergency

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References

Firsov, S. N., Reznikova, O. V. (2013). Fault tolerance of spacecraft orientation and stabilization system. Radio Electronics, Computer Science, Control, 2, 103–111. doi: http://doi.org/10.15588/1607-3274-2013-2-17

Ovchinnikov, M. Yu., Roldugin, D. S. (2019). Recent advances in the active magnetic control of satellites. Spacecraft & Technologies, 2 (28), 73–86. doi: http://doi.org/10.26732/2618-7957-2019-2-73-86

Yang, Y. (2016). Controllability of spacecraft using only magnetic torques. IEEE Transactions on Aerospace and Electronic Systems, 2 (52), 954–961. doi: http://doi.org/10.1109/taes.2015.150520

Yang, Y. (2019). Spacecraft modeling, attitude determination, and control: quaternion-based approach. Taylor & Francis Group, LLC, 340. doi: http://doi.org/10.1201/9780429446580

Ovchinnikov, M. Yu., Roldugin, D. S., Penkov, V. I. (2015). Three-axis active magnetic attitude control asymptotical study. Acta Astronautica, 110, 279–286. doi: http://doi.org/10.1016/j.actaastro.2014.11.030

Celani, F. (2015). Robust three-axis attitude stabilization for inertial pointing spacecraft using magnetorquers. Acta Astronautica, 107, 87–96. doi: http://doi.org/10.1016/j.actaastro.2014.11.027

Ivanov, D. S., Ovchinnikov, M. Yu., Penkov, V. I., Roldugin, D. S., Doronin, D. M., Ovchinnikov, A. V. (2017). Advanced numerical study of the three-axis magnetic attitude control and determination with uncertainties. Acta Astronautica, 132, 103–110. doi: http://doi.org/10.1016/j.actaastro.2016.11.045

Sofyalı, A., Jafarov, E. M., Wisniewski, R. (2018). Robust and global attitude stabilization of magnetically actuated spacecraft through sliding mode. Aerospace Science and Technology, 76, 91–104. doi: http://doi.org/10.1016/j.ast.2018.01.022

Alpatov, A. P. (2016). Dinamika kosmicheskikh letatelnykh apparatov. Kyiv: Naukova dumka, 488. Available at: https://www.nas.gov.ua/UA/Book/Pages/default.aspx?BookID=0000014648

Alpatov, A., Lapkhanov, E. (2019). The use of mobile control methods for stabilization of a spacecraft with aeromagnetic deorbiting system. System technologies, 6, 41–54. doi: http://doi.org/10.34185/1562-9945-6-125-2019-04

Curtis, H. (2020) Orbital Mechanics for Engineering Students. Butterworth-Heinemann. doi: http://doi.org/10.1016/c2016-0-02107-1

Chulliat, A., Brown, W., Alken, P., Beggan, C., Nair, M., Cox, G. et. al. (2020). The US/UK World Magnetic Model for 2020–2025. National Centers for Environmental Information. doi: http://doi.org/10.25923/ytk1-yx35

Fortescue, P., Stark, J., Swinerd, G. (2011) Spacecraft systems engineering. Chichester: John Wiley & Sons Ltd, 724. doi: http://doi.org/10.1002/9781119971009

Mirer, S. A. (2007). Mekhanika kosmicheskogo poleta. Orbitalnoe dvizhenie. Moscow: Rezolit, 270.

ECSS-E-ST-10-04C. Space engineering, Space environment (2008). Noordwijk: ECSS Secretariat, ESA-ESTEC, Requirements & Standards Division, 198. Available at: https://ecss.nl/standard/ecss-e-st-10-04c-space-environment/

Alpatov, A. P., Khoroshylov, S. V., Maslova, A. I. (2019). Сontactless de-orbiting of space debris by the ion beam. Dynamics and control. Kyiv: Akademperiodyka, 170. doi: http://doi.org/10.15407/akademperiodyka.383.170

Alpatov, A., Khoroshylov, S., Lapkhanov, E. (2020). Synthesizing an algorithm to control the attitude motion of SC equipped with an aeromagnetic deorbiting system. Eastern-European Journal of Enterprise Technologies, 1 (5 (103)), 37–46. doi: http://doi.org/10.15587/1729-4061.2020.192813

Parshukov, A. N. (2009). Metody sinteza modalnykh reguliatorov. Tiumen, 83.

Lapkhanov, E. (2021). Development of methodological approaches for the synthesis of control algorithms for spacecraft deorbiting with using an aeromagnetic deorbiting system. Dnipro, 254.

The dynamic of orbital parameters changes during SC orbiting

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Published
2022-09-30
How to Cite
Zheliabov, P., & Lapkhanov, E. (2022). Development of the methodological approaches for the attitude control system of the Earth remote sensing satellite in the conditions of the onboard equipment partial failures. EUREKA: Physics and Engineering, (5), 77-90. https://doi.org/10.21303/2461-4262.2022.002020
Section
Engineering