Influence of deviations in manufacturing of electrothermal propulsion system on nanosatellite maneuvering accuracy

Cite item

Full Text


A method is proposed for assessing the results of adjustment maneuvers for a nanosatellite (NS) with an electrothermal propulsion system (ETPS). Using the example of the SamSat-M nanosatellite under development, common causes of maneuvering errors associated with deviations in the manufacturing of the propulsion system are revealed. Probabalistic analysis of the NS maneuvering process was carried out. The design parameters of the ETPS are considered as random factors. Statistical models of the distributions of all random factors are assumed to be equally probable, which is the worst-case scenario, since the true distributions of the design parameters of the ETPS are unknown. The methodological basis of the study is the method of statistical modeling (Monte Carlo method) followed by the use of regression and factor analysis, on the basis of which the influence of the scatter of each of the design parameters on the controlled parameters is determined. Requirements for the design parameters of the ETPS that affect the spread of the projections of the velocity growth vector of the NS and the arising angular motion have been formulated. The presented results can be used to assess the influence of production deviations in the design parameters of propulsion systems on the nature of spacecraft motion, as well as to state requirements for the spread of design parameters to ensure the achievement of the objective.

About the authors

L. I. Sinitsin

Samara National Research University

Author for correspondence.
ORCID iD: 0000-0002-6569-1645

Postgraduate Student

Russian Federation

I. V. Belokonov

Samara National Research University

ORCID iD: 0000-0002-5486-8820

Doctor of Science (Engineering), Professor, Head of Inter-University Department of Space Research

Russian Federation


  1. Sochacki M., Narkiewicz J. Propulsion system modelling for multi-satellite missions performed by nanosatellites. Transactions on Aerospace Research. 2018. V. 2018, Iss. 4. P. 58-67. doi: 10.2478/tar-2018-0030
  2. Tummala A.R., Dutta A. An overview of cube-satellite propulsion technologies and trends. Aerospace. 2017. V. 4, Iss. 4. doi: 10.3390/aerospace4040058
  3. Lukyanchik A. Parametrical studies of a maneuvering ammonia resistojet nanosatellite. Information and Space. 2018. No. 3. P. 157-166. (In Russ.)
  4. Coxhill I.G., Gibbon D. A xenon resistojet propulsion system for microsatellites. 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit (July, 10-13, 2005, Tucson, Arizona). doi: 10.2514/6.2005-4260
  5. Lee R.H., Bauer A.M., Killingsworth M.D., Lilly T.C., Duncan J.A., Ketsdever A.D. Free-molecule-microresistojet performance using water propellant for nanosatellite applications. Journal of Spacecraft and Rockets. 2008. V. 45, Iss. 2. P. 264-269. doi: 10.2514/1.32341
  6. Lemmer K. Propulsion for CubeSats. Acta Astronautica. 2017. V. 134. P. 231-243. doi: 10.1016/j.actaastro.2017.01.048
  7. Blinov V.N., Vavilov I.S., Kositsyn V.V., Lukyanchik A.I., Ruban V.I., Shalay V.V. Study of power-to-weight ratio of the electrothermal propulsion system of nanosatellite maneuvering satellite platform. Dynamics of Systems, Mechanisms and Machines. 2017. V. 5, no. 2. P. 4-16. (In Russ.). doi: 10.25206/2310-9793-2017-5-2-04-16
  8. Zhumayev Z.S., Shcheglov G.A. Analysis of design parameters of solar power propulsion systems for nano-satellite. Proceedings of Higher Educational Institutions. Маchine Building. 2012. No. 12. С. 59-65. (In Russ.)
  9. Draper N.R., Smith H. Applied regression analysis. New York: Wiley, 1981. 709 p.
  10. Harman H.H. Modern factor analysis. The University of Chicago Press, 1960. 400 p.
  11. Manturov A.I. Mekhanika upravleniya dvizheniyem kosmicheskikh apparatov [Mechanics of spacecraft motion control]. Samara: Samara State Aerospace University Publ., 2003. 62 p.
  12. Popov V.I. Sistemy oriyentatsii i stabilizatsii kosmicheskikh apparatov [Spacecraft orientation and stabilization systems]. Moscow: Mashinostroenie Publ., 1986. 184 p.
  13. Ivanov D.S., Trofimov S.P., Shirobokov M.G. Chislennoye modelirovaniye orbitalnogo i uglovogo dvizheniya kosmicheskikh apparatov [Numerical modeling of spacecraft orbital and angular motion]. Moscow: IPM im. M.V. Keldysha Publ., 2016. 118 p. doi: 10.20948/mono-2016-trofimov
  14. Belokonov I.V., Ivliev A.V., Bogatyrev A.M., Kumarin A.A., Lomaka I.A., Simakov S.P. Selection of project structure for nanosatellite propulsion system. Vestnik of Samara University. Aerospace and Mechanical Engineering. 2019. V. 18, no. 3. P. 29-37. (In Russ.). doi: 10.18287/2541-7533-2019-18-3-29-37
  15. Titov B.A., Sirant A.L. Investigating the dynamics of space vehicles with an attitude control system on the basis of two-component liquid propellant low-thrust rocket engines. Vestnik of the Samara State Aerospace University. 2007. No. 1. P. 98-105. (In Russ.). doi: 10.18287/2541-7533-2007-0-1(12)-98-105
  16. Sarychev V.A., Gutnik S.A. Dynamics of satellite subject to gravitational and aerodynamic torques. Investigation of equilibria. Keldysh Institute Preprints. 2014. No. 39. 36 p. (In Russ.)
  17. Semenov K.K. The reliability of Monte-Carlo approach for applications in the interval analysis problems. Journal of Computational Technologies. 2016. V. 21, no. 2. P. 42-52. (In Russ.)

Supplementary files

Supplementary Files

Copyright (c) 2021 VESTNIK of Samara University. Aerospace and Mechanical Engineering

Creative Commons License
This work is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies