Article

Cover

Title

Modeling the deployment of a two-link spoke of a large-sized space reflector taking into account the backlash

Authors

F.V. Mitin, E.N. Nikulin

Organization

Baltic State Technical University «VOENMEH» named after D. F. Ustinov
Saint Petersburg, Russian Federation

Abstract

This article discusses the process of deployment a two-link spoke of a large-sized transformable space-based reflector. In view of the high costs of carrying out field tests, the construction of correct mathematical models is an urgent task. Currently, the creation of large-sized systems is actively developing. Such systems consist of several interconnected links. When delivered to a given orbit, the large-sized system is folded for placement in the launch vehicle. After entering the orbit, it is deployed to the specified operating state. A mathematical model has been developed for the deployment of the spoke, improved in terms of taking into account the separation of parameters depending on the length and time, which makes it possible to study the arising vibrations of the structure. It is important to take into account the backlash in the connections. Even small gaps in the spoke link connections can lead to a manifold increase in the stabilization time of the system. The developed mathematical model makes it possible to consider various conditions for linking links, change the mass-dimensional parameters and materials of the spoke. The results of modeling are presented, showing the correctness of mathematical models. Conclusions are made about the admissibility of using mathematical models for spokes consisting of a larger number of links.

Keywords

large-sized reflector, deployment of a spoke, mathematical model of a two-link spoke, modeling of the deployment process

References

[1] Lopatin A. V., Rutkovskaya M. A. Obzor konstrukcij sovremennyh transformiruemyh kosmicheskih antenn (chast' 1) [Review of modern transformable space antenna designs (part 1)]. Vestnik SibGAU, 2007, no. 2, pp. 51–57. (In Russian)

[2] Ponomarev S. V. Transformiruemye reflektory antenn kosmicheskih apparatov [Transformable reflectors for spacecraft antennas]. Tomsk State University Journal of Mathematics and Mechanics, 2011, no. 4, pp. 110–119. (In Russian)

[3] Reznik S. V., Chubanov D. E. Modelirovanie dinamiki raskrytiya krupnogabaritnogo transformiruemogo reflektora kosmicheskoj antenny iz kompozicionnogo materiala [Modeling the dynamics of the deployment of a large-sized transformable reflector of a space antenna made of composite material]. RUDN Journal of Engineering Researches, 2018, vol. 19, no. 4, pp. 411–425. (In Russian)

[4] Taygin V. B., Lopatin А. V. Method of achievement the high accuracy of the shape of reflectors of mirror antennas of spacecraft // Spacecrafts & Technologies, 2019, vol. 3, no. 4, pp. 200–208. doi: 10.26732/2618-7957-2019-4-200-208.

[5] Sun Z., Zhang Y., Yang D. Structural design, analysis, and experimental verification of an H-style deployable mechanism for large space-borne mesh antennas // Acta Astronautica, 2021, no. 178, pp. 481–498.

[6] Berns V. A., Levin V. E., Krasnorutsky D. A., Marinin D. A., Zhukov E. P., Malenkova V. V., Lakiza P. A. Development of a calculation and experimental method for modal analysis of large transformable space structures // Spacecrafts & Technologies, 2018, vol. 2, no. 3, pp. 125–133. doi: 10.26732/2618-7957-2018-3-125-133.

[7] Kabanov S. A., Zimin B. A., Mitin F. V. Razrabotka i analiz matematicheskih modelej raskrytiya podvizhnyh chastej transformiruemyh kosmicheskih konstrukcij. CHast' I [Development and Research of Mathematical Models of Deployment of Mobole Parts of Transformable Space Construction. Part I]. Mekhatronika, Avtomatizatsiya, Upravlenie, 2020, vol. 20, no. 1, pp. 51–64. (In Russian)

[8] Kabanov S. A., Zimin B. A., Mitin F. V. Razrabotka i analiz matematicheskih modelej raskrytiya podvizhnyh chastej transformiruemyh kosmicheskih konstrukcij. CHast' II [Development and Research of Mathematical Models of Deployment of Mobole Parts of Transformable Space Construction. Part II]. Mekhatronika, Avtomatizatsiya, Upravlenie, 2020, vol. 21, no. 2, pp. 117–128. (In Russian)

[9] Kabanov S. A., Mitin F. V. Optimization of the stages of deploying a large-sized space-based reflector // Acta Astronautica, 2020, vol. 176, pp. 717–724.

[10] Huang H., Cheng Q., Zheng L., Yang Y. Development for petal-type deployable solid-surface reflector by uniaxial rotation mechanism // Acta Astronautica, 2021, vol. 178, pp. 511–521.

[11] Li P., Ma Q., Song Y., Liu C., Tian Q., Ma S., Hu H. Deployment dynamics simulation and ground test of a large space hoop truss antenna reflector // Science China Physics, Mechanics & Astronomy, 2017, vol. 47, 104602.

[12] Jiang X., Zhengfeng B. Dynamics Modelling and Simulation for Deployment Characteristics of Mesh Reflector Antennas // Applied Sciences, 2020, vol. 10, pp. 78–84.

[13] Liu L., Shan J., Zhang Y. Dynamics modeling and analysis of spacecraft with large deployable hoop-truss antenna // Journal of Spacecraft and Rockets, 2016, vol. 53, pp. 471–479.

[14] Guo H. W., Zhang J., Liu R. Q., Deng Z. Q., Cao D. Q. Nonlinear dynamics analysis of joint dominated space deployable truss structures // Journal of Harbin Institute of Technology, 2013, vol. 20, pp. 68–74.

[15] Panovko Ya. G. Vnutrennee trenie pri kolebaniyah [Internal friction during vibrations]. Moscow, Fizmatgiz, 1960, 193 p. (In Russian)

For citing this article

Mitin F.V., Nikulin E.N. Modeling the deployment of a two-link spoke of a large-sized space reflector taking into account the backlash // Spacecrafts & Technologies, 2021, vol. 5, no. 3, pp. 146-152. doi: 10.26732/j.st.2021.3.03

This Article is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License (CC BY-NC 4.0).