TECHNICAL MECHANICS
ISSN (Print): 1561-9184, ISSN (Online): 2616-6380

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Home > Journal Issues > No 1 (2024) Technical mechanics > 4
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UDC 629.78

Technical mechanics, 2024, 1, 40 - 49

MATHEMATICAL MODEL FOR SELECTING THE AUXILIARY EQUIPMENT PARAMETERS OF AERODYNAMIC DEORBIT SYSTEMS

DOI: https://doi.org/10.15407/itm2024.01.040

Wang Changqinq, Palii . S.

      ABOUT THE AUTHORS

Wang Changqinq
Northwestern Polytechnical University

Palii . S.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      ABSTRACT

      The goal of this work is to develop a model for selecting the design parameters of auxiliary equipment for aerodynamic deorbit systems. For normal operation, an aerodynamic deorbit system, according to its class, is equipped with the following support systems: for deployment, inflation, nd storage onboard the space object to be deorbited. The deployment system consists of two components: a mast deployment system, in which four rolled-up masts are stored and deployed, and an airfoil storage spindle, on which four quadrants of a film material are wound. Aerodynamic systems can be inflated in several ways: using a system of gas storage and supply to the shell, using the residual pressure, or using the sublimation of a powder substance. The characteristics of sublimable substances and inert gases for inflation are given. The paper presents a methodology for determining the inflating gas parameters taking into account the exposure of the aerodynamic system to space debris fragments. The following requirements are imposed on the storage system materials: resistance to space factors, resistance to dynamic loads in orbital injection, and resistance to thermal deformations. A mathematical model for selecting the auxiliary system parameters of aerodynamic deorbit systems is presented. This model includes deployment system mass estimation, relationships for determining the inflation system mass for aerodynamic systems of various configurations, wall thickness estimation for gas cylinders of different configurations, and relationships for determining the storage system mass for aerodynamic deorbit systems of different configurations.
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      KEYWORDS

space object, aerodynamic deorbit system, auxiliary equipment, design parameters, mathematical model

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      REFERENCES

1. Jenkins C. H. M. Progress in Astronautics and Aeronautics. V. 191. Gossamer Spacecraft: Membrane and Inflatable Structures Technology for Space Applications. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2001. 586 pp.

2. Yavorsky B. M., Detlaf A. A., Lebedev B. M. Handbook on Physics for Engineers and Students. Moscow, 2006. 1,056 pp. (in Russian).

3. Shikhirin V. N., Ionova V. F., Shalnev O. V., Kotlyarenko V. I.. Elastic Mechanisms and Structures. Irkutsk, 2006. 286 pp. (in Russian).

4. The Echo-I inflation system: technical report. Langley Research Center; chief D. L. Clemmons Jr. Hampton, Virginia, 1964. 56 pp. No. TN D-2194.

5. Thunnissen D. P., Webster M. S., Engelbrecht C. S. Low-Mass Inflation Systems for Inflatable Structures. Jet Propulsion Lab. 22 pp. URL: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19960054146.pdf (application date 03/12/2014).

6. Meteoroid and space debris terrestrial environment reference model MASTER-2009 [Electronic resource]. ESA-SD-DVD-02, Release 1.0, December 2010. 1 electronic disc (DVD-R).

7. Koshmarov Yu. A., Ryzhov Yu. A. Applied Rarefied Gas Dynamics. Moscow, 1977. 184 pp. (in Russian)

8. Pisarenko G. S., Yakovlev A. P., Matveev V. V. Handbook on Materials Resistance. Kyiv, 1988. 736 pp. (in Russian).

9. Sutton G. P., Biblarz O. Rocket Propulsion Elements. Eighth Edition. John Wiley & Sons, Inc., 2010. 784 pp.

10. Shalin R. E., Efremov I. S., Yarovinskiy Yu. L., Lukin V. I. Experience in design and manufacturing of large-size structures from aluminum-lithium alloys for rocket-space engineering products. Welding Production. No. 11. 1996. URL: https://viam.ru/sites/default/files/scipub/1996/1996-202092.pdf. (in Russian)

11. Ti 6Al 4V (Grade 5) Titanium Alloy Data Sheet. URL: https://kyocera-sgstool.co.uk/titanium-resources/titanium-information-everything-you-need-to-know/ti-6al-4v-grade-5-titanium-alloy-data-sheet/#:~:text=Titanium%206al-4v%20has%20a%20density%20of%204.43%20g%2Fcc.

12. Titanium Ti-5Al-2Sn-2Zr-4Mo-4Cr (Ti-17) Beta Processed. Matweb. URL: https://www.matweb.com/search/datasheet_print.aspx?matguid=a33b3d2218204cb0b6f84724768a4176.

13. Titanium Ti-10V-2Fe-3Al (Ti 10-2-3) Solution Treated 850C (1560F). Matweb. URL: https://www.matweb.com/search/DataSheet.aspx?MatGUID=e810947a42894199adec39058992b53a&ckck=1.

14. Titanium IMI 829 (Ti-5.5Al-3.5Sn-3Zr-1Nb-0.25Mo-0.3Si). Matweb. URL: https://www.matweb.com/search/datasheet.aspx?matguid=f76e8131f6fb427ba943a92882273970&n=1.

15. Gaydachuk A. V., Karpikova O. A., Kondratev A. V., Slivinskiy M. V. Honeycomb Cores and Panel Structures for Space Purposes. In 2 vol. V. 1. Technological Imperfections of Honeycomb Cores and Structures; ed. A. V. Gaydachuk (Ed.). Kharkiv: N.E. Zhukovsky National Aerospace University Kharkiv Aviation Institute, 2012. 279 pp. (in Russian)

16. Banichuk N. V., Karpov I. I., Klimov D. M. Mechanics of Large Space Structures. Moscow: Factorial, 1997. 302 pp. (in Russian).





Copyright () 2024 Wang Changqinq, Palii . S.

Copyright 2014-2024 Technical mechanics


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