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Calculation of Basic Design Parameters and Structure of a Reactive Penetrator Intended for Movement in Lunar Soil

  • AIRCRAFT AND ROCKET ENGINE DESIGN AND DEVELOPMENT
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Abstract

A possible design scheme of a lunar reactive penetrator is considered that is able to penetrate into regolith and deliver the scientific equipment to a specified point of the ground volume. The dependences connecting the main design parameters are given. They allow estimating the principal possibility of movement in the ground. Three options for calculating the penetrator model with different types of solid propellant are presented and recommendation for required propellant volume is given.

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REFERENCES

  1. Craft, J., Wilson, J., Chu, P., Zacny, K., and Davis, K., Percussive Digging Systems for Planetary Research, IEEE Aerospace and Electronic Systems Magazine, 2010, vol. 25, issue 10, pp. 21–26.

    Article  Google Scholar 

  2. Fedorov, S.V., Veldanov, V.A., and Fedorova, N.A., On the Possibility of Increasing Rocky Target Penetration Depth for Compound Penetrators Featuring a Tail Assembly Jettisoned at Impact, Vesnik MGTU im. Baumana. Mashinostroenie, 2019, no. 1 (124), pp. 30–50.

    Google Scholar 

  3. Fedorov, S.V. and Fedorova, N.A., Penetrating Modules for Rocky Target Penetration with Featuring a Tail Assembly Jettisoned at Impact, Izvestiya RARAN, 2018, no. 2 (102), pp. 77–83.

    Google Scholar 

  4. Korshun, E.V., Markianov, A.V., Rusakov, A.V., Sizov, A.A., Tverdokhlebova, E.M., and Khomin, T.M., Spacecraft Propulsion and Electrical Power Systems Electronic Databank Designing, Trudy MAI, 2014, no. 73, URL: http://trudymai.ru/eng/published.php?ID=48489.

    Google Scholar 

  5. Rodchenko, V.V., Sadretdinova, E.R., and Gusev, E.V., Choice of Parameters of Penetrator for Research of a Lunar Ground, Vestnik MAI, 2010, no. 3, pp. 83–90.

    Google Scholar 

  6. Rodchenko, V.V., Sadretdinova, E.R., Zagovorchev, V.A., and Galeev, A.V., The Selection of Terrestial Soil-Analogs as a Medium for Movement of Lunar Reactive Penetrator, Al’ternativnaya Energetika i Ekologiya, 2017, no. 28–30 (240–242), pp. 69–81.

    Google Scholar 

  7. Zagovorchev, V.A. and Rodchenko, V.V., Calculation of Main Design Parameters of a Reactive Penetrator Intended for Movement in Lunar Soil, Izv. Vuz. Av. Tekhnika, 2019, vol. 62, no. 4, pp. 65–72 [Russian Aeronautics (Engl. Transl.), vol. 62, no. 4, pp. 595–603].

    Google Scholar 

  8. Zhu Y., Zhou Q., Liu B., and Li Z., Finite Element Analysis on Interaction between Lunar Regolith and Cutter, Procedia Engineering, 2014, vol. 73, pp. 194–203.

    Article  Google Scholar 

  9. Trubnikov, A.A., Popov, V.O., and Alekseeva, N.A., Methodology for Calculating the Combustion Surface Area of Power Propulsion Systems, Polzunovskii Vestnik, 2018, no. 4, pp. 145–148.

    Google Scholar 

  10. Mingireanu, F., Jula, N., Miclos, S., Savastru, D., and Baschir, L., Solid Rocket Motors Internal Ballistic Model with Erosive and Condensed Phase Considerations, UPB Scientific Bulletin, Series A: Applied Mathematics and Physics, 2018, vol. 80, issue 4, pp. 255–266.

    Google Scholar 

  11. Mishchenkova, O.V., Solving Selection Problems in Process Analysis in Solid Fuel Engines, Vestnik IzhGTU im. M.T. Kalashnikova, 2016, vol. 19, no. 2, pp. 120–123.

    Google Scholar 

  12. Belyakov, A.Yu., Solid Fuel Combustion Surface Modelling with Regard for Heat-Conducting Elements, Trudy MAI, 2020, no. 110, URL: http://trudymai.ru/eng/published.php?ID=112931.

    Google Scholar 

  13. Chevula, S., Design and Testing of Rocket Motors with Composite Propellants, Int. J. of Mechanical and Production Engineering Research and Development, 2019, vol. 9, issue 4, pp. 745–752.

    Article  Google Scholar 

  14. Marmureanu, M.I., Solid Rocket Motor Internal Ballistics Simulation Using Different Burning Rate Models, UPB Scientific Bulletin, Series D: Mechanical Engineering, 2014, vol. 76, issue 4, pp. 49–56.

    Google Scholar 

  15. Egorov, M.Yu., Gorodnev, V.O., Egorov, D.M., and Egorov, S.M., Numerical Study of the Intrachamber Processes Dynamics in a Rocket Engine for Mobile Complexes with a Multi-Turret Powder Charge, Vestnik PNIPU. Aerokosmicheskaya Tekhnika, 2020, no. 60, pp. 55–63.

    Google Scholar 

  16. Aliev, A.V. and Voevodina, O.A., Models of Chemically Equilibrium Flow of Combustion Products in Problems of Internal Ballistics for a Large Rocket Engine, Khimicheskaya Fizika i Mezoskopiya, 2015, vol. 17, no. 2, pp. 203–207.

    Google Scholar 

  17. Guzachev, D.S., Kratirov, D.V., Zorin, V.A., and Mikheev, N.I., Small-Size Rocket Impulse-Reaction Launch Dynamics, Izv. Vuz. Av. Tekhnika, 2011, vol. 54, no. 2, pp. 18–20 [Russian Aeronautics (Engl. Transl.), vol. 54, no. 2, pp. 141–145].

    Google Scholar 

  18. Sorkin, R.E., Gazotermodinamika raketnykh dvigatelei na tverdom toplive (Gas Thermodynamics of Solid Propellant Rocket Engines), Moscow: Nauka, 1967.

    Google Scholar 

  19. Egorov, M.Yu., Numerical Research of Intra-Chamber Processes Dynamics during Startup of a Special Solid Propellant Engine, Izv. Vuz. Av. Tekhnika, 2017, vol. 60, no. 4, pp. 104–111 [Russian Aeronautics (Engl. Transl.), vol. 60, no. 2, pp. 591–599].

    Google Scholar 

  20. Rodchenko, V.V., Sadretdinova, E.R., Zagovorchev, V.A., and Lugovtsov, I.V., Choice of Parameters of Penetrator for Research of a Lunar Ground, Trudy MAI, 2012, no. 59, URL: http://trudymai.ru/eng/published.php?ID=35254.

    Google Scholar 

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ACKNOWLEDGEMENTS

The work is performed as a part of the state assignment of the Ministry of Science and Higher Education of the Russian Federation (project code FSFF-2020-0016).

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Authors and Affiliations

  1. Moscow Aviation Institute (National Research University), Volokolamskoe sh. 4, 125993, Moscow, Russia

    V. A. Zagovorchev, P. F. Pronina & V. V. Rodchenko

Authors
  1. V. A. Zagovorchev
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  2. P. F. Pronina
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  3. V. V. Rodchenko
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Corresponding author

Correspondence to V. A. Zagovorchev.

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Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2020, No. 4, pp. 126 - 132.

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Zagovorchev, V.A., Pronina, P.F. & Rodchenko, V.V. Calculation of Basic Design Parameters and Structure of a Reactive Penetrator Intended for Movement in Lunar Soil. Russ. Aeronaut. 63, 698–705 (2020). https://doi.org/10.3103/S1068799820040182

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  • DOI: https://doi.org/10.3103/S1068799820040182

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