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Calculation of Main Design Parameters of a Reactive Penetrator Intended for Movement in Lunar Soil

  • Flight Dynamics and Control of Flight Vehicles
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Abstract

The possibility of using penetrators to study the Moon’s subsurface is considered and possible launch options are indicated. Dependencies are given that allow calculating the penetrator mass, penetration depth, and arising overloads with sufficient accuracy. The use of a solid propellant engine on a penetrator is demonstrated.

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Acknowledgements

This work was fulfilled as part of the state assignment of the Ministry of Science and Higher Education of the Russian Federation, code 9.7969.2017/8.9.

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Authors and Affiliations

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

    V. A. Zagovorchev & V. V. Rodchenkov

Authors
  1. V. A. Zagovorchev
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  2. V. V. Rodchenkov
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Correspondence to V. A. Zagovorchev.

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Russian Text © The Author(s), 2019, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2019, No. 4, pp. 65–72.

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Zagovorchev, V.A., Rodchenkov, V.V. Calculation of Main Design Parameters of a Reactive Penetrator Intended for Movement in Lunar Soil. Russ. Aeronaut. 62, 595–603 (2019). https://doi.org/10.3103/S1068799819040093

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  • DOI: https://doi.org/10.3103/S1068799819040093

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