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Trajectory Control for a Spacecraft with an Inflatable Braking Device in the Martian Atmosphere

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Abstract

The possibility of using an inflatable braking device for controlled descent in the Martian atmosphere of large-capacity cargoes is analyzed. The most complicated version of the trajectory control problem is considered, namely, the injection of a spacecraft at hyperbolic velocity into a parking orbit after braking in the atmosphere.

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REFERENCES

  1. Harpold, J.C. and Graves, C.A., Shuttle Entry Guidance, J. Astronautical Sciences, 1979, vol. 27, no. 3.

  2. Yaroshevskii, V.A., Algorithms of Control over Trajectory Motion of Spacecraft at the Stage of Their Entry into the Atmosphere, Aerokosmich. Tekhn. Tekhnol., 1999, no. 1.

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Authors and Affiliations

  1. Babakin Research Center, Moscow, Russia

    S. N. Aleksashkin, O. V. Vlasenko, K. M. Pichkhadze & A. V. Terterashvili

  2. Zhukovsky Central Aerohydrodynamical Institute, Zhukovsky, Moscow oblast, Russia

    A. V. Bobylev & V. A. Yaroshevsky

Authors
  1. S. N. Aleksashkin
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  2. A. V. Bobylev
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  3. O. V. Vlasenko
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  4. K. M. Pichkhadze
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  5. A. V. Terterashvili
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  6. V. A. Yaroshevsky
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Aleksashkin, S.N., Bobylev, A.V., Vlasenko, O.V. et al. Trajectory Control for a Spacecraft with an Inflatable Braking Device in the Martian Atmosphere. Cosmic Research 41, 280–284 (2003). https://doi.org/10.1023/A:1024011200969

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  • DOI: https://doi.org/10.1023/A:1024011200969

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