Effect of yaw-tilted hinge axis on deployment robustness of mars airplane

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper investigates the robustness of the aerial deployment behavior of the foldable-wing airplane for Mars exploration especially focused on the effect of the hinge axis tilting in a yaw direction. This study deals with four dispersive parameters for the robustness evaluation: drop velocity, surrounding gust velocity, initial pitch angle, and height. The robustness of several tilted and non-tilted hinge axis designs are calculated and then compared. The result clearly shows that the tilted hinge axis design can deploy with lower torque than the torque of the non-tilted hinge axis design. The increase of sideslip angle due to the hinge axis tilting suppressed an aerodynamic force on the deploying wing.

Original languageEnglish
Title of host publication30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016
PublisherInternational Council of the Aeronautical Sciences
ISBN (Electronic)9783932182853
Publication statusPublished - 2016
Event30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016 - Daejeon, Korea, Republic of
Duration: 2016 Sep 252016 Sep 30

Other

Other30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016
CountryKorea, Republic of
CityDaejeon
Period16/9/2516/9/30

Keywords

  • Folding wing
  • Low Reynolds number
  • Mars exploration
  • Parametric study
  • UAV

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Materials Science(all)

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  • Cite this

    Fujita, K., Nagai, H., & Oyama, A. (2016). Effect of yaw-tilted hinge axis on deployment robustness of mars airplane. In 30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016 International Council of the Aeronautical Sciences.