On the Stability of Pitching Motion of Reentry Vehicle with the Tilted Toroidal Ballute

  • Hirotaka Otsu
  • Yoshiki Takama

Introduction

An aerodynamic ballute system is an inflatable large aerodynamic decelerating device that can enhance the drag force of the reentry vehicle system drastically. The enhanced drag force and large frontal area of the ballute can reduce the ballistic coefficient of the reentry vehicle system, which can mitigate the reentry heating drastically. Among various kinds of ballute configurations[1], we focused on the trailing toroidal ballute configuration as shown in Fig.1. Figure 1 shows the schematic view of the reentry vehicle system with the trailing toroidal ballute. In this configuration, the toroidal ballute is attached to the reentry capsule by several cables. For the above configuration, the aerodynamics and aerothermodynamics are investigated numerically and experimentally[2, 3]. Their results showed that the trailing toroidal ballute will be a candidate for the future reentry vehicle system among the various ballute configurations.

Keywords

Test Model Tilt Angle Schematic View Aerodynamic Force AIAA Paper 
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References

  1. 1.
    Rohrschneider, R.R., Braun, R.D.: Survey of Ballute Technology for Aerocapture. Journal of Spacecraft and Rockets 44(1), 10–23 (2007)CrossRefGoogle Scholar
  2. 2.
    Gnoffo, P.A., Buck, G., Moss, J.N., Nielsen, E., Berger, K., Jones, W.T., Rudavsky, R.: Aerothermodynamic Analyses of Towed Ballutes. AIAA Paper 2006-3771 (2001)Google Scholar
  3. 3.
    Rasheed, A., Fujii, K., Hornung, H.G.: Experimental Investigation of the Flow over a Toroidal Aerocapture Ballute. AIAA Paper 2001-2460 (2001)Google Scholar
  4. 4.
    Otsu, H.: Effect of Lift on the Reentry Vehicle System with the Trailing Toroidal Ballute. AIAA Paper 2008-0234 (January 2008)Google Scholar
  5. 5.
    Otsu, H., Abe, T.: Numerical and Experimental Investigation of Aerodynamic Characteristics of the Tilted Toroidal Ballute. AIAA Paper 2009-7410 (October 2009)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • Hirotaka Otsu
    • 1
  • Yoshiki Takama
    • 2
  1. 1.Ryukoku UniversityOtsuJapan
  2. 2.Japan Aerospace Exploration AgencyChofuJapan

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