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Study of Pressure Oscillations in Supersonic Parachute

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Abstract

Supersonic parachutes are a critical element of planetary mission whose simple structure, light-weight characteristics together with high ratio of aerodynamic drag makes them the most suitable aerodynamic decelerators. The use of parachute in supersonic flow produces complex shock/shock and wake/shock interaction giving rise to dynamic pressure oscillations. The study of supersonic parachute is difficult, because parachute has very flexible structure which makes obtaining experimental pressure data difficult. In this study, a supersonic wind tunnel test using two rigid bodies is done. The wind tunnel test was done at Mach number 3 by varying the distance between the front and rear objects, and the distance of a bundle point which divides suspension lines and a riser. The analysis of Schlieren movies revealed shock wave oscillation which was repetitive and had large pressure variation. The pressure variation differed in each case of change in distance between the front and rear objects, and the change in distance between riser and the rear object. The causes of pressure oscillation are: interaction of wake caused by front object with the shock wave, fundamental harmonic vibration of suspension lines, interference between shock waves, and the boundary layer of suspension lines.

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Abbreviations

\(d_\mathrm{{s}}\) :

Diameter of suspension lines and riser

f :

Frequency

l :

Length of suspension line

L :

Distance between front and rear object

\(L_\mathrm{{s}}\) :

Distance between the bundling point and the leading edge of rear object

M :

Mach number

n :

Mode number

\(N_\mathrm{{s}}\) :

Number of suspension lines

\(P_{0}\) :

Total pressure behind shock wave

Re :

Reynolds number

t :

Time

T :

Tension

\(\gamma \) :

Specific heat ratio

\(\rho \) :

Linear density of suspension lines

1:

Before passing of shock wave

2:

After passing of shock wave

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Acknowledgements

We would like to thank ISAS, JAXA for providing us opportunities to use supersonic wind tunnel for conducting this research.

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Authors and Affiliations

  1. Department of Mechanical Engineering, Graduate School of Integrated Science and Technology, Shizuoka University, Hamamatsu, 432-8561, Japan

    Nimesh Dahal, Katsuyoshi Fukiba & Kazuki Mizuta

  2. Department of Space Systems and Astronautics, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, 252-5210, Japan

    Yusuke Maru

Authors
  1. Nimesh Dahal
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  2. Katsuyoshi Fukiba
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  3. Kazuki Mizuta
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  4. Yusuke Maru
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Corresponding author

Correspondence to Nimesh Dahal.

Additional information

An earlier version of this paper was presented at APISAT 2017, Seoul, Korea, October 2017.

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Dahal, N., Fukiba, K., Mizuta, K. et al. Study of Pressure Oscillations in Supersonic Parachute. JASS 19, 24–31 (2018). https://doi.org/10.1007/s42405-018-0025-3

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  • DOI: https://doi.org/10.1007/s42405-018-0025-3

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