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Numerical Simulation of the Supersonic Disk-Gap-Band Parachute by Using Implicit Coupling Method

  • Xue Yang , Li Yu EMAIL logo , Cheng Shen and Xiao Shun Zhao
Published/Copyright: July 14, 2017

Abstract

The implicit coupling method is applied to model the 0.8 m disk-band-gap parachute at Mach 2.0. The fluid and structure governing equations are solved by the Lower-Upper Symmetric Gauss-Seidel (LU-SGS) algorithm and Newmark scheme, respectively. By exchanging the numerical results of the coupling surface with Gauss-Seidel algorithm, high accuracy solutions at every physical time step are obtained. The numerical results of the canopy drag coefficient and projected area fit well with the wind tunnel test results. The simulation reproduces the shock oscillation and breathing phenomenon of the canopy that are usually observed in these systems at Mach 2.0. Furthermore, it is found that the unstable saddle point is the main reason for the shock oscillation of the canopy. And the unsynchronized phases of the canopy area and shock oscillation curves lead to the drag of the canopy oscillate in irregular state.

Funding statement: Funding of Jiangsu Innovation Program for Graduate Education, (Grant / Award Number: KYLX16_0402), the Fundamental Research Funds for the Central Universities and National Natural Science Foundation of China, (Grant / Award Number: ‘11272345’).

Acknowledgments

This work was co-supported by the National Natural Science Foundation of China (No. 11272345), Funding of Jiangsu Innovation Program for Graduate Education (KYLX16_0402) and the Fundamental Research Funds for the Central Universities. They are gratefully acknowledged by the author.

References

[1] J.R. Cruz, R.E. Mineck, D.F. Keller and M.V. Bobskill, Wind tunnel testing of various disk-gap-band parachutes, 17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, 2003.10.2514/6.2003-2129Search in Google Scholar

[2] K. Karagiozis, R. Kamakoti, F. Cirak and C. Pantano, A computational study of supersonic disk-gap-band parachutes using Large-Eddy simulation coupled to a structural membrane, J. Fluids Struct. 27 (2011), 175–192.10.1016/j.jfluidstructs.2010.11.007Search in Google Scholar

[3] L. Yu, H. Cheng, Y.N. Zhan and S.T. Li, Study of parachute inflation process using fluid–structure interaction method, Chinese J. Aeronaut 27 (2014), 272–279.10.1016/j.cja.2014.02.021Search in Google Scholar

[4] Y. Coquet and P. Bordenave, Improvements in fluid structure interaction simulation of parachute using LS-Dyna, 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, Dublin, 2011.10.2514/6.2011-2590Search in Google Scholar

[5] J.S. Lingard and M.G. Darley, Simulation of parachute fluid structure interaction in supersonic flow, 18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, 2005.10.2514/6.2005-1607Search in Google Scholar

[6] M. Barnhardt, T. Drayna, I. Nompelis, G.V. Candler and W. Garrard, Detached eddy simulations of the MSL parachute at supersonic conditions, 19th AIAA Aerodynamic Decelerator Technology Conference and Seminar, Williamsburg, 2007.10.2514/6.2007-2529Search in Google Scholar

[7] J. Zhang, N. Zhao, D.F. Ren et al., Application of the level set method on adaptive Cartesian grids, Explosion Shock Waves 28 (2008), 439–442.Search in Google Scholar

[8] R.L. Taylor, E. Onate and P.A. Ubach, Finite element analysis of membrane structures, Textile Composites Inflatable Struct. 33 (2005), 47–68.10.1007/1-4020-3317-6_4Search in Google Scholar

[9] L. Hong, D.B. Joseph and L. Rainald, An Ac-curate, Fast, Matrix-Free implicit method for computing unsteady flows on un-structured grids, 37th AIAA Aero-Space Sciences Meeting and Exhibit, 1999.Search in Google Scholar

[10] A. Sengupta, M. Wernet, J. Roeder and R. Kelsch, Supersonic testing of 0.8 m disk gap band parachutes in the wake of a subscale MSL entry vehicle, 20th AIAA Aerodynamic Decelerator Conference, 2009.10.2514/6.2009-2974Search in Google Scholar

[11] A. Sengupta, Fluid structure interaction of parachutes in supersonic planetary entry, 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, Dublin, Ireland, 2011.10.2514/6.2011-2541Search in Google Scholar

[12] A. Sengupta, M. Wernet and L. Hall, Temporal characteristics of disk gap band parachutes from Mach 2 to 2.5, Aerodynamic Decelerator Systems Technology Conferences, Daytona Beach, Florida, 2013.10.2514/6.2013-1330Search in Google Scholar

Received: 2016-3-23
Accepted: 2017-5-4
Published Online: 2017-7-14
Published in Print: 2017-7-26

© 2017 Walter de Gruyter GmbH, Berlin/Boston

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