Fully-coupled fluid-structure interaction simulations of a supersonic parachute

Jonathan Boustani; Michael F. Barad; Cetin C. Kiris; Christoph Brehm

doi:10.2514/6.2019-3279

Fully-coupled fluid-structure interaction simulations of a supersonic parachute

Jonathan Boustani, Michael F. Barad, Cetin C. Kiris, Christoph Brehm

Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

8 Scopus citations

Abstract

A validated computational fluid-structure interaction method for simulating the complex interaction between the large deformation of very thin, highly deformable structures and compressible flows is extended to consider large-scale problems in supersonic flows using parallel computing. The coupled fluid-structure interaction system is solved in a partitioned, or weakly-coupled, manner. The foundations of the applied fluid-structure interaction method are a higher-order, block-structured Cartesian, sharp immersed boundary method for the compressible Navier-Stokes equations and a computational structural dynamics solver employing a geometrically nonlinear 3-node shell element based on the mixed interpolation of tensorial components formulation. The method is applied to large deformation fluid-structure interaction validation cases before being applied to the inflation of a supersonic parachute in the upper Martian atmosphere where the goal is to demonstrate the capabilities of the solver when considering large-scale problems in supersonic flows.

Original language	English
Title of host publication	AIAA Aviation 2019 Forum
Pages	1-22
Number of pages	22
DOIs	https://doi.org/10.2514/6.2019-3279
State	Published - 2019
Event	AIAA Aviation 2019 Forum - Dallas, United States Duration: Jun 17 2019 → Jun 21 2019

Publication series

Name	AIAA Aviation 2019 Forum

Conference

Conference	AIAA Aviation 2019 Forum
Country/Territory	United States
City	Dallas
Period	6/17/19 → 6/21/19

Bibliographical note

Funding Information:
JB was funded by the NASA Kentucky EPSCoR Research Infrastructure Development Grant (RIDG) program through grant number RIDG-17-005 with Dr. S. Smith as program director. CB greatly acknowledges funding from NASA Ames Computational Aeroscience Branch under contract 80NSSC18K0883. Computing resources were provided by the NASA Advanced Supercomputing systems Pleiades and Electra. The authors thank John Higgins for his contributions to the sketches in this paper.

Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

ASJC Scopus subject areas

Computer Science Applications
Electrical and Electronic Engineering
Aerospace Engineering

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10.2514/6.2019-3279

Cite this

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title = "Fully-coupled fluid-structure interaction simulations of a supersonic parachute",

abstract = "A validated computational fluid-structure interaction method for simulating the complex interaction between the large deformation of very thin, highly deformable structures and compressible flows is extended to consider large-scale problems in supersonic flows using parallel computing. The coupled fluid-structure interaction system is solved in a partitioned, or weakly-coupled, manner. The foundations of the applied fluid-structure interaction method are a higher-order, block-structured Cartesian, sharp immersed boundary method for the compressible Navier-Stokes equations and a computational structural dynamics solver employing a geometrically nonlinear 3-node shell element based on the mixed interpolation of tensorial components formulation. The method is applied to large deformation fluid-structure interaction validation cases before being applied to the inflation of a supersonic parachute in the upper Martian atmosphere where the goal is to demonstrate the capabilities of the solver when considering large-scale problems in supersonic flows.",

author = "Jonathan Boustani and Barad, {Michael F.} and Kiris, {Cetin C.} and Christoph Brehm",

note = "Funding Information: JB was funded by the NASA Kentucky EPSCoR Research Infrastructure Development Grant (RIDG) program through grant number RIDG-17-005 with Dr. S. Smith as program director. CB greatly acknowledges funding from NASA Ames Computational Aeroscience Branch under contract 80NSSC18K0883. Computing resources were provided by the NASA Advanced Supercomputing systems Pleiades and Electra. The authors thank John Higgins for his contributions to the sketches in this paper. Publisher Copyright: {\textcopyright} 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; AIAA Aviation 2019 Forum ; Conference date: 17-06-2019 Through 21-06-2019",

year = "2019",

doi = "10.2514/6.2019-3279",

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PY - 2019

Y1 - 2019

N2 - A validated computational fluid-structure interaction method for simulating the complex interaction between the large deformation of very thin, highly deformable structures and compressible flows is extended to consider large-scale problems in supersonic flows using parallel computing. The coupled fluid-structure interaction system is solved in a partitioned, or weakly-coupled, manner. The foundations of the applied fluid-structure interaction method are a higher-order, block-structured Cartesian, sharp immersed boundary method for the compressible Navier-Stokes equations and a computational structural dynamics solver employing a geometrically nonlinear 3-node shell element based on the mixed interpolation of tensorial components formulation. The method is applied to large deformation fluid-structure interaction validation cases before being applied to the inflation of a supersonic parachute in the upper Martian atmosphere where the goal is to demonstrate the capabilities of the solver when considering large-scale problems in supersonic flows.

AB - A validated computational fluid-structure interaction method for simulating the complex interaction between the large deformation of very thin, highly deformable structures and compressible flows is extended to consider large-scale problems in supersonic flows using parallel computing. The coupled fluid-structure interaction system is solved in a partitioned, or weakly-coupled, manner. The foundations of the applied fluid-structure interaction method are a higher-order, block-structured Cartesian, sharp immersed boundary method for the compressible Navier-Stokes equations and a computational structural dynamics solver employing a geometrically nonlinear 3-node shell element based on the mixed interpolation of tensorial components formulation. The method is applied to large deformation fluid-structure interaction validation cases before being applied to the inflation of a supersonic parachute in the upper Martian atmosphere where the goal is to demonstrate the capabilities of the solver when considering large-scale problems in supersonic flows.

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Fully-coupled fluid-structure interaction simulations of a supersonic parachute

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