Fluid–structure interaction modeling of complex parachute designs with the space–time finite element techniques

Sathe, Sunil; Benney, Richard; Charles, Richard; Doucette, Emily A.; Miletti, Jose A; Senga, Masayoshi; Stein, Keith; Tezduyar, Tayfun E.

doi:10.1016/j.compfluid.2005.07.010

Cited by 28 publications

(14 citation statements)

References 28 publications

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“…The first kind of these methods is good at providing accurate incompressible aerodynamic simulations, such as developing the semi-implicit method for pressure-linked equations (SIM-PLE algorithm), 1,2 applying the immersed boundary method 3,4 or the front tracking method. 5 The second kind uses a real parachute configuration and the finite element method to simulate both the structure and fluid dynamic behavior, including the space-time fluid structure interaction (FSI)technique [6][7][8][9][10][11] and commercial software LS-DYNA, [12][13][14] which uses the Eulerian-Langrangian penalty coupling algorithm and the multimaterial Eulerian formulation based fluid solver to simulate parachute problems. Restricted by the complex configuration of a real parachute system, the first kind of methods usually uses a semi-experimental 15,16 hypothesis to establish a parachute canopy model or upgrade the mass-spring damper (MSD) model to treat the parachute canopy as a virtual spring net system.…”

Section: Introductionmentioning

confidence: 99%

Simulation of 3D parachute fluid–structure interaction based on nonlinear finite element method and preconditioning finite volume method

Fan

Xia

2014

Chinese Journal of Aeronautics

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A fluid-structure interaction method combining a nonlinear finite element algorithm with a preconditioning finite volume method is proposed in this paper to simulate parachute transient dynamics. This method uses a three-dimensional membrane-cable fabric model to represent a parachute system at a highly folded configuration. The large shape change during parachute inflation is computed by the nonlinear Newton-Raphson iteration and the linear system equation is solved by the generalized minimal residual (GMRES) method. A membrane wrinkling algorithm is also utilized to evaluate the special uniaxial tension state of membrane elements on the parachute canopy. In order to avoid large time expenses during structural nonlinear iteration, the implicit Hilber-Hughes-Taylor (HHT) time integration method is employed. For the fluid dynamic simulations, the Roe and HLLC (Harten-Lax-van Leer contact) scheme has been modified and extended to compute flow problems at all speeds. The lower-upper symmetric Gauss-Seidel (LU-SGS) approximate factorization is applied to accelerate the numerical convergence speed. Finally, the test model of a highly folded C-9 parachute is simulated at a prescribed speed and the results show similar characteristics compared with experimental results and previous literature. ª 2014 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA.

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Section: Introductionmentioning

confidence: 99%

Simulation of 3D parachute fluid–structure interaction based on nonlinear finite element method and preconditioning finite volume method

Fan

Xia

2014

Chinese Journal of Aeronautics

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“…Transonic flow past a sphere was also reported in 2006 [52]. The FSI computations reported in 2007 [5,[53][54][55][56][57] and 2008 [58][59][60][61][62][63] were for flow past a flag, patient-specific models of a middle cerebral artery with aneurysm and a birfucating middle cerebral artery with aneurysm, carotid artery birfucation, abdominal aortic aneurysms, parachutes with complex designs, a cloth piece falling over a rigid rod, flow in a tube constrained with a diaphragm, inflation of a balloon, flow through and around a windsock, descent of a T-10 parachute with fabric porosity, sails, Orion spacecraft parachutes, flow around two flexible spheres colliding, and a flexible sphere sliding past a constriction in a channel.…”

Section: Years 2001-2010mentioning

confidence: 91%

Space–time computations in practical engineering applications: a summary of the 25-year history

Tezduyar

Takizawa

2018

Comput Mech

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In an article published online in July 2018 it was stated that the algorithm proposed in the article is "enabling practical implementation of the space-time FEM for engineering applications." In fact, space-time computations in practical engineering applications were already enabled in 1993. We summarize the computations that have taken place since then. These computations started with finite element discretization and are now also with isogeometric discretization. They were all in 3D space and were all carried out on parallel computers. For quarter of a century, these computations brought solution to many classes of complex problems ranging from Orion spacecraft parachutes to wind turbines, from patient-specific cerebral aneurysms to heart valves, from thermo-fluid analysis of ground vehicles and tires to turbocharger turbines and exhaust manifolds.

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“…There exist several approaches to perform this analysis, starting from the simplest one, where the nozzle is characterized only by the mass, the inertia and a torsional spring at the throat, to more complex FSI models [34] as the one studied in this work.…”

Section: Aeroelastic Frequency Shiftingmentioning

confidence: 99%

Fluid–structure interaction study of the start-up of a rocket engine nozzle

2010

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a b s t r a c tThe aim of this paper is to analyze the aeroelastic processes developed during the starting phase of a rocket engine via a coupling fluid/structure code. This analysis gives a better understanding of the behavior of the structure as the shock waves propagate inside the engine nozzle. The gasdynamics Euler equations are solved for the fluid and constitutive linear elastic solid assuming large displacements and rotations with no material damping is adopted for the structure. The coupling of each subproblem is carried out with a Gauß-Seidel algorithm over the fluid and structure states. For the fluid problem an ALE (Arbitrary Lagrangian-Eulerian) formulation is used. It allows us to define a reference system following the moving boundaries while the structure is deformed. The code is validated with a study of the flutter phenomena that may occur when a supersonic compressible fluid flows over a flat solid plate. Regarding the rocket engine ignition problem, a modal analysis of the structure is performed in order to analyze the eigenfrequency shifts when considering the coupling with the fluid flow.

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Fluid–structure interaction modeling of complex parachute designs with the space–time finite element techniques

Cited by 28 publications

References 28 publications

Simulation of 3D parachute fluid–structure interaction based on nonlinear finite element method and preconditioning finite volume method

Simulation of 3D parachute fluid–structure interaction based on nonlinear finite element method and preconditioning finite volume method

Space–time computations in practical engineering applications: a summary of the 25-year history

Fluid–structure interaction study of the start-up of a rocket engine nozzle

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