Computational Aero-Structural Coupling For Hypersonic Applications

Haupt, Matthias; Niesner, Reinhold; Unger, Ralf; Horst, Peter

doi:10.2514/6.2006-3252

Cited by 36 publications

(19 citation statements)

References 9 publications

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“…The software visualization tool kit (VTK) in addition to the necessary modifications and algorithms [7] is used as interpolation routine for the Vulcain-2 grid. For the study of the Volvo-S6 wind tunnel nozzle, the commercial MPCCI toolkit was used.…”

Section: Interpolation Between Structural and Aerodynamic Partmentioning

confidence: 99%

“…Each of the coprocesses sets the boundary conditions, starts, stops, and controls a simulation code. The physical quantities are exchanged by means of conservative extended grid to grid interpolation routines [7] or optionally by commercial MPCCI routines. The coprocesses and the exchange of the physical quantities are controlled by a python script called control code, in which the coupling algorithm is implemented.…”

Section: Fluid-structure Couplingmentioning

confidence: 99%

“…While in these first studies simplified generic configurations of the launcher have been investigated, for the present work unstructured grids are generated including important geometric details such as the helium-shell, connectors between booster, and main body, as well as various other details and two different nozzle geometries. The launcher geometry corresponds to the NLR wind tunnel model as shown in [5] and the coupling by interpolation routines of the Technical University of Braunschweig [7] and the commercial multi-purpose code coupling interface (MPCCI) library [5]. After preliminary coupled simulations with a simplified FEM-description of the nozzle [5], a realistic structural description as well as a CFD grid of the Vulcain-2 nozzle contour is used.…”

Section: Introductionmentioning

confidence: 99%

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A fluid structure coupling of the Ariane-5 nozzle section during start phase by detached eddy simulation

Lüdeke¹,

Calvo²

2010

CEAS Space J

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Concerning the requirements of future rocket technologies, providing a cost-efficient access to orbit as well as an increase in system reliability, a deeper insight into the unsteady phenomena during ascent of modern launchers is essential. Unsteady interactions and resonances of the turbulent separated launcher wake and the nozzle structure play an important role for the design of future main stage propulsion systems. The so-called buffeting coupling phenomenon is one of the main challenges during ascent. In the present study, a coupled simulation of the afterbody of the Ariane-5 launcher with a realistic structural and aerodynamic representation of different nozzle configurations is carried out. On the computational fluid dynamics side, unsteady detached eddy simulations are coupled with structural computations for different nozzle configurations. The essential features of the interaction process are well captured. The coupling algorithm is validated by a nonlinear supersonic panel flutter simulation with highly transient mechanical interaction.

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Section: Interpolation Between Structural and Aerodynamic Partmentioning

confidence: 99%

Section: Fluid-structure Couplingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A fluid structure coupling of the Ariane-5 nozzle section during start phase by detached eddy simulation

Lüdeke¹,

Calvo²

2010

CEAS Space J

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“…The data transfer and in- [15] terpolation of the displacements and forces between the nonconforming grids is established with ifls, see [5]. Using the computational fluid mechanics(CFD) solver TAU [11] for the solution of the Euler equation (Dirichlet boundary conditions) the unknown aerodynamic forces of the fluid surface mesh can be computed.…”

Section: Fluid-structure Interactionmentioning

confidence: 99%

Extension and Application of a Nonlinear Reduced Order Model to Gust Load Prediction in Time Domain

Strobach¹,

Lindhorst²,

Haupt³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Abstract. This paper aims at extending a markov chain based reduced order model to discrete gust load prediction in an aeroelastic simulation. An method for the incorporation of the disturbance velocity approach is presented and evaluated for the AGARD445 wing based on different training strategies. The reduced order model trained under elastic and gust load conditions can successfully predict the gust response in a rigid and in an elastic setup. Thus the presented ROM approach can serve as one single CFD surrogate model to predict aerodynamic forces under multiple loading conditions.

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“…The developed simulation environment i §s covers both physical couplings in a partitioned approach using individual codes for the involved subdomains §uid and structure. A detailed description of i §s can be taken from [8]. Validation studies of coupled problems analyzed by di¨erent individual code combinations are presented in [810].…”

Section: Coupled Simulation Approachmentioning

confidence: 99%

Fluid-structure interaction analysis applied to thermal barrier coated cooled rocket thrust chambers with subsequent local investigation of delamination phenomena

Kowollik

Horst

Haupt

2013

Progress in Propulsion Physics

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The aim of this work is to investigate numerically thermal barrier coating (TBC) systems applied to realistic rocket thrust chamber conditions. A global full parametric three-dimensional (3D) modeling approach for cooled rocket thrust chambers is presented to be able to simulate the §uidstructure interaction (FSI) phenomena involved. In a subsequent analysis step, realistic mechanical and thermal boundary conditions are extracted from critical design regions of the global model and applied to a local ¦nite element model (FEM) to analyze possible TBC delaminations by means of a Fracture Mechanics (FM) approach.

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Computational Aero-Structural Coupling For Hypersonic Applications

Cited by 36 publications

References 9 publications

A fluid structure coupling of the Ariane-5 nozzle section during start phase by detached eddy simulation

A fluid structure coupling of the Ariane-5 nozzle section during start phase by detached eddy simulation

Extension and Application of a Nonlinear Reduced Order Model to Gust Load Prediction in Time Domain

Fluid-structure interaction analysis applied to thermal barrier coated cooled rocket thrust chambers with subsequent local investigation of delamination phenomena

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