Simulating solid propellant rockets at CSAR

Heath, Michael T.; Fiedlerf, Robert A.; Dick, William A.

doi:10.2514/6.2000-3455

Cited by 4 publications

(4 citation statements)

References 5 publications

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“…The CSAR Rocket Code [12] is an integrated, wholesystem solid propellant rocket simulation. It focuses on propellant combustion, turbulent flows, rocket case and nozzle structures under both normal and abnormal operations, component aging and other failure models.…”

Section: Csar Rocketmentioning

confidence: 99%

Compact Application Signatures for Parallel and Distributed Scientific Codes

Lü

Reed²

2002

ACM/IEEE SC 2002 Conference (SC'02)

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Understanding the dynamic behavior of parallel programs is key to developing efficient system software and runtime environments; this is even more true on emerging computational Grids where resource availability and performance can change in unpredictable ways. Event tracing provides details on behavioral dynamics, albeit often at great cost. We describe an intermediate approach, based on curve fitting, that retains many of the advantages of event tracing but with lower overhead. These compact "application signatures" summarize the time-varying resource needs of scientific codes from historical trace data. We also developed a comparison scheme that measures similarity between two signatures, both across executions and across execution environments.

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Section: Csar Rocketmentioning

confidence: 99%

Compact Application Signatures for Parallel and Distributed Scientific Codes

Lü

Reed²

2002

ACM/IEEE SC 2002 Conference (SC'02)

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“…Hence, there is no need to keep into account mixing processes between oxidiser and reducer. Much effort has been done in research oriented to the CFD applied to solid propellant combustion, see for example [4,5].…”

Section: Introductionmentioning

confidence: 99%

Numerical modelling of gas-solid interface for homogeneous propellant combustion

Peratta¹

2007

WIT Transactions on the Built Environment, Vol 92

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This paper reports on the implementation and results obtained with a timedependent Arbitrary Lagrangian-Eulerian Finite Volume calculation for modelling the fluid-solid interface in laminar burning of solid energetic materials. The formulation is based on the conservation equations of mass, momentum and energy troughout the moving interface. Degradation-pirolysis and combustion are taken into account in the solid and gase phase, respectively. The chemical model is implemented with 7 unidirectional global reactions and 12 reactive species. The outcomes of the model are pressure, temperature, density, heat release, species concentration, gas speed and bulk burning rate. The numerical model is able to describe the main characteristics of the flame structure, including the induction (dark) zone. Burning rates and species concentration profiles are in good agreement with experimental measurements and previously published literature. The method can be used to study a variety of time-dependent processes including transient ignition, extinction, and combustion instabilities.

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“…The primary goal of the Center for Simulation of Advanced Rockets is to perform detailed, whole-system simulations, making use of science-based models rather than empirical relations whenever possible 1,2 . Obtaining accurate numerical solutions to such a complex problem requires enormous computational resources.…”

Section: Introductionmentioning

confidence: 99%

Coupled fluid-structure 3-D solid rocket motor simulations

Fiedler

Jiao

Namazifard

et al. 2001

37th Joint Propulsion Conference and Exhibit

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We describe our numerical method for threedimensional simulations of solid rocket motors in which the internal gas dynamics, the combustion of the propellant, and the structural response are fully coupled. The combustion zone is treated as a thin layer using appropriate jump conditions, and the regression rate is determined using a nonlinear dynamic combustion model. An Arbitrary Lagrangian-Eulerian formulation is used in the gas dynamics and structural mechanics modules to follow the regression of the propellant. We demonstrate the parallel scalability of our ALE implementation and its ability to handle significant burn back of the propellant on a model problem with a very high burn rate.

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Simulating solid propellant rockets at CSAR

Cited by 4 publications

References 5 publications

Compact Application Signatures for Parallel and Distributed Scientific Codes

Compact Application Signatures for Parallel and Distributed Scientific Codes

Numerical modelling of gas-solid interface for homogeneous propellant combustion

Coupled fluid-structure 3-D solid rocket motor simulations

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