Parallel structural analysis of solid rocket motors

Namazifard, A.; Parsons, I. D.; Acharya, Amit; Taciroğlu, Ertuǧrul; Hales, Jan Harry

doi:10.2514/6.2000-3457

Cited by 10 publications

(5 citation statements)

References 11 publications

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“…As mentioned earlier, we focus here on the application of the ALE methods for problems involving regressing solid domains. An example of such a problem is the burning solid-propellant fuel of a rocket engine [12] where a portion of the material becomes extinct due to combustion. For this type of problems, ALE kinematics may be used to map the reference domain (i.e., the mesh) onto the current volume of the material domain at its boundaries.…”

Section: Ale Kinematics As Applied To Eroding Bodiesmentioning

confidence: 99%

“…Thus, this is a reasonable three-dimensional test of the ALE formulation described earlier for eroding bodies, and its implementation. The application of the method to practical problems, e.g., simulation of solid-propellant rockets, can be found elsewhere [12,10].…”

Section: Regressing Ellipsoidal Cavity With Internal Pressurementioning

confidence: 99%

“…doi:10.1016/j.compstruc.2008. 12.008 material domain. The change in geometry may be associated with additional surface tractions (e.g., reactive forces caused by mass transfer due to phase changes).…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Arbitrary Lagrangian–Eulerian methods for analysis of regressing solid domains and interface tracking

Taciroğlu

Acharya

Namazifard

et al. 2009

Computers & Structures

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Section: Ale Kinematics As Applied To Eroding Bodiesmentioning

confidence: 99%

Section: Regressing Ellipsoidal Cavity With Internal Pressurementioning

confidence: 99%

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Arbitrary Lagrangian–Eulerian methods for analysis of regressing solid domains and interface tracking

Taciroğlu

Acharya

Namazifard

et al. 2009

Computers & Structures

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“…For problems in which no interface moves through the material (e.g., burn times so short that the regression of the propellant is negligible), the linear system resulting from the equations of motion is symmetric and can be solved most efficiently using a scalable parallel multigrid method 12 . For problems with significant propellant burn-back, the equations of motion are expressed in a parametric domain which is mapped to an evolving undeformed reference configuration 13 . The resulting linear system is non-symmetric, and a BiCGSTAB method is used.…”

Section: Structural Mechanics Solver: Rocsolidmentioning

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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“…This implicit/explicit coupling scheme is In the next several subsections, we describe in more detail the individual components of the GEN2 package, particularly those which were not included in GEN1. Rocsolid is described in detail elsewhere 5 , while Rocflu is currently under development.…”

Section: Overview Of the Gen2 Simulation Packagementioning

confidence: 99%

Simulations of Slumping Propellant and Flexing Inhibitors in Solid Rocket Motors

Fiedler

Breitenfeld

Jiao

et al. 2002

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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We describe and present results from GEN2, the second-generation three-dimensional solid rocket motor simulation package developed at CSAR. The internal gas dynamics, propellant combustion, and structural response are fully coupled. In addition to several test cases, we simulate propellant slumping at a joint slot due to uneven gas pressure loads in the Titan IV SRMU. We also study the motion of a flexible inhibitor and its effect on the gas flow near a joint slot in a section of a typical large solid rocket motor. IntroductionDetailed 3-D simulation of solid rocket motors requires solving a very complex, tightly coupled multiphysics problem that includes a wide range of length and time scales. Obtaining accurate numerical solutions for relatively simple geometries, physical models, and even fairly short burn times, requires enormous computational resources that are available today only at major supercomputing centers. Each physics module (gas dynamics, structural mechanics, etc.) must run efficiently in parallel on many processors and data must be exchanged frequently between modules in order to solve the tightly coupled system.

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Parallel structural analysis of solid rocket motors

Cited by 10 publications

References 11 publications

Arbitrary Lagrangian–Eulerian methods for analysis of regressing solid domains and interface tracking

Arbitrary Lagrangian–Eulerian methods for analysis of regressing solid domains and interface tracking

Coupled fluid-structure 3-D solid rocket motor simulations

Simulations of Slumping Propellant and Flexing Inhibitors in Solid Rocket Motors

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