Parallel structural analysis of solid rocket motors

A Namazifard; I Parsons; A Acharya; E Taciroglu; J Hales

doi:10.2514/6.2000-3457

Parallel structural analysis of solid rocket motors

A Namazifard
, I Parsons
, A Acharya
, E Taciroglu
, J Hales

Scientific Computing & AI

Research output: Contribution to conference › Paper › peer-review

Abstract

We describe a parallel structural analysis code, ROCSOLID, that has been developed to model the structural response of solid rocket motors. ROCSOLID is based on an implicit finite element discretization of the rocket geometry. A scalable multigrid solver is used to solve the system of linear matrix equations encountered at each time step. Newton iteration is employed to treat the various nonlinearities required by a realistic model. Moving interfaces (i.e., combustion interfaces) are treated using an ALE formulation. © 2000 by the American Institute of Aeronautics and Astronautics.

Original language	English
Pages	3457
Number of pages	1
DOIs	https://doi.org/10.2514/6.2000-3457
State	Published - Jul 24 2000
Event	36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Las Vegas, United States Duration: Jul 24 2000 → Jul 28 2000

Conference

Conference	36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Country/Territory	United States
City	Las Vegas
Period	07/24/00 → 07/28/00

Keywords

Structural Analysis
Solid Rocket Motor
Arbitrary Lagrangian Eulerian
Rockets
Conjugate Gradient Algorithm
Solid Propellants
Explicit and Implicit Methods
Interprocessor Communication
Conjugate Gradient Method
Solid Rockets

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title = "Parallel structural analysis of solid rocket motors",

abstract = "We describe a parallel structural analysis code, ROCSOLID, that has been developed to model the structural response of solid rocket motors. ROCSOLID is based on an implicit finite element discretization of the rocket geometry. A scalable multigrid solver is used to solve the system of linear matrix equations encountered at each time step. Newton iteration is employed to treat the various nonlinearities required by a realistic model. Moving interfaces (i.e., combustion interfaces) are treated using an ALE formulation. {\textcopyright} 2000 by the American Institute of Aeronautics and Astronautics.",

keywords = "Structural Analysis, Solid Rocket Motor, Arbitrary Lagrangian Eulerian, Rockets, Conjugate Gradient Algorithm, Solid Propellants, Explicit and Implicit Methods, Interprocessor Communication, Conjugate Gradient Method, Solid Rockets",

author = "A Namazifard and I Parsons and A Acharya and E Taciroglu and J Hales",

year = "2000",

month = jul,

day = "24",

doi = "10.2514/6.2000-3457",

language = "English",

pages = "3457",

note = "36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; Conference date: 24-07-2000 Through 28-07-2000",

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TY - CONF

T1 - Parallel structural analysis of solid rocket motors

AU - Namazifard, A

AU - Parsons, I

AU - Acharya, A

AU - Taciroglu, E

AU - Hales, J

PY - 2000/7/24

Y1 - 2000/7/24

N2 - We describe a parallel structural analysis code, ROCSOLID, that has been developed to model the structural response of solid rocket motors. ROCSOLID is based on an implicit finite element discretization of the rocket geometry. A scalable multigrid solver is used to solve the system of linear matrix equations encountered at each time step. Newton iteration is employed to treat the various nonlinearities required by a realistic model. Moving interfaces (i.e., combustion interfaces) are treated using an ALE formulation. © 2000 by the American Institute of Aeronautics and Astronautics.

AB - We describe a parallel structural analysis code, ROCSOLID, that has been developed to model the structural response of solid rocket motors. ROCSOLID is based on an implicit finite element discretization of the rocket geometry. A scalable multigrid solver is used to solve the system of linear matrix equations encountered at each time step. Newton iteration is employed to treat the various nonlinearities required by a realistic model. Moving interfaces (i.e., combustion interfaces) are treated using an ALE formulation. © 2000 by the American Institute of Aeronautics and Astronautics.

KW - Structural Analysis

KW - Solid Rocket Motor

KW - Arbitrary Lagrangian Eulerian

KW - Rockets

KW - Conjugate Gradient Algorithm

KW - Solid Propellants

KW - Explicit and Implicit Methods

KW - Interprocessor Communication

KW - Conjugate Gradient Method

KW - Solid Rockets

UR - https://www.researchgate.net/publication/247108183_Parallel_Structural_Analysis_of_Solid_Rocket_Motors

U2 - 10.2514/6.2000-3457

DO - 10.2514/6.2000-3457

M3 - Paper

SP - 3457

T2 - 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Y2 - 24 July 2000 through 28 July 2000

ER -

Parallel structural analysis of solid rocket motors

Abstract

Conference

Keywords

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