Titan IV SRMU anomaly and redesign analyses

Chang, I-Shih; Patel, N.; Yang, Shangbin

doi:10.2514/6.1994-3284

Cited by 5 publications

(6 citation statements)

References 1 publication

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Section: Grain Deformation In the Titan IV Solid Rocket Motorsupporting

confidence: 79%

“…A uniform , following data presented in Reference [36]. The deformation of the grain in the aft segment at the centre-aft joint in shown in Figure 25, and is qualitatively similar to that shown in Reference [36]. The times required to perform a single linear matrix equation solve using the SGI Origin2000 and the IBM Blue Horizon are shown in Table IV.…”

Section: Grain Deformation In the Titan IV Solid Rocket Motorsupporting

confidence: 65%

“…The structural analysis code built around the multigrid algorithm discussed in this paper has been used as a component code in the coupled analyses of solid rocket motors (see Reference [35] for a discussion of the algorithms employed). Other researchers have investigated a failure of the Titan IV solid rocket motor resulting from the large deformation of a portion of the solid propellant [36]. As a prelude to a complete analysis of this system, a structural analysis was performed using the model of the Titan IV shown in Figure 22.…”

Section: Grain Deformation In the Titan IV Solid Rocket Motormentioning

confidence: 99%

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A distributed memory parallel implementation of the multigrid method for solving three‐dimensional implicit solid mechanics problems

Namazifard

Parsons

2004

Numerical Meth Engineering

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SUMMARYWe describe the parallel implementation of a multigrid method for unstructured finite element discretizations of solid mechanics problems. We focus on a distributed memory programming model and use the MPI library to perform the required interprocessor communications. We present an algebraic framework for our parallel computations, and describe an object-based programming methodology using Fortran90. The performance of the implementation is measured by solving both fixed-and scaled-size problems on three different parallel computers (an SGI Origin2000, an IBM SP2 and a Cray T3E). The code performs well in terms of speedup, parallel efficiency and scalability. However, the floating point performance is considerably below the peak values attributed to these machines. Lazy processors are documented on the Origin that produce reduced performance statistics. The solution of two problems on an SGI Origin2000, an IBM PowerPC SMP and a Linux cluster demonstrate that the algorithm performs well when applied to the unstructured meshes required for practical engineering analysis.

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Section: Grain Deformation In the Titan IV Solid Rocket Motorsupporting

confidence: 79%

Section: Grain Deformation In the Titan IV Solid Rocket Motorsupporting

confidence: 65%

Section: Grain Deformation In the Titan IV Solid Rocket Motormentioning

confidence: 99%

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A distributed memory parallel implementation of the multigrid method for solving three‐dimensional implicit solid mechanics problems

Namazifard

Parsons

2004

Numerical Meth Engineering

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“…点火瞬态, 作用在推进剂表面的燃气压强是不断变化的动态过程. 耦合分析点火瞬间药柱变形, 可采用在流动模型中加入变形系数矩阵的方法 [15] , 也可采用在每一个时间步内同时求解流动和变形的 http://engine.scichina.com/doi/10.1360/ze2011-41-6-703 方法 [16] . 前一种方法应用于 Titan PQM-1 发动机, 原理是在环形槽部分建立二维流动模型, 在后段药柱选择关键点根据实验数据建立药柱变形系数矩阵, 通过求解压强结合系数矩阵得到药柱的变形.…”

Section: 药柱变形研究现状unclassified

固体火箭发动机点火瞬间流固耦合综述

李¹,

曹²,

李³

et al. 2011

Sci. Sin.-Tech.

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“…Chang et al 33 adopted a quasi-static approach, in which the load on the propellant surface due to the fluid pressure at each of nine different times (i.e., after each very large system time step) was applied in a static structural analysis using ABAQUS to determine a new propellant geometry for the next fluids time step. This method successfully captured the slumping for a propellant Young's modulus ~8.3 MPa, but would have missed any oscillatory or non-axisymmetric motion of the propellant.…”

Section: Slumping In the Titan IV Srmumentioning

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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Titan IV SRMU anomaly and redesign analyses

Cited by 5 publications

References 1 publication

A distributed memory parallel implementation of the multigrid method for solving three‐dimensional implicit solid mechanics problems

A distributed memory parallel implementation of the multigrid method for solving three‐dimensional implicit solid mechanics problems

固体火箭发动机点火瞬间流固耦合综述

Simulations of Slumping Propellant and Flexing Inhibitors in Solid Rocket Motors

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