An efficient, intelligent solution for viscous flows inside solid rocket motors

Chang, I-Shih

doi:10.2514/6.1991-2429

Cited by 8 publications

(5 citation statements)

References 7 publications

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“…Similar 7 to those discussed in Ref. 8 for the flow analysis, the advantages of using the present method for the thermal analysis are as follows: "* Easy implementation of an exact design configuration "* Optimum use of computational resources "• High-resolution analysis results for minimum cost "* Elimination of elapsed time through an automated procedure "* Same procedure for any complicated configuration "* Same mesh generation program for different applications, e.g., flow and structural analyses "* Significant reduction in effort required for a high-resolution solution of transient heat transfer in a multi-material structure…”

supporting

confidence: 68%

“…Because of its capability and flexibility to produce computational mesh efficiently for an arbitrary domain, the adaptive, unstructured, finite-element mesh generation is especially suitable for the problem involving a receding boundary as that demonstrated in Ref. 8 for the flow analysis and can be refined further to analyze the thermal problem involving moving boundaries. The solution procedure discussed in this study is equally applicable to a structural stress analysis.…”

Section: Figure 14 Star-37s Motor Assemblymentioning

confidence: 99%

“…5 and was streamlined for rocket motor internal flow analysis in Ref. 8 and for multi-material, thermal analysis in this study. To simplify the numerical solution procedure and data transmission between the mesh generation program MESHRT and the finite-element analysis program ABAQUS, two auxiliary computer programs MHTOAB and ABTOMH are developed.…”

Section: Solution Proceduresmentioning

confidence: 99%

“…5 through 7 and was extended and streamlined to the solution of axisymmetric flows inside solid rocket motors of arbitrary configuration with nonuniform inlet boundary conditions in Ref. 8. In this study, the technique is extended further to multi-material, grid generation for transient heat conduction.…”

mentioning

confidence: 99%

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Adaptive, unstructured, finite element, multimaterial, thermal analysis

Chang

1993

Journal of Spacecraft and Rockets

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supporting

confidence: 68%

Section: Figure 14 Star-37s Motor Assemblymentioning

confidence: 99%

Section: Solution Proceduresmentioning

confidence: 99%

mentioning

confidence: 99%

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Adaptive, unstructured, finite element, multimaterial, thermal analysis

Chang

1993

Journal of Spacecraft and Rockets

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“…The recirculation bubble in the cavity has changed its size and shape as the time progresses. The centreline Mach number and pressure (p/p 0 ) for different burn-back geometries were compared with numerical results 20 in Fig. 5 and a good match has been obtained.…”

Section: Results and Discussion 31 Single-phase Calculation Of Titamentioning

confidence: 92%

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi¹,

Kumar²,

Chakraborty³

2015

DSJ

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New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

Xiao

Amano

Cai

et al. 2005

Journal of Heat Transfer

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Use of aluminized composite solid propellants and submerged nozzles are common in solid rocket motors (SRM). Due to the generation of slag, which injects into a combusted gas flow, a two-phase flow pattern is one of the main flow characteristics that need to be investigated in SRM. Validation of two-phase flow modeling in a solid rocket motor combustion chamber is the focus of this research. The particles’ boundary conditions constrain their trajectories, which affect both the two-phase flow calculations, and the evaluation of the slag accumulation. A harsh operation environment in the SRM with high temperatures and high pressure makes the measurement of the internal flow field quite difficult. The open literature includes only a few sets of experimental data that can be used to validate theoretical analyses and numerical calculations for the two-phase flow in a SRM. Therefore, mathematical models that calculate the trajectories of particles may reach different conclusions mainly because of the boundary conditions. A new method to determine the particle velocities on the solid propellant surface is developed in this study, which is based on the x-ray real-time radiography (RTR) technique, and is coupled with the two-phase flow numerical simulation. Other methods imitate the particle ejection from the propellant surface. The RTR high-speed motion analyzer measures the trajectory of the metal particles in a combustion chamber. An image processing software was developed for tracing a slug particle path with the RTR images in the combustion chamber, by which the trajectories of particles were successfully obtained.

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An efficient, intelligent solution for viscous flows inside solid rocket motors

Cited by 8 publications

References 7 publications

Adaptive, unstructured, finite element, multimaterial, thermal analysis

Adaptive, unstructured, finite element, multimaterial, thermal analysis

Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

New Method to Determine the Velocities of Particles on a Solid Propellant Surface in a Solid Rocket Motor

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