Linear Analysis of Erosive Burning in Solid Propellant Motors

2009 ◽  
Author(s):  
Luca Massa
Keyword(s):  
Solid Propellant ◽  
Linear Analysis ◽  
Erosive Burning

Solid-propellant erosive burning

1992 ◽  
Vol 8 (4) ◽  
pp. 741-747 ◽  
Author(s):  
J. C. Godon ◽  
J. Duterque ◽  
G. Lengelle
Keyword(s):  
Solid Propellant ◽  
Erosive Burning

scholarly journals The generation of axial vorticity in solid-propellant rocket-motor flows

2001 ◽  
Vol 429 ◽  
pp. 283-305 ◽  
Author(s):  
S. BALACHANDAR ◽  
J. D. BUCKMASTER ◽  
M. SHORT
Keyword(s):  
Solid Propellant ◽  
Reynolds Numbers ◽  
Linear Analysis ◽  
Rocket Motor ◽  
Cautionary Note ◽  
Small Deviations ◽  
Perturbation Amplitude ◽  
Vortex Effect ◽  
Solid Propellant Rocket ◽  
Propellant Rocket

We examine small deviations from axial symmetry in a solid-propellant rocket motor, and describe a ‘bath-tub-vortex’ effect, in which substantial axial vorticity is generated in a neighbourhood of the chamber centreline. The unperturbed flow field is essentially inviscid at modest Reynolds numbers, even at the chamber walls, as has long been known, but the inviscid perturbed flow is singular at the centreline, and viscous terms are required to regularize it. We examine perturbations sufficiently small that a linear analysis is valid everywhere (εRe small, where ε is a measure of the perturbation amplitude and Re is a Reynolds number), and larger perturbations in which a nonlinear patch is created near the centreline of radius O(√ε). Our results provide an explanation of swirl experimentally observed by others, and a cautionary note for those concerned with numerical simulations of these flows, whether laminar or turbulent.

Numerical simulation of ignition transient in solid rocket motor: a revisit

2017 ◽  
Vol 89 (6) ◽  
pp. 936-945 ◽  
Author(s):  
Junaid Godil ◽  
Ali Kamran
Keyword(s):  
Flow Field ◽  
Motor Development ◽  
Solid Propellant ◽  
Research Effort ◽  
Solid Rocket Motor ◽  
Content Type ◽  
Rocket Motors ◽  
One Dimensional ◽  
Erosive Burning ◽  
Solid Rocket

Purpose The capability to predict and evaluate the motor pressure during each phase by means of a numerical analysis can significantly increase the efficiency of the preliminary design process with a reduction of both the motor development and operational costs. This paper aims to perform numerical simulation to analyze the ignition transient in solid rocket motor by solving Euler equation coupled with some semi-empirical correlations. These relations take into account the main phenomena affecting the ignition transient. Coupling relationships include the heat transfer of the gas to the propellant and erosive burning rate relationship. Design/methodology/approach The current research effort divides motor into series of control volumes along the port axis, and the variation of port area, burning surface and burning rate along the port are taken into account. A set of governing equations are then solved using explicit, time-dependent, predictor-corrector finite difference method. The numerical model helps to capture and embed shock wave associated with igniter flow within the solution. Second-order artificial viscosity dampens out the numerical oscillations due to sharp gradient within the flow field. The developed computer code predicts the start-up characteristics of motor. The study also provides comparison of simulation results with in-house experimental motor. Findings Simulations are performed with and without erosive burning to demonstrate that the flow model is a good physical approximation of motor. Numerical results calculated by this model without erosive burning are not in good agreement with experimental results. This minor discrepancy has motivated the inclusion of erosive burning in numerical model. The simulated results are then compared with the experimental data for head-end and rear-end pressure. The agreement between simulation and experiment is remarkable. In summary, major finding of this study is that unsteady quasi-one-dimensional gas dynamic model can capture the flow field in the motor during ignition transient effectively. Research limitations/implications Unsteady quasi-one-dimensional gas dynamic model can capture the flow field in the motor during ignition transient effectively. However, in systems where two- and three-dimensional effects are pre-dominant, one would require to develop a more elaborate, multi-dimensional model which will allow for further understanding of the flow behavior and eventually lead to modeling of rocket motors with more complex geometries. Practical implications The close agreement between experimental and simulation results can be considered as forced to some degree, because the general mathematical model of erosive burning contains a free variable erosive burning exponent. However, in future, this variable can be established a priori by erosive burning tests. Originality/value The solid propellant ignition process consists of series of rapid events and must be completed in a fraction of a second. An understanding of the dynamics of ignition has become increasingly vital with the development of larger and more sophisticated solid propellant rocket motors. This research effort provides the simulation framework to predict and evaluate the motor pressure during each phase by means of a numerical analysis, thus significantly increasing the efficiency of the preliminary design process with a reduction of both the motor development and operational costs.

Erosive burning in solid propellant motors

1991 ◽  
Author(s):  
J. GODON ◽  
J. DUTERQUE ◽  
G. LENGELLE
Keyword(s):  
Solid Propellant ◽  
Erosive Burning

An experimental investigation of the erosive burning characteristics of a nonhomogeneous solid propellant

AIAA Journal ◽  
1965 ◽  
Vol 3 (3) ◽  
pp. 523-525 ◽  
Author(s):  
M. J. ZUCROW ◽  
J. R. OSBORN ◽  
J. M. MURPHY
Keyword(s):  
Experimental Investigation ◽  
Solid Propellant ◽  
Erosive Burning
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