Inert Particles for Axial-Combustion-Instability Suppression in a Solid Rocket Motor

2008 ◽  
Vol 24 (6) ◽  
pp. 1347-1354 ◽  
Author(s):  
David R. Greatrix
Keyword(s):  
Combustion Instability ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Inert Particles ◽  
Solid Rocket

Mache Effect and Combustion Instability in Solid Rocket Motor

1999 ◽  
Vol 15 (6) ◽  
pp. 856-860 ◽  
Author(s):  
Igor G. Assovskiy ◽  
Sergei A. Rashkovskiy
Keyword(s):  
Combustion Instability ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket

scholarly journals Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor

2021 ◽  
Author(s):  
Christopher Baczynski
Keyword(s):  
Pressure Wave ◽  
Combustion Instability ◽  
Combustion Process ◽  
Rocket Motor ◽  
Structural Vibration ◽  
Solid Rocket Motor ◽  
Aspect Ratios ◽  
Port Area ◽  
Solid Rocket ◽  
The Given

A comprehensive numerical model for internal ballistic simulation under dynamic flow, combustion and structural vibration conditions is used to investigate the effectiveness of grain port area transitions of a reference solid rocket motor as a means for suppression of axial combustion instability symptoms. Modification of the propellant grain geometry is one of several traditional means for suppressing symptoms in actual motors. With respect to these symptoms, individual transient simulation runs show the evolution of the axial pressure wave and associated DC shift for the given grain geometry, as initiated by a given pressure disturbance. Limit pressure wave magnitudes are collected for a number of simulation runs for different grain area transition positions, steepness and aspect ratios, and mapped on an attenuation trend chart. Effects of acceleration, through structural vibration of the propellant surface, on the combustion process are investigated, and their influence on the effectiveness of grain area transitions is examined. With or without acceleration/vibrations effects included, the numerical results produced in this study confirm the significant ability of a grain area transition to suppress combustion instability symptoms.

scholarly journals Fluid-structure interaction considerations for solid rocket motor internal ballistics modeling

2021 ◽  
Author(s):  
Giovanni Montesano
Keyword(s):  
Burning Rate ◽  
Combustion Instability ◽  
Three Dimensional ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Fluid Structure ◽  
Dimensional Finite Element ◽  
Solid Rocket ◽  
Model Components ◽  
Three Dimensional Finite Element

A study of the numerical modeling and prediction of nonlinear unsteady combustion instability within the combustion chamber of a solid rocket motor (SRM) is the main objective. The numerical model consists of a three-dimensional finite-element representation of a cylindrical-grain motor, coupled to a quasi-one-dimensional internal ballistic flow (IBF) model, where a quasi-steady rapid kinetic rate burning rate algorithm is used to model the propellant combustion and regression. Fluid-structure-combustion interaction subroutines are also employed to control the simulated motor firings and the data transferred between the fluid, structure and burning rate model components. Results illustrating the significant effects of structural vibrations on the burning rate and consequently the IBF are shown and compared to experimental data. Modeling considerations are illustrated, giving insight into the physical phenomena of SRM combustion instability.

scholarly journals Effects Of Grain Geometry And Vibration On The Suppression Of Combustion Instability In A Solid Rocket Motor

2021 ◽  
Author(s):  
Christopher Baczynski
Keyword(s):  
Pressure Wave ◽  
Combustion Instability ◽  
Combustion Process ◽  
Rocket Motor ◽  
Structural Vibration ◽  
Solid Rocket Motor ◽  
Aspect Ratios ◽  
Port Area ◽  
Solid Rocket ◽  
The Given

A comprehensive numerical model for internal ballistic simulation under dynamic flow, combustion and structural vibration conditions is used to investigate the effectiveness of grain port area transitions of a reference solid rocket motor as a means for suppression of axial combustion instability symptoms. Modification of the propellant grain geometry is one of several traditional means for suppressing symptoms in actual motors. With respect to these symptoms, individual transient simulation runs show the evolution of the axial pressure wave and associated DC shift for the given grain geometry, as initiated by a given pressure disturbance. Limit pressure wave magnitudes are collected for a number of simulation runs for different grain area transition positions, steepness and aspect ratios, and mapped on an attenuation trend chart. Effects of acceleration, through structural vibration of the propellant surface, on the combustion process are investigated, and their influence on the effectiveness of grain area transitions is examined. With or without acceleration/vibrations effects included, the numerical results produced in this study confirm the significant ability of a grain area transition to suppress combustion instability symptoms.

scholarly journals Fluid-structure interaction considerations for solid rocket motor internal ballistics modeling

2021 ◽  
Author(s):  
Giovanni Montesano
Keyword(s):  
Burning Rate ◽  
Combustion Instability ◽  
Three Dimensional ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Fluid Structure ◽  
Dimensional Finite Element ◽  
Solid Rocket ◽  
Model Components ◽  
Three Dimensional Finite Element

A study of the numerical modeling and prediction of nonlinear unsteady combustion instability within the combustion chamber of a solid rocket motor (SRM) is the main objective. The numerical model consists of a three-dimensional finite-element representation of a cylindrical-grain motor, coupled to a quasi-one-dimensional internal ballistic flow (IBF) model, where a quasi-steady rapid kinetic rate burning rate algorithm is used to model the propellant combustion and regression. Fluid-structure-combustion interaction subroutines are also employed to control the simulated motor firings and the data transferred between the fluid, structure and burning rate model components. Results illustrating the significant effects of structural vibrations on the burning rate and consequently the IBF are shown and compared to experimental data. Modeling considerations are illustrated, giving insight into the physical phenomena of SRM combustion instability.

Effects of time-varying grain shape on combustion instability of a solid rocket motor

2015 ◽  
Vol 138 (3) ◽  
pp. 1892-1892
Author(s):  
Taeyoung Park ◽  
Hunki Lee ◽  
Won-Suk Ohm ◽  
Dohyung Lee
Keyword(s):  
Grain Shape ◽  
Combustion Instability ◽  
Rocket Motor ◽  
Time Varying ◽  
Solid Rocket Motor ◽  
Solid Rocket

Computational Fluid Dynamics Simulation of Combustion Instability in Solid Rocket Motor : Implementation of Pressure Coupled Response Function

2016 ◽  
Vol 66 (3) ◽  
pp. 216 ◽  
Author(s):  
S. Saha ◽  
D. Chakraborty
Keyword(s):  
Fluid Dynamics ◽  
Growth Rate ◽  
Computational Fluid Dynamics ◽  
Response Function ◽  
Combustion Instability ◽  
Rocket Motor ◽  
Dynamics Simulation ◽  
Solid Rocket Motor ◽  
Pressure Oscillations ◽  
Solid Rocket

<p class="NomenclatureClauseTitle">Combustion instability in solid propellant rocket motor is numerically simulated by implementing propellant response function with quasi steady homogeneous one dimensional formulation. The convolution integral of propellant response with pressure history is implemented through a user defined function in commercial computational fluid dynamics software. The methodology is validated against literature reported motor test and other simulation results. Computed amplitude of pressure fluctuations compare closely with the literarture data. The growth rate of pressure oscillations of a cylindrical grain solid rocket motor is determined for different response functions at the fundamental longitudinal frequency. It is observed that for response function more than a critical value, the motor exhibits exponential growth rate of pressure oscillations.</p>

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