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 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.

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 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 Mechanisms and applications of vibration energy harvesting in solid rocket motors

2021 ◽  
Author(s):  
Chirag Goel ◽  
G. Srinivas
Keyword(s):  
Energy Harvesting ◽  
Fossil Fuels ◽  
Piezoelectric Materials ◽  
Rocket Motor ◽  
Structural Vibration ◽  
Space Vehicles ◽  
Solid Rocket Motor ◽  
Vibration Energy Harvesting ◽  
Vibration Data ◽  
Solid Rocket

AbstractEnergy harvesting has become a fascinating topic of research. As the world moves towards reducing its dependency on fossil fuels, new and innovative techniques of energy harvesting have been tested and developed. The use of piezoelectric materials to harvest the ambient vibrations from the surroundings is one method that has seen a dramatic rise in use for power harvesting. Remote sensors can be powered by these piezoelectric materials and could potentially act as a continuous source of energy. In space vehicles, energy is generated using solar panels which are bulky, heavy and expensive. Instead piezoelectric harvesters can be used to generate power and are much lighter, compact and relatively cheap when produced in bulk. This paper presents a theoretical study on energy harvesting from structural vibration caused by combustion instability of a solid rocket motor through the motor burnout. Vibration data of tested solid rocket motor was taken as a reference and was inputted as the boundary condition. The 3-D model of the harvester system was designed on Fusion360 and the simulation was performed on COMSOL. Finally, improvements needed in the system to enhance practicality were discussed.

scholarly journals Numerical Evaluation of the Use of Aluminum Particles for Enhancing Solid Rocket Motor Combustion Stability

2021 ◽  
Author(s):  
David Greatrix
Keyword(s):  
Pressure Wave ◽  
Internal Flow ◽  
Rocket Motor ◽  
Combustion Stability ◽  
Transient Pressure ◽  
Solid Rocket Motor ◽  
Aluminum Particles ◽  
Internal Ballistic ◽  
Reactive Particles ◽  
Solid Rocket

The ability to predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms typically necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. On the mitigation side, one in practice sees the use of inert or reactive particles for the suppression of pressure wave development in the motor chamber flow. With the focus of the present study placed on reactive particles, a numerical internal ballistic model incorporating relevant elements, such as a transient, frequency-dependent combustion response to axial pressure wave activity above the burning propellant surface, is applied to the investigation of using aluminum particles within the central internal flow (particles whose surfaces nominally regress with time, as a function of current particle size, as they move downstream) as a means of suppressing instability-related symptoms in a cylindrical-grain motor. The results of this investigation reveal that the loading percentage and starting size of the aluminum particles have a significant influence on reducing the resulting transient pressure wave magnitude.

scholarly journals Numerical Evaluation of the Use of Aluminum Particles for Enhancing Solid Rocket Motor Combustion Stability

2021 ◽  
Author(s):  
David Greatrix
Keyword(s):  
Pressure Wave ◽  
Internal Flow ◽  
Rocket Motor ◽  
Combustion Stability ◽  
Transient Pressure ◽  
Solid Rocket Motor ◽  
Aluminum Particles ◽  
Internal Ballistic ◽  
Reactive Particles ◽  
Solid Rocket

The ability to predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms typically necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. On the mitigation side, one in practice sees the use of inert or reactive particles for the suppression of pressure wave development in the motor chamber flow. With the focus of the present study placed on reactive particles, a numerical internal ballistic model incorporating relevant elements, such as a transient, frequency-dependent combustion response to axial pressure wave activity above the burning propellant surface, is applied to the investigation of using aluminum particles within the central internal flow (particles whose surfaces nominally regress with time, as a function of current particle size, as they move downstream) as a means of suppressing instability-related symptoms in a cylindrical-grain motor. The results of this investigation reveal that the loading percentage and starting size of the aluminum particles have a significant influence on reducing the resulting transient pressure wave magnitude.

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