The ability to predict with some accuracy a given solid rocket motor’s performance before undertaking one or several costly experimental test firings is important. On the numerical prediction side, as various component models evolve, their incorporation into an overall internal ballistics simulation program allows for new motor firing simulations to take place, which in turn allows for updated comparisons to experimental firing data. In the present investigation, utilizing an updated simulation program, the focus is on quasi-steady performance analysis and scale effects (influence of motor size). The predicted effects of negative/positive erosive burning and propellant/casing deflection, as tied to motor size, on a reference cylindrical-gra...
Small-scale rocket motors are widely used by propulsion industries to carry out burn rate measuremen...
Solid Rocket Motors are propulsive systems providing thrust from products exiting through a nozzle,...
Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, lea...
Internal ballistics simulations of solid rocket motors have been conducted with the propellant grain...
In solid rocket motors, the absence of combustion controllability and the large amount of financial ...
Four erosive burning models, equations (11) to (14). are developed in this work by using a power law...
Traditionally, Solid Rocket Motor (SRM) internal ballistic performance has been analyzed and predict...
In solid propellant rocket motor internal ballistic calculation, next coefficients, performance para...
The Monte Carlo method was used to investigate thrust imbalance and its first time derivative throug...
To acquire the erosive characteristics of two-channel combustion chambers, a quasi-one-dimensional i...
The ability to accurately model the operation of a solid rocket motor before undergoing multiple fir...
Erosive burning changes the burning rate of solid rocket propellants which can normally be approxima...
Two different independent variable forms, a difference form and a ratio form, were investigated for ...
Small-scale solid rocket motors have been extremely successful among propulsion industries in the la...
A modular computer program named SPPMEF has been developed which isintended for purposes of predicti...
Small-scale rocket motors are widely used by propulsion industries to carry out burn rate measuremen...
Solid Rocket Motors are propulsive systems providing thrust from products exiting through a nozzle,...
Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, lea...
Internal ballistics simulations of solid rocket motors have been conducted with the propellant grain...
In solid rocket motors, the absence of combustion controllability and the large amount of financial ...
Four erosive burning models, equations (11) to (14). are developed in this work by using a power law...
Traditionally, Solid Rocket Motor (SRM) internal ballistic performance has been analyzed and predict...
In solid propellant rocket motor internal ballistic calculation, next coefficients, performance para...
The Monte Carlo method was used to investigate thrust imbalance and its first time derivative throug...
To acquire the erosive characteristics of two-channel combustion chambers, a quasi-one-dimensional i...
The ability to accurately model the operation of a solid rocket motor before undergoing multiple fir...
Erosive burning changes the burning rate of solid rocket propellants which can normally be approxima...
Two different independent variable forms, a difference form and a ratio form, were investigated for ...
Small-scale solid rocket motors have been extremely successful among propulsion industries in the la...
A modular computer program named SPPMEF has been developed which isintended for purposes of predicti...
Small-scale rocket motors are widely used by propulsion industries to carry out burn rate measuremen...
Solid Rocket Motors are propulsive systems providing thrust from products exiting through a nozzle,...
Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, lea...