Abstract
In the design of a propelling charge with single perforated stick propellants, it is necessary to determine a limit value of the filling coefficient in order to clarify wherether the designed propelling charge can be filled into a combustion chamber or not. This paper presents a method for determining a priority number of stick propellants and the limit value of the filling coefficient. These parameters are the bases for designing solid rocket motor, especially, in the case of anti-tank solid rocket motors, where the number of the stick propellants are up to hundreds.
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