Patent ID: 7918163

Claim:
Method of combustion for tubular propellant charges with a very high charge density and high progressivity for barrel weapons, the method comprising: radially perforating at least two propellant tubes which have circular outer and inner boundary surfaces in their entirety with combustion or ignition channels at an e-dimension distance selected in relation to the actual type of propellant and the desired combustion characteristics of said propellant tubes, treating at least one of the total number of outer surfaces of these propellant tubes that are available for initiation with an inhibition, surface treatment or surface coating, delaying the propagation of ignition of said all outer surfaces of at least one propellant tube, so that ignition of the propellant tubes is successively done one after the other and combustion of a propellant tube is partially mutually overlapping the combustion of the next propellant tube such that the maximum pressure within the barrel weapon resulting from each combustion is equal to or slightly below a maximum operational pressure of the barrel weapon, and selecting a first propellant tube from among the at least two propellant tubes with a different e-dimension distance in relation to the e-dimension distance of a second propellant tube from among the at least two propellant tubes.