초록 ▼

A propellant system for launching a large-caliber projectile includes a propellant having at least three partial charges. The first partial charge is adapted to acceleration requirements of the projectile; the second partial charge has a higher combustion velocity than that of the first partial char

A propellant system for launching a large-caliber projectile includes a propellant having at least three partial charges. The first partial charge is adapted to acceleration requirements of the projectile; the second partial charge has a higher combustion velocity than that of the first partial charge; and the third partial charge has a lower combustion velocity than that of the first partial charge. The propellant system further includes an electric energy supply and control device connected to the propellant for igniting the propellant. The electric energy supply and control device has a plasma generator for affecting a combustion behavior of the propellant such as to obtain for said first partial charge, after ignition of the propellant, a maximum gas pressure level of always the same magnitude independently from an initial propellant temperature, and to obtain, for the third partial charge, a conversion such as to prolong the maximum gas pressure level in a predeterminable manner.

대표청구항 ▼

1. A propellant system for launching a large-caliber projectile, comprising(a) a propellant including (1) a first partial charge adapted to acceleration requirements of the projectile; (2) a second partial charge having a higher combustion velocity than that of said first partial charge; and (3) a t

1. A propellant system for launching a large-caliber projectile, comprising(a) a propellant including (1) a first partial charge adapted to acceleration requirements of the projectile; (2) a second partial charge having a higher combustion velocity than that of said first partial charge; and (3) a third partial charge having a lower combustion velocity than that of said first partial charge; and (b) an electric energy supply and control device connected to said propellant for igniting said propellant; said electric energy supply and control device including plasma generating means for affecting a combustion behavior of said propellant for obtaining for said first partial charge, after ignition of said propellant, a maximum gas pressure level of always the same magnitude independently from an initial propellant temperature, and for obtaining, for said third partial charge, a conversion such as to prolong the maximum gas pressure level in a predeterminable manner.