SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2003 - IPC

FIELD: rocket engines. SUBSTANCE: proposed solid-propellant rocket engine includes layers of propellant arranged crosswise relative to axis of charge and is furnished with initiation system providing detonation of propellant layers in turn. Layers of propellant featuring high detonation capacity whose thickness is considerably greater than critical detonation thickness are internal with other layers of propellant featuring low detonation capacity whose thickness is considerably less than critical detonation thickness being, however, sufficient to prevent transmission of detonation from previous layer featuring high detonation capacity to following layer of high detonation capacity. Layers of propellant of high detonation capacity and layers of propellant of low detonation capacity are braced to each other. Initial system provides detonation of propellant layers in turn at preset constant or variable frequency. EFFECT: creation of rocket engine featuring high specific thrust pulse with possibility of thrust changing within range. 1 dwg