Patent ID: 9371801
Filing Date: 2016-06-21
CPC Classification: F02K

Claim Text:
1. An ignition device in a two-pulse rocket motor, wherein the two-pulse rocket motor comprises: a pressure vessel, a first propellant that is placed within the pressure vessel and burns during a first pulse stage, a second propellant that is placed within the pressure vessel and burns during a second pulse stage following the first pulse stage, and a barrier membrane placed so as to cover an entire initial burning surface of the second propellant, wherein the barrier membrane is provided with an inner barrier membrane that covers an inner peripheral surface of the second propellant and an aft barrier membrane that covers a rear surface of the second propellant, and an end portion where the aft barrier membrane and the inner barrier membrane meet is joined over the entire circumference thereof; said ignition device comprising: an energy supply unit, an energy transfer unit connected at one end to the energy supply unit, and an ignition unit connected to other end of the energy transfer unit, wherein the ignition unit is fixed to the aft barrier membrane, and the second propellant is ignited and the barrier membrane is ruptured by operation of the energy supply unit, the energy transfer unit and the ignition unit, and wherein the ignition unit is provided with: a booster charge connected to the energy transfer unit, a main charge placed around the periphery of the booster charge, and a sheet-like molded material that fixes the booster charge and the main charge to the aft barrier membrane.