Ignition device for two-pulse rocket motor with thermal barrier membrane
In a two-pulse rocket motor provided with a pressure vessel, a first propellant placed within the pressure vessel that burns during a first pulse stage, a second propellant placed within the pressure vessel that burns during a second pulse stage following the first pulse stage, and a barrier membrane placed so as to cover the entire initial burning surface of the second propellant, wherein the barrier membrane is provided with an inner barrier membrane that covers the inner peripheral surface of the second propellant and an aft barrier membrane that covers the 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. The ignition device includes an energy supply unit, an energy transfer unit connected at one end to the energy supply unit, and an ignition unit.
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.
2. The ignition device for a two-pulse rocket motor according to claim 1 , wherein the main charge is a boron potassium nitrate based pelletized explosive.
3. The ignition device for a two-pulse rocket motor according to claim 2 , wherein the energy transfer unit is an optical fiber, shock tube detonator or lead tube.
4. The ignition device for a two-pulse rocket motor according to claim 2 , wherein the energy supply unit is an optical energy generating device that includes a laser diode or a pyrotechnic energy generation device that includes an initiator.
5. The ignition device for a two-pulse rocket motor according to claim 1 , wherein the booster charge is black powder or boron potassium nitrate based powdered explosive contained in a case.
6. The ignition device for a two-pulse rocket motor according to claim 5 , wherein the energy transfer unit is an optical fiber, shock tube detonator or lead tube.
7. The ignition device for a two-pulse rocket motor according to claim 5 , wherein the energy supply unit is an optical energy generating device that includes a laser diode or a pyrotechnic energy generation device that includes an initiator.
8. The ignition device for a two-pulse rocket motor according to claim 1 , wherein the sheet-like molded material is a flexible, non-scattering and completely burnable material such as a cured polymer that includes hydroxyl-terminated polybutadiene (HTPB), sponge or adhesive.
9. The ignition device for a two-pulse rocket motor according to claim 8 , wherein the energy transfer unit is an optical fiber, shock tube detonator or lead tube.
10. The ignition device for a two-pulse rocket motor according to claim 8 , wherein the energy supply unit is an optical energy generating device that includes a laser diode or a pyrotechnic energy generation device that includes an initiator.
11. The ignition device for a two-pulse rocket motor according to claim 1 , wherein the energy transfer unit is an optical fiber, shock tube detonator or lead tube.
12. The ignition device for a two-pulse rocket motor according to claim 1 , wherein the energy supply unit is an optical energy generating device that includes a laser diode or a pyrotechnic energy generation device that includes an initiator.