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    • 67. 发明申请
    • IGNITION DEVICE FOR TWO-PULSE ROCKET MOTOR WITH THERMAL BARRIER MEMBRANE
    • 带有热障膜的双脉冲电动机点火装置
    • US20130327016A1
    • 2013-12-12
    • US13911449
    • 2013-06-06
    • MITSUBISHI HEAVY INDUSTRIES, LTD.ASAHI KASEI CHEMICALS CORPORATION
    • Tomohiro KISHIDAYukihiro TSUNEZUMIChiyako MIHARATasuku SUZUKIKatsunori IEKI
    • F02K9/95
    • F02K9/95
    • 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.
    • 在设置有压力容器的双脉冲火箭发动机中,放置在压力容器内的第一推进剂在第一脉冲阶段期间燃烧,放置在压力容器内的第二推进剂在第一脉冲阶段之后的第二脉冲阶段期间燃烧, 以及覆盖所述第二推进剂的整个初始燃烧表面的隔离膜,其中所述阻隔膜设置有覆盖所述第二推进剂的内周面的内阻挡膜和覆盖所述第二推进剂的所述后表面的后挡板膜 的第二推进剂,并且后挡板膜和内阻挡膜相接的端部在其整个圆周上接合。 点火装置包括能量供应单元,一端连接到能量供应单元的能量传递单元和点火单元。