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    • 6. 发明授权
    • Laser ignition for liquid propellant rocket engine injectors
    • 液体推进剂火箭发动机喷油器的激光点火
    • US09347399B1
    • 2016-05-24
    • US08988059
    • 1997-12-10
    • William S. BrownGlenn T. Bennett
    • William S. BrownGlenn T. Bennett
    • F02K9/00F02K9/95
    • F02K9/00F02K9/95
    • A laser beam is utilized to ignite the fuel and oxidizer injected into a combustion chamber. An injector has a plurality of injector elements each injecting fuel and oxidizer into a flame holding zone adjacent the injector face plate where fuel and oxidizer are mixing at a rate to sustain flammability. The laser beam is introduced parallel to the injector face plate passing through the fuel and oxidizer mixing zones igniting the propellants. The propellants are ignited by having a laser beam tuned to a frequency to excite the oxidizer such that it will chemically combine with the fuel to form an ignition kernel in the flame holding zone. When a plurality of injector elements are ignited in this manner a controlled ignition process in the combustion chamber is achieved.
    • 激光束用于点燃注入燃烧室的燃料和氧化剂。 喷射器具有多个喷射器元件,每个喷射器元件将燃料和氧化剂喷射到与喷射器面板相邻的火焰保持区域中,其中燃料和氧化剂以可燃性的速率混合。 激光束平行于通过燃料的注射器面板引入,并且点燃推进剂的氧化剂混合区域。 通过将激光束调谐到频率以激发氧化剂来点燃推进剂,使得其与燃料化学结合以在火焰保持区域中形成点火核。 当以这种方式点燃多个喷射器元件时,实现了燃烧室中的受控点火过程。
    • 7. 发明授权
    • Solid propellant rocket motors employing tungsten alloy burst discs and methods for the manufacture thereof
    • 使用钨合金爆破片的固体推进剂火箭发动机及其制造方法
    • US08713912B2
    • 2014-05-06
    • US12834289
    • 2010-07-12
    • James H. DupontSean J. Whitmarsh
    • James H. DupontSean J. Whitmarsh
    • F02G1/00F02K9/00F16K17/14
    • F02K9/32F02K9/978F05D2230/22F05D2300/13Y10T29/49346Y10T137/1647
    • Embodiments of a solid propellant rocket motor are provided. In one embodiment, the solid propellant rocket motor includes a pressure vessel having a cavity therein, a solid propellant disposed within the cavity, a nozzle fluidly coupled to the cavity, and a tungsten alloy burst disc positioned proximate the nozzle. The tungsten alloy burst disc is configured to block gas flow through the nozzle when the tungsten alloy burst disc is intact and to fragment at a predetermined burst pressure. Embodiments of a method are further provided for manufacturing a burst disc. In one embodiment, the method comprises the step of forming a burst disc from a tungsten alloy. Embodiments of a burst disc are still further provided. In one embodiment, the burst disc includes an outer annular portion, and a central portion comprising a tungsten alloy.
    • 提供固体推进剂火箭发动机的实施例。 在一个实施例中,固体推进剂火箭发动机包括其中具有空腔的压力容器,设置在空腔内的固体推进剂,与腔体流体耦合的喷嘴以及位于喷嘴附近的钨合金爆裂盘。 当钨合金爆破盘完好并且以预定的爆破压力分裂时,钨合金爆裂盘被构造成阻挡通过喷嘴的气体流动。 还提供了用于制造突发盘的方法的实施例。 在一个实施例中,该方法包括从钨合金形成爆破盘的步骤。 还提供了突发盘的实施例。 在一个实施例中,爆破盘包括外部环形部分和包括钨合金的中心部分。