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    • 5. 发明申请
    • HYBRID-CYCLE LIQUID PROPELLANT ROCKET ENGINE
    • 混合循环液体推进剂发动机
    • WO2014144369A1
    • 2014-09-18
    • PCT/US2014/028748
    • 2014-03-14
    • ORBITAL SCIENCES CORPORATIONELIAS, Antonio, L.
    • ELIAS, Antonio, L.
    • F02K9/48
    • F02K9/42F02K9/48
    • Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.
    • 本文描述了用于混合液体推进剂火箭发动机的系统和方法。 在一个实施例中,发动机包括由第一涡轮机驱动的第一泵,由第二涡轮机供电的第二泵和气体发生器。 气体发生器的输出端连接到第一涡轮机和第二涡轮机。 发动机还包括由第三涡轮机驱动的第三泵,由第四涡轮机供电的第四泵和在壁和燃烧室中具有膨胀器循环的喷嘴。 第三泵的输出连接到膨胀机循环,并且壁的输出连接到第三涡轮机和第四涡轮机。 第四泵的输出,第三涡轮的输出和第四涡轮的输出连接到燃烧室。