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    • 5. 发明申请
    • SUPERSONIC AIRCRAFT JET ENGINE
    • 超音速飞机喷气发动机
    • WO2008105847A2
    • 2008-09-04
    • PCT/US2007/021624
    • 2007-10-10
    • AERION CORPORATION
    • CHASE, James, D.GARZON, German, Andres
    • B64C30/00
    • B64C30/00B64D27/20B64D29/04B64D33/02B64D2033/026Y02T50/44
    • Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following X 0 ) a region just ahead of the lip X 1 ) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.
    • 超音速飞行器的喷气发动机进气口结构包括具有入口斜坡和与斜坡向外隔开的发动机罩唇缘的结构,使得进入的空气在斜坡和凸缘之间流动,所述唇缘和斜坡被配置为产生 从斜坡的前部向外延伸以通过唇部的第一倾斜冲击和从斜坡的后部向外延伸到下列X 0之一的终端冲击) 一个恰好在唇部X 1前面的区域)基本上与所述唇缘相连。 产生不均匀的冲击系统,其产生接近等熵压缩和相对冲击回收的中心区域,并且减小冲压回收的外部区域,但导致减小的整流罩角度和阻力。 还提供翻译罩结构和喷嘴与机身轮廓一体化以减少船尾拖曳的功能。