Supersonic aircraft with active lift distribution control for reducing sonic boom
    2.
    发明申请
    Supersonic aircraft with active lift distribution control for reducing sonic boom 审中-公开
    超音速飞机具有主动升力分配控制,用于减少声波

    公开(公告)号:US20060157613A1

    公开(公告)日:2006-07-20

    申请号:US11039651

    申请日:2005-01-19

    CPC classification number: B64C3/50 B64C30/00

    Abstract: Methods and systems for actively reducing sonic boom in commercial supersonic aircraft and other supersonic aircraft are described herein. A method for operating an aircraft in accordance with one aspect of the invention includes configuring at least one lift control device to produce a first streamwise lift distribution, and flying the aircraft at a subsonic speed while the lift control device is configured to produce the first streamwise lift distribution. The method can further include configuring the lift control device to produce a second streamwise lift distribution, and flying the aircraft at a supersonic speed while the lift control device is configured to produce the second streamwise lift distribution. The first streamwise lift distribution produces an N-shaped ground pressure signature and a corresponding first sonic boom at the supersonic speed. The second streamwise lift distribution, however, produces a “shaped” ground pressure signature and a corresponding second sonic boom that is less than the first sonic boom at the supersonic speed.

    Abstract translation: 本文描述了用于在商业超音速飞机和其他超音速飞行器中主动减少声波的方法和系统。 根据本发明的一个方面的用于操作飞行器的方法包括:配置至少一个升降控制装置以产生第一流式升降分配,并且以亚音速飞行飞行器,而升降控制装置被配置成产生第一流式 电梯分配。 该方法还可以包括配置升降控制装置以产生第二流式升降分配,并且在升降控制装置构造成产生第二流式升降分配时以超音速飞行飞行器。 第一个流动升力分配产生N形地面压力特征和超音速对应的第一个声波起重臂。 然而,第二个流动升力分配产生一个“形状的”地面压力特征和相应的第二个声波起重臂,它在超音速下小于第一个声音起重臂。

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