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1. 发明授权

US6152404A Apparatus for influencing a wing root airflow in an aircraft 失效
标题翻译：影响飞机机翼根部气流的装置
公开(公告)号：US6152404A
公开(公告)日：2000-11-28
申请号：US78292
申请日：1998-05-13
申请人： Axel Flaig , Detlev Schwetzler , Ulrich Stache, deceased
发明人： Axel Flaig , Detlev Schwetzler , Ulrich Stache, deceased
IPC分类号： B64C9/24 , B64C21/00 , B64C23/06
CPC分类号： B64C23/06 , B64C9/24 , Y02T50/162 , Y02T50/44
摘要： An apparatus advantageously influences the wing root airflow along the wing root of an aircraft having a high lift system including leading edge slats provided on the main wings. The apparatus includes a respective vortex generator arranged on the inboard end of each leading edge slat in the area of the wing root, and further includes a respective transition fairing arranged on a separation edge that is let into the leading edge of the wing root and that borders along the inboard edge of the respective slat. The vortex generator is a rigid member fixed to the leading edge slat and may be in the shape of a horn, a disk, or a winglet. The transition fairing may be a rigid member fixed to the wing root along the separation edge, or may be a flexible elastic member that can be inflated to have a variable outer contour. The present system avoids the need of additional independently movable auxiliary flaps, and thus achieves a reduced weight, complexity, and maintenance requirement.
摘要翻译：装置有利地影响沿着具有高提升系统的飞机的翼根的翼根气流，包括设置在主翼上的前缘板条。该装置包括设置在翼根区域中每个前缘板条的内侧端部的相应的涡流发生器，并且还包括布置在分离边缘上的相应的过渡整流装置，该分离边缘进入翼根的前缘，并且其中，沿着相应板条的内侧边缘边界。涡流发生器是固定到前缘板条的刚性构件，并且可以是喇叭，盘或小翼的形状。过渡整流罩可以是沿着分离边缘固定到翼根的刚性构件，或者可以是可膨胀以具有可变外轮廓的柔性弹性构件。本系统避免了额外的独立移动的辅助翼片的需要，从而实现了减轻的重量，复杂性和维护要求。

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