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1. 发明申请

US20030057332A1 Flap arrangement for varying the aerodynamic lift generated by an aerodynamic element of an aircraft 有权
标题翻译：用于改变由飞行器的空气动力学元件产生的空气动力升力的翼片装置
公开(公告)号：US20030057332A1
公开(公告)日：2003-03-27
申请号：US10255765
申请日：2002-09-25
发明人： Detlev Schwetzler , Peter May
IPC分类号： B64C013/16
CPC分类号： B64C9/18
摘要： An auxiliary flap is movably arranged on a planar trailing edge of an aerodynamic element such as a wing, rudder, stabilizer, or flap. The auxiliary flap is rotatable and/or slidable relative to the aerodynamic element, to move selectively into three positions. In a first position, a free edge of the auxiliary flap protrudes into an airflow boundary layer on one side of the aerodynamic element, to decrease lift. In a second position, a free edge of the aerodynamic element protrudes into an airflow boundary layer on the other side of the aerodynamic element, to increase lift. In a third neutral position, the auxiliary element does not protrude into either boundary layer, so as not to influence lift. The auxiliary flap is simple and rapidly acting. The flap protrudes substantially perpendicularly into the boundary layer flow. The auxiliary flap has a planar plate shape.
摘要翻译：辅助翼片可移动地布置在诸如翼，舵，稳定器或翼片的空气动力学元件的平面后缘上。辅助翼片可相对于空气动力学元件旋转和/或滑动，以选择性地移动到三个位置。在第一位置，辅助翼片的自由边缘突出到空气动力元件的一侧上的气流边界层中，以减小升力。在第二位置，空气动力元件的自由边缘突出到空气动力元件的另一侧上的气流边界层中，以增加升力。在第三中立位置，辅助元件不突出到任一边界层中，以便不影响升力。辅助翼片简单快速。翼片基本上垂直地突出到边界层流中。辅助翼片具有平板形状。

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