公开(公告)号：EP2881322A1

公开(公告)日：2015-06-10

申请号：EP14196292.8

申请日：2014-12-04

申请人： Tamarack Aerospace Group, Inc.

发明人： Guida, Nicholas R.

IPC分类号： B64C23/06

CPC分类号： B64C23/072 ,  B64C5/10 ,  B64C13/16 ,  B64C23/076 ,  Y02T50/164

摘要： An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.

摘要翻译： 一个可调节的升降机修剪翼尖可以连接到飞机的基准翼。 可调节升降机修剪翼尖可以包括水平部分，其包括控制表面和连接到水平部分的垂直部分。 垂直部分可以围绕可以基本上垂直于水平部分的轴线移动。 可以结合调整控制表面和垂直部分以在飞行状态下增加机翼效率。

公开(公告)号：EP2881323A1

公开(公告)日：2015-06-10

申请号：EP14196307.4

申请日：2014-12-04

申请人： Tamarack Aerospace Group, Inc.

发明人： Guida, Nicholas R.

IPC分类号： B64C23/06

CPC分类号： B64C23/069 ,  B64C2003/148 ,  Y02T50/12 ,  Y02T50/164

摘要： A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.

摘要翻译： 流动中断装置可以使流动与翼尖装置以期望的迎角分离。 流动中断装置可以联接到翼尖装置的前缘，其中流动破坏器可以被配置为减轻翼尖装置上的负载。 流动破坏器可以包括以阈值迎角延伸到边界层中的边缘，其可能破坏边界层并导致流动与翼尖装置分离。 这种分离的流动可以减少在遇到横向流动的各种飞行条件期间翼尖装置和机翼所经受的应力。

公开(公告)号：EP2881322B1

公开(公告)日：2017-06-14

申请号：EP14196292.8

申请日：2014-12-04

申请人： Tamarack Aerospace Group, Inc.

发明人： Guida, Nicholas R.

IPC分类号： B64C23/06

CPC分类号： B64C23/072 ,  B64C5/10 ,  B64C13/16 ,  B64C23/076 ,  Y02T50/164

摘要： An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.

摘要翻译： 可调升力改装翼尖可以连接到飞机的基准翼。 可调节升力修改翼尖可以包括水平部分，该水平部分包括控制表面和联接到水平部分的垂直部分。 垂直部分可围绕可基本垂直于水平部分的轴线移动。 控制表面和垂直部分可以在飞行条件下一起调整以增加机翼效率。

公开(公告)号：EP2881323B1

公开(公告)日：2016-10-19

申请号：EP14196307.4

申请日：2014-12-04

申请人： Tamarack Aerospace Group, Inc.

发明人： Guida, Nicholas R.

IPC分类号： B64C23/06

CPC分类号： B64C23/069 ,  B64C2003/148 ,  Y02T50/12 ,  Y02T50/164

摘要： A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.