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1. 发明申请

US20120205490A1 AIRCRAFT HORIZONTAL STABILISER FITTED WITH LEADING-EDGE STRAKE 审中-公开
标题翻译：飞机水平稳定器配有前沿边缘
公开(公告)号：US20120205490A1
公开(公告)日：2012-08-16
申请号：US13502175
申请日：2010-10-18
申请人： Ian Roy Whitehouse , Carsten Weber , Markus Fischer , Alain Tanguy
发明人： Ian Roy Whitehouse , Carsten Weber , Markus Fischer , Alain Tanguy
IPC分类号： B64C5/02 , B64C5/06
CPC分类号： B64C5/02 , B64C23/06 , Y02T50/162
摘要： An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.
摘要翻译：一种用于飞行器的可调节或全移动的水平稳定器，所述稳定器具有前缘，后缘，根部和尖端以及相对于所述稳定器固定或与所述稳定器一体形成的支架稳定器前缘毗邻根部。

2. 发明授权

US10543899B2 Aircraft horizontal stabiliser fitted with leading-edge strake 有权
公开(公告)号：US10543899B2
公开(公告)日：2020-01-28
申请号：US13502175
申请日：2010-10-18
申请人： Ian Roy Whitehouse , Carsten Weber , Markus Fischer , Alain Tanguy
发明人： Ian Roy Whitehouse , Carsten Weber , Markus Fischer , Alain Tanguy
IPC分类号： B64C5/02
摘要： An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.

3. 发明授权

US08128038B2 High-lift device for an aircraft 有权
标题翻译：用于飞机的高升降装置
公开(公告)号：US08128038B2
公开(公告)日：2012-03-06
申请号：US11568969
申请日：2005-05-09
申请人： Ian Roy Whitehouse , Edmund Kay , Daniel Dodd
发明人： Ian Roy Whitehouse , Edmund Kay , Daniel Dodd
IPC分类号： B64C3/50
CPC分类号： B64C9/24 , B64C23/06 , Y02T50/162 , Y02T50/32 , Y02T50/44
摘要： An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when the high-lift device is in the deployed position, air may flow through an opening (7) in the wing (2) and over the aerofoil surface. During flight, air preferably flows into the boundary layer (13) on the upper surface of the wing (2). This energises the boundary layer (13), aft of the trailing edge of the drooped leading edge flap increasing its stability allowing the maximum achievable lift coefficient to be increased and hence reducing aircraft take-off and approach speeds.
摘要翻译：飞行器包括限定翼面的翼（2），所述翼（2）包括可在收起位置和展开位置之间移动的下垂的前缘翼片（1）。机翼（2）被布置成使得在高升力装置处于展开位置时的飞行中，空气可以流过机翼（2）中的开口（7）并且在机翼表面上方流动。在飞行中，空气最好流入机翼（2）上表面上的边界层（13）。这使能边界层（13），下垂的前缘翼片的后缘的后部增加了其稳定性，从而可以增加最大可实现的升力系数，从而减少飞机起飞和进近速度。

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