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公开(公告)号：US20090108125A1
公开(公告)日：2009-04-30
申请号：US11927257
申请日：2007-10-29
CPC分类号： B64C21/04 , B64C9/38 , Y02T50/166
摘要： Coanda Effect and lift produced along a surface of an airfoil are increased by ducting compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling or other structure as an exhaust plume. One or more internal ducts extend from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance.
摘要翻译： 通过将压缩流体从发动机引导到翼型件的表面，沿着翼型件的表面产生的附壁效应和升力增加。 发动机产生主要通过整流罩或其他结构作为排气羽流朝向飞行器的后端的废气。 一个或多个内部管道从发动机延伸到翼面的表面，从而将压缩的流体从发动机传递到表面，以便抑制沿着表面的流动分离，从而使发动机排气流保持附着在表面上 更宽的跨度 这种结构和技术可以在设计用于利用上表面吹风（USB）技术和用于短起飞和着陆（STOL））性能的结构的飞机中发现。
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2.发明授权公开(公告)号：US07878458B2
公开(公告)日：2011-02-01
申请号：US11927290
申请日：2007-10-29
IPC分类号： B64C21/04
CPC分类号： B64C9/38 , B64C3/58 , B64C7/00 , B64C21/04 , B64C2230/04 , Y02T50/166
摘要： Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.
摘要翻译： 由飞机的翼型产生的升力通过抑制从翼型的表面的流体分离而增加。 发动机整流罩从翼型件的表面向外延伸，其具有用于将废气引导到飞行器后部的出口平面。 从表面向外延伸并且靠近发动机整流罩的出口平面的围栏被构造成沿着翼面表面的至少一部分引导废气，从而限制气体的翼展运动并增加气体所展示的附壁效应， 从而增加沿着翼面的表面产生的升力量。 这种技术可以用于短时起飞（STOL）飞机。
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公开(公告)号：US08087618B1
公开(公告)日：2012-01-03
申请号：US12500419
申请日：2009-07-09
IPC分类号： B64C3/50
CPC分类号： B64C9/38 , B64C21/04 , Y02T50/166
摘要： A propulsion system for an aircraft includes an airfoil, an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust, a propulsion flap carried by the airfoil and disposed aft of the engine cowling and a plurality of exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling.
摘要翻译： 用于飞机的推进系统包括翼型件，发动机，其具有由翼型件承载的发动机整流罩，并且构造成产生主要通过作为发动机排气的发动机整流罩指向翼型的后端的排气，由...引导的推进翼 所述翼型件和所述发动机整流罩的后部以及设置在所述推进翼片中的多个排气喷射孔，并且适于接收来自所述发动机整流罩的废气的至少一部分。
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公开(公告)号：US20090108141A1
公开(公告)日：2009-04-30
申请号：US11927290
申请日：2007-10-29
CPC分类号： B64C9/38 , B64C3/58 , B64C7/00 , B64C21/04 , B64C2230/04 , Y02T50/166
摘要： Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.
摘要翻译： 由飞机的翼型产生的升力通过抑制从翼型的表面的流体分离而增加。 发动机整流罩从翼型件的表面向外延伸，其具有用于将废气引导到飞行器后部的出口平面。 从表面向外延伸并且靠近发动机整流罩的出口平面的围栏被构造成沿着翼面表面的至少一部分引导废气，从而限制气体的翼展运动并增加气体所展示的附壁效应， 从而增加沿着翼面的表面产生的升力量。 这种技术可以用于短时起飞（STOL）飞机。
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公开(公告)号：US07823840B2
公开(公告)日：2010-11-02
申请号：US11927257
申请日：2007-10-29
IPC分类号： B64C3/50
CPC分类号： B64C21/04 , B64C9/38 , Y02T50/166
摘要： Coanda Effect and lift produced along a surface of an airfoil are increased by ducting compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling or other structure as an exhaust plume. One or more internal ducts extend from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance.
摘要翻译： 通过将压缩流体从发动机引导到翼型件的表面，沿着翼型件的表面产生的附壁效应和升力增加。 发动机产生主要通过整流罩或其他结构作为排气羽流朝向飞行器的后端的废气。 一个或多个内部管道从发动机延伸到翼面的表面，从而将压缩的流体从发动机传递到表面，以便抑制沿着表面的流动分离，从而使发动机排气流保持附着在表面上 更宽的跨度 这种结构和技术可以在设计用于利用上表面吹风（USB）技术和用于短起飞和着陆（STOL））性能的结构的飞机中发现。
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公开(公告)号：USD616804S1
公开(公告)日：2010-06-01
申请号：US29325636
申请日：2008-10-03
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公开(公告)号：US06843452B1
公开(公告)日：2005-01-18
申请号：US10463469
申请日：2003-06-17
CPC分类号： B64C3/50 , B64C3/58 , B64C9/00 , B64C39/12 , B64C2003/145 , Y02T50/12 , Y02T50/14 , Y02T50/32 , Y02T50/44
摘要： A mobile platform lift increasing system includes at least one wing-shaped structure having a leading edge, a trailing edge and a chord length perpendicularly measurable between the leading and trailing edges. A rotatable control surface is located near a trailing edge undersurface. The control surface length is approximately one to five percent of the chord length. A deployment device is positioned between the wing shaped structure and the control surface. The deployment device operably rotates the control surface through a plurality of positions ranging between an initial position and a fully deployed position. Wing lift is increased at speeds up to approximately transonic speed by continuously rotating the control surface to accommodate variables including mobile platform weight change from fuel usage.
摘要翻译： 移动平台提升系统包括至少一个翼形结构，其具有前缘，后缘和在前缘和后缘之间可垂直测量的弦长。 可旋转的控制表面位于后缘下表面附近。 控制面长度约为弦长的一至五。 展开装置位于翼形结构和控制表面之间。 展开装置可操作地使控制表面旋转穿过初始位置和完全展开位置之间的多个位置。 通过连续旋转控制表面来容纳变化，包括从燃料使用中移动平台重量变化，机翼升力以高达大约跨音速的速度增加。
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公开(公告)号：US06592072B1
公开(公告)日：2003-07-15
申请号：US10175623
申请日：2002-06-20
IPC分类号： B64C300
CPC分类号： B64C3/14 , B64C2003/147 , Y02T50/12
摘要： A method for forming a transonic wing that segregates a baseline transonic wing into a plurality of airfoil segments that are collectively modified an optimized so as to tailor a spanwise variation of the baseline transonic wing in a manner that includes the optimized airfoil segments. An improved wing is also provided.
摘要翻译： 一种用于形成跨音速翼的方法，其将基准跨音速翼分离成多个翼型段，其被共同修改为优化的，以便以包括优化的翼型段的方式定制基准跨音速翼的翼展方向变化。 还提供了改进的机翼。
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公开(公告)号：US4858852A
公开(公告)日：1989-08-22
申请号：US56250
申请日：1987-06-01
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/149 , Y02T50/12
摘要： A special contour near the trailing edge of an airfoil which improves the airfoil effectiveness. The contour is a combination of a blunt airfoil base, a local region of high surface curvature, typically on the airfoil lower surface, and upper surface and lower surface trailing edge slopes that diverge from each other.
摘要翻译： 在翼型的后缘附近有一个特殊的轮廓，提高了翼型的有效性。 轮廓是平头翼型基座，高表面曲率的局部区域，通常在翼型下表面上，以及彼此分开的上表面和下表面后缘的组合。
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