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1. 发明申请

US20110180146A1 MICROVANES FOR AIRCRAFT AFT BODY DRAG REDUCTION 有权
标题翻译：飞机机身减速机的微型飞机
公开(公告)号：US20110180146A1
公开(公告)日：2011-07-28
申请号：US12406819
申请日：2009-03-18
申请人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
发明人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
IPC分类号： B64C1/38
CPC分类号： B64C23/06 , B64C1/0009 , B64C2230/26 , F15D1/0035 , Y02T50/12 , Y02T50/162 , Y02T50/166 , Y10T137/0318
摘要： The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.
摘要翻译：本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度，减阻元件被定位。

2. 发明授权

US08226038B2 Microvanes for aircraft aft body drag reduction 有权
标题翻译：飞机尾灯微型车身减阻
公开(公告)号：US08226038B2
公开(公告)日：2012-07-24
申请号：US12406819
申请日：2009-03-18
申请人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
发明人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
IPC分类号： B64C1/38
CPC分类号： B64C23/06 , B64C1/0009 , B64C2230/26 , F15D1/0035 , Y02T50/12 , Y02T50/162 , Y02T50/166 , Y10T137/0318
摘要： The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.
摘要翻译：本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度，减阻元件被定位。

3. 发明授权

US06368059B1 Controlled passive porosity systems to mitigate cavitation 失效
标题翻译：控制的被动孔隙系统以减轻气蚀
公开(公告)号：US06368059B1
公开(公告)日：2002-04-09
申请号：US09627636
申请日：2000-07-28
申请人： Brant H. Maines
发明人： Brant H. Maines
IPC分类号： B64C1130
CPC分类号： B63H1/15 , B63H1/26 , B63H1/28 , B64C11/18 , B64C21/025 , B64C2230/06 , B64C2230/14 , B64C2230/20 , B64C2230/22 , B64C2230/28 , Y02T50/166 , Y10S415/914
摘要： A controlled passive porosity system includes a lifting device for operation in a multi-phase liquid, the lifting device having a low pressure surface with a plurality of holes and a high pressure surface with a plurality of holes. A common plenum is disposed within the lifting device and allows fluid communication between liquid adjacent the high pressure surface and liquid adjacent the low pressure surface. When cavitation occurs adjacent to the low pressure surface, a series of valves associated with the holes allows selective and localized fluid communication between the surfaces. The fluid communication has the effect of raising the pressure of the liquid in the area of cavitation, thereby eliminating the cavitation. In an alternate embodiment, the lifting device includes a first plenum, a second plenum, and an intermediate fluid passage, the fluid passage fluidly connecting the first plenum and the second plenum. A valve disposed in the fluid passage selectively blocks or allows fluid communication between the high pressure surface and the low pressure surface to eliminate cavitation.
摘要翻译：受控的被动孔隙系统包括用于在多相液体中操作的提升装置，提升装置具有具有多个孔的低压表面和具有多个孔的高压表面。在提升装置内设置有一个共同的通风室，并允许在邻近高压表面的液体和邻近低压表面的液体之间流体连通。当气蚀邻近低压表面发生时，与孔相关联的一系列阀允许表面之间的选择性和局部流体连通。流体通信具有在空化区域中提高液体的压力的效果，从而消除空化。在替代实施例中，提升装置包括第一增压室，第二增压室和中间流体通道，流体通道流体连接第一增压室和第二增压室。设置在流体通道中的阀选择性地阻挡或允许高压表面和低压表面之间的流体连通以消除气蚀。

4. 发明授权

US09963223B2 Aerodynamic force sensing apparatus 有权
公开(公告)号：US09963223B2
公开(公告)日：2018-05-08
申请号：US13007099
申请日：2011-01-14
申请人： Kurt M. Chankaya , Brant H. Maines
发明人： Kurt M. Chankaya , Brant H. Maines
IPC分类号： G06F19/00 , B64C23/06
CPC分类号： B64C23/076 , Y02T50/164
摘要： An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.

5. 发明申请

US20120185181A1 Aerodynamic Force Sensing Apparatus 有权
标题翻译：气动力传感装置
公开(公告)号：US20120185181A1
公开(公告)日：2012-07-19
申请号：US13007099
申请日：2011-01-14
申请人： Kurt M. Chankaya , Brant H. Maines
发明人： Kurt M. Chankaya , Brant H. Maines
IPC分类号： G06F19/00
CPC分类号： B64C23/076 , Y02T50/164
摘要： An aerodynamic force sensing apparatus for providing an air data computer with information to calculate air data. The apparatus includes a plurality of vanes supportable in a vane array extending from a distal end of an airfoil of an aircraft, and one or more sensors configured to sense the response of one or more vanes of the vane array to aerodynamic forces and to transmit corresponding signals to an air data computer (ADC) for use by the ADC in calculating air data.
摘要翻译：一种用于向空中数据计算机提供计算空气数据的信息的空气动力感测装置。该装置包括可从飞行器的翼型件的远端延伸的叶片阵列中支撑的多个叶片，以及配置成感测叶片阵列的一个或多个翼片对于空气动力的响应的一个或多个传感器，并且传送相应的信号到空中数据计算机（ADC）供ADC用于计算空中数据。

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