公开(公告)号：EP2230175A3

公开(公告)日：2017-03-08

申请号：EP10275027.0

申请日：2010-03-17

申请人： Lockheed Martin Corporation

发明人： Smith, Brian ,  Maines, Brant ,  Ma, Edward ,  DiGirolamo, Edward ,  Yagle, Patrick

IPC分类号： B64C23/06 ,  B64C1/00 ,  F15D1/00

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 (106). The method includes the steps of positioning a plurality of drag reducing elements on the fuselage (102) of the aircraft, wherein the drag reducing elements (108) are positioned on the fuselage from a position at the breakline of the fuselage (102) and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements (108) 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 (102) at the location where the drag reducing element (108) is positioned.

公开(公告)号：EP2230175B1

公开(公告)日：2019-07-31

申请号：EP10275027.0

申请日：2010-03-17

申请人： Lockheed Martin Corporation

发明人： Smith, Brian ,  Maines, Brant ,  Ma, Edward ,  DiGirolamo, Edward ,  Yagle, Patrick

IPC分类号： B64C23/06 ,  B64C1/00 ,  F15D1/00

公开(公告)号：EP2230175A2

公开(公告)日：2010-09-22

申请号：EP10275027.0

申请日：2010-03-17

申请人： Lockheed Martin Corporation

发明人： Smith, Brian ,  Maines, Brant ,  Ma, Edward ,  DiGirolamo, Edward ,  Yagle, Patrick

IPC分类号： B64C23/06 ,  B64C1/00

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 (106). The method includes the steps of positioning a plurality of drag reducing elements on the fuselage (102) of the aircraft, wherein the drag reducing elements (108) are positioned on the fuselage from a position at the breakline of the fuselage (102) and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements (108) 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 (102) at the location where the drag reducing element (108) 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，特别是具有上升的后身体（106）的飞机。 该方法包括以下步骤：将多个减阻元件定位在飞行器的机身（102）上，其中减阻元件（108）从机身（102）的断线处的位置定位在机身上并延伸 朝着飞机的尾巴。 在优选实施例中，多个减阻元件（108）中的每个减速元件（108）被定位成使得减阻元件的第一端相对于机身周围的空气流动成大约15和35°之间的角度（ 102）位于减阻元件（108）所在的位置。