-
公开(公告)号：WO03004353A9
公开(公告)日：2003-04-10
申请号：PCT/US0221604
申请日：2002-07-08
Applicant: DRAPER LAB CHARLES S
Inventor： PLUMP JOHN M , GUPTA NEIL R
CPC classification number: B64C29/02 , B64C39/024 , B64C39/062 , B64C2201/027 , B64C2201/088 , B64C2201/108 , B64C2201/127 , B64C2201/162
Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.
Abstract translation: 一种包括具有纵向轴线的环形机身和在机身的前缘和后缘之间沿着纵向轴线延伸的管道的飞行器，第一和第二反向旋转的变桨距转子组件，第一和第二反向旋转变桨距转子组件同轴地安装在 机身和至少一个固定到环形机身的鸭翼，并具有定位在机身的导管之外并且在机身的前缘的轴向前方的前缘，其中至少一部分鸭翼包括控制表面 具有可变的迎角。 本发明提供了一种可垂直起降的飞行器，在固定的空间点上长时间悬停并在封闭区域内运行。 飞行器也能够在悬停和高速前飞之间转换。
-
公开(公告)号：WO03004353A3
公开(公告)日：2003-09-18
申请号：PCT/US0221604
申请日：2002-07-08
Applicant: DRAPER LAB CHARLES S
Inventor： PLUMP JOHN M , GUPTA NEIL R
CPC classification number: B64C29/02 , B64C39/024 , B64C39/062 , B64C2201/027 , B64C2201/088 , B64C2201/108 , B64C2201/127 , B64C2201/162
Abstract: An aerial vehicle (10) including a toroidal fuselage (12) having a longitudinal axis (14), and a duct (16) extending along the longitudinal axis (14) between a leading edge (18) and a trailing edge (20) of the fuselage (12), first and second counter-rotating, variable pitch rotor assemblies (22, 24) coaxially mounted within the duct (16) of the fuselage (12), and at least one canard wing (26) secured to the toroidal fuselage (12) and having a leading edge (28) positioned out of the duct (16) of the fuselage (12) and axially forward of the leading edge of the fuselage (12), wherein at least a portion of the canard wing (26) comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle (10) that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operated in confined areas. The aerial vehicle (10) also has the ability to transition between a hover and high speed forward flight.
Abstract translation: 包括具有纵向轴线（14）的环形机身（12）的空中飞行器（10）和沿着纵向轴线（14）在前缘（18）和后缘（20）之间延伸的管道（16） 机体（12），同轴地安装在机身（12）的管道（16）内的第一和第二反向旋转变桨距转子组件（22,24），以及至少一个固定到环形的叶片（26） 机身（12）并具有位于机身（12）的导管（16）之外的前缘（28）并且机身（12）的前缘的轴向前方，其中，所述机翼（12）的至少一部分 26）包括具有可变迎角的控制表面。 本发明提供一种能够垂直起飞和着陆的飞行器（10），在固定的空间点上悬停长时间，并在密闭区域内操作。 飞行器（10）还具有在悬停和高速前进飞行之间转换的能力。
-
公开(公告)号：AU2002354809A1
公开(公告)日：2003-01-21
申请号：AU2002354809
申请日：2002-07-08
Applicant: DRAPER LAB CHARLES S
Inventor： PLUMP JOHN M , GUPTA NEIL R
Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.
-
-
Search Results
3
records
(took 0.02 seconds)
