公开(公告)号：EP2722277A1

公开(公告)日：2014-04-23

申请号：EP13171020.4

申请日：2013-06-07

申请人： Bell Helicopter Textron Inc.

发明人： Covington, Charles E. ,  Fenny, Carlos A. ,  Atkins, Brady G.

IPC分类号： B64C27/56 ,  B64C27/00

CPC分类号： B64C27/59 ,  B64C27/605 ,  B64C2027/004 ,  Y10T74/18056

摘要： According to one embodiment, a stability augmentation system 200 includes a master linkage 210, a stability augmentation motor 220, and three linkages 212, 214, 216. A first linkage 212, is coupled to the master linkage 210 and operable to receive movements representative of pilot commands from a pilot command system. A second linkage 214 is coupled between the stability augmentation motor 220 and the master linkage 210 and operable to receive movements representative of augmentation commands from the stability augmentation motor 220. A third linkage 216 is coupled to the master linkage 210 and operable to transmit movements representative of blade position commands to a blade control system 116 in response to the movements representative of pilot commands and the movements representative of augmentation commands.
To be accompanied, when published, by Figure 3 of the drawings.

摘要翻译： 根据一个实施例，稳定性增强系统200包括主联动装置210，稳定性增加电动机220和三个联动装置212,214,216。第一联动装置212联接到主联动装置210并可操作以接收代表 来自飞行员指挥系统的飞行员命令。 第二联动装置214耦合在稳定性增强电动机220和主联动装置210之间，并且可操作以接收代表来自稳定性增强电动机220的增强指令的运动。第三联动装置216耦合到主联动装置210并可操作以传递运动代表 的刀片位置命令响应于代表导向命令的运动和代表增加命令的运动而发生到刀片控制系统116。 随附，当出版时，由图3的附图。

公开(公告)号：EP2722277B1

公开(公告)日：2015-03-11

申请号：EP13171020.4

申请日：2013-06-07

申请人： Bell Helicopter Textron Inc.

发明人： Covington, Charles E. ,  Fenny, Carlos A. ,  Atkins, Brady G.

IPC分类号： B64C27/56 ,  B64C27/00 ,  B64C27/59 ,  B64C27/605

CPC分类号： B64C27/59 ,  B64C27/605 ,  B64C2027/004 ,  Y10T74/18056

公开(公告)号：EP1232943A3

公开(公告)日：2003-03-12

申请号：EP02075616.9

申请日：2002-02-15

申请人： BELL HELICOPTER TEXTRON INC.

发明人： Covington, Cecil E. ,  Stamps, Frank B. ,  Braswell, James L., Jr. ,  Popelka, David A. ,  Bennet, Richard L. ,  Settle, Thomas B., Jr. ,  Covington, Charles E.

IPC分类号： B64C27/605 ,  B64C27/28 ,  B64C29/00

CPC分类号： B64C27/37 ,  B64C27/08 ,  B64C27/605 ,  B64C29/0033

摘要： An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust while allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns, each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each of the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta-3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades in a rotor disk position which is substantially transverse to the craft body; (2) a helicopter mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of flight.

公开(公告)号：EP1232943B1

公开(公告)日：2004-08-11

申请号：EP02075616.9

申请日：2002-02-15

申请人： BELL HELICOPTER TEXTRON INC.

发明人： Covington, Cecil E. ,  Stamps, Frank B. ,  Braswell, James L., Jr. ,  Popelka, David A. ,  Bennet, Richard L. ,  Settle, Thomas B., Jr. ,  Covington, Charles E.

IPC分类号： B64C27/605 ,  B64C27/28 ,  B64C29/00

CPC分类号： B64C27/37 ,  B64C27/08 ,  B64C27/605 ,  B64C29/0033

公开(公告)号：EP1232943A2

公开(公告)日：2002-08-21

申请号：EP02075616.9

申请日：2002-02-15

申请人： BELL HELICOPTER TEXTRON INC.

发明人： Covington, Cecil E. ,  Stamps, Frank B. ,  Braswell, James L., Jr. ,  Popelka, David A. ,  Bennet, Richard L. ,  Settle, Thomas B., Jr. ,  Covington, Charles E.

IPC分类号： B64C27/32 ,  B64C27/605 ,  B64C29/02

CPC分类号： B64C27/37 ,  B64C27/08 ,  B64C27/605 ,  B64C29/0033

摘要： An aircraft with a tilt rotor assembly comprising a craft body, a plurality of rotor blades which are subject to three modes of flight operation, a tilting mast coupling the plurality of rotor blades to the craft body and for selectively moving the plurality of rotor blades between the three modes of flight operation, a hub coupling the plurality of rotor blades to the tilting mast in a manner which transfers torque and thrust while allowing tilting of a rotor thrust vector, a main swashplate for tilting in response to operator input to control the direction of the rotor thrust vector, a plurality of pitch horns, each mechanically coupled to a particular one of the plurality of rotor blades and to the main swashplate, for communicating swashplate input to each of the plurality of rotor blades, a plurality of links coupling the main swashplate to the plurality of pitch horns, wherein each of the plurality of pitch horns is mechanically coupled to a particular one of the plurality of rotor blades by one of the plurality of links in a particular position which yields a delta-3 value which is not optimum, and a feedback swashplate and cooperating feedback links for receiving disk tilting input from the plurality of rotor blades during flight, and for supplying a mechanical input to the main swashplate to compensate for the less than optimum delta-3 coupling between the plurality of pitch horns and the plurality of links. The three modes of flight include: (1) an airplane mode of flight with the plurality of rotor blades in a rotor disk position which is substantially transverse to the craft body; (2) a helicopter mode of flight with the plurality of rotor blades in a rotor disk position substantially parallel to the craft body with direction of flight being controlled by a rotor thrust vector; and (3) a transition mode of flight with the plurality of rotor blades moving between the rotor disk positions associated with the airplane mode of flight and the helicopter mode of flight.

摘要翻译： 一种具有倾斜转子组件的飞机，包括飞行器主体，经受三种飞行操作模式的多个转子叶片，将多个转子叶片耦合到飞行器主体的倾斜杆，以及用于选择性地将多个转子叶片 三种飞行模式，轮毂将多个转子叶片以转向和推力方式传递到倾斜桅杆的方式，同时允许转动推力矢量倾斜;主旋转斜盘，用于响应于操作者输入倾斜以控制方向 转子推力矢量的多个桨距，每一个机械地联接到多个转子叶片中的特定的一个转子叶片上并与主斜盘通信，用于将旋转斜盘输入传送到多个转子叶片中的每一个;多个连杆， 主斜盘到多个桨距角，其中多个俯仰角中的每一个机械地联接到多个旋转中的特定一个 或叶片由特定位置中的一个链接产生不是最佳的Δ-3值，以及反馈斜盘和协作反馈链路，用于在飞行期间从多个转子叶片接收盘倾斜输入，并用于供应 主旋转斜盘的机械输入以补偿多个桨距角与多个连杆之间的不太合适的Δ-3耦合。 三种飞行模式包括：（1）飞行器飞行模式，其中多个转子叶片处于基本上横向于飞行器体的转子盘位置; （2）直升机飞行方式，其中多个转子叶片处于基本上平行于飞行器体的转子盘位置，其中飞行方向由转子推力矢量控制; 和（3）与多个转子叶片在与飞行器飞行模式相关联的转子盘位置与直升机飞行方式之间移动的过渡飞行模式。