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91. 发明授权

US09650135B2 Invertible aircraft 有权
公开(公告)号：US09650135B2
公开(公告)日：2017-05-16
申请号：US14885972
申请日：2015-10-16
申请人： AeroVironment Inc.
发明人： Matthew Todd Keennon , Karl Robert Klingebiel
IPC分类号： B64C27/08 , B64C39/02 , B64C27/12 , B64C27/59 , B64C11/20 , B64C11/32 , B64C27/04 , B64C29/00 , B64C27/473 , B64D31/00 , B64C27/06 , G05D1/00
CPC分类号： B64D31/06 , B64C11/20 , B64C11/32 , B64C27/04 , B64C27/06 , B64C27/08 , B64C27/12 , B64C27/473 , B64C27/59 , B64C29/0033 , B64C39/02 , B64C39/024 , B64C39/028 , B64C2027/4733 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/126 , B64C2201/127 , B64D31/00 , G05D1/0038 , G05D1/005
摘要： A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

92. 发明申请

US20160090177A1 METHODS AND APPARATUS TO CONTROL PITCH AND TWIST OF BLADES 审中-公开
标题翻译：控制叶片和叶片的方法和装置
公开(公告)号：US20160090177A1
公开(公告)日：2016-03-31
申请号：US14502655
申请日：2014-09-30
申请人： The Boeing Company
发明人： Ian M. Gunter , Thomas R. Kenow , Chris Jorgens
IPC分类号： B64C27/59
CPC分类号： B64C27/72 , B64C27/605 , B64C2027/7244 , B64C2027/7255 , Y02T50/34
摘要： Methods and apparatus to control pitch and twist of blades are disclosed. An example apparatus includes a twist input assembly driven by a drive shaft that drives a rotation of blades of a rotorcraft, the twist input assembly comprising a twist shaft, a first gear set driven by the drive shaft, and a first frequency controller to create a first rotational speed difference between a first gear of the first gear set and the drive shaft, the first rotational speed difference to cause the twist shaft to oscillate. The examples apparatus includes a pitch input assembly driven by the drive shaft, the pitch input assembly comprising a pitch link in communication with a first one of the blades of the rotorcraft, a second gear set driven by the drive shaft, and a second frequency controller to create a second rotational speed difference between a second gear of the second gear set and the drive shaft, the second rotational speed difference to cause the pitch link to oscillate.
摘要翻译：公开了用于控制叶片的俯仰和扭转的方法和装置。一个示例性装置包括由驱动旋转飞轮的叶片旋转的驱动轴驱动的扭转输入组件，扭转输入组件包括扭转轴，由驱动轴驱动的第一齿轮组，以及第一频率控制器，第一齿轮组的第一齿轮与驱动轴之间的第一转速差，第一转速差导致扭转轴摆动。示例装置包括由驱动轴驱动的桨距输入组件，桨距输入组件包括与旋翼飞机的第一叶片连通的俯仰杆，由驱动轴驱动的第二齿轮组和第二频率控制器以在第二齿轮组的第二齿轮和驱动轴之间产生第二转速差，第二转速差使得音调连杆振荡。

93. 发明授权

US09150308B2 Rotorcraft autopilot system, components and methods 有权
标题翻译： Rotorcraft自动驾驶仪系统，组件和方法
公开(公告)号：US09150308B2
公开(公告)日：2015-10-06
申请号：US13763590
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Marc Feifel , Mark Marvin , Nicolas Albion
IPC分类号： H02K7/14 , B64C27/68 , B64C27/59 , B64C13/04 , B64C13/30 , B64C27/57 , B64C27/58
CPC分类号： B64C27/68 , B64C13/04 , B64C13/18 , B64C13/30 , B64C27/57 , B64C27/58 , B64C27/59 , F16F15/121 , Y02T50/44
摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.
摘要翻译：自动驾驶执行器包括第一和第二电动机，每个电动机包括可旋转的电动机输出轴，使得电动机中的一个或两个可以驱动致动器输出轴。自动驾驶仪主机壳体可拆卸地安装在靠近循环控制的直升机上，并且通常容纳自动驾驶执行器以及主要的自动驾驶仪电子装置。循环式隔振器由致动器轴可拆卸地支撑，用于共同旋转并且耦合到循环控制器，以在致动器轴处衰减循环振动频率，同时致动器轴的低于谐振频率的转速耦合到循环控制。力限制连杆包括第一和第二端以及两者之间的可变长度。当施加小于放开力的力时，力限制连杆具有松弛的长度，并且当施加的力超过转动力以允许引导超驰时，可变长度改变。

94. 发明申请

US20150166175A1 ROTORCRAFT FITTED WITH AN ANTI-TORQUE TAIL ROTOR THAT CONTRIBUTES SELECTIVELY TO PROVIDING THE ROTORCRAFT WITH LIFT AND WITH PROPULSION IN TRANSLATION 有权
标题翻译： ROTORCRAFT配有抗扭转尾转轮，可以选择性地提供翻转和推翻翻译的转子
公开(公告)号：US20150166175A1
公开(公告)日：2015-06-18
申请号：US14564394
申请日：2014-12-09
申请人： AIRBUS HELICOPTERS
发明人： Pierre PRUD'HOMME-LACROIX , Olivier BISTUER
IPC分类号： B64C27/82 , B64C27/52 , B64C27/56 , B64C27/78 , B64C27/59
CPC分类号： B64C27/82 , B64C27/52 , B64C27/56 , B64C27/59 , B64C27/605 , B64C27/78 , B64C2027/8218 , B64C2027/8281
摘要： A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).
摘要翻译：旋翼机设置有具有恒定方向的驱动轴的抗扭矩尾旋翼，并且具有主要设置在旋翼航空器尾翼一侧的转子盘。用于控制尾部转子的叶片的控制机构包括与叶片接合的旋转控制板，并且可通过沿着尾部转子的驱动轴线延伸的控制杆移动。控制板布置在恒定的安装平面（PM）中，用于在叶片间距上提供永久性的周期性变化。控制杆的转动改变了叶片间距的周期性变化在提供对提升作用的贡献之间的作用，并且提供对旋翼飞机平移中的推进作用的贡献，这取决于控制板在其安装中的角度取向飞机（PM）。

95. 发明申请

US20150139799A1 COUNTER-ROTATING ROTOR SYSTEM WITH STATIC MAST 有权
标题翻译：具有静态MAST的反转转子系统
公开(公告)号：US20150139799A1
公开(公告)日：2015-05-21
申请号：US14081300
申请日：2013-11-15
申请人： Sikorsky Aircraft Corporation
发明人： Bryan Kenneth Baskin , Todd A. Garcia
IPC分类号： B64C27/10 , B64C27/59
CPC分类号： B64C27/10 , B64C27/59
摘要： A coaxial, dual rotor system includes a first rotor assembly positioned at a rotor axis. A first rotor quill shaft is operably connected to the first rotor assembly at the rotor axis to drive rotation of the first rotor assembly about the rotor axis. A nonrotating static mast extends along the rotor axis through the first rotor quill shaft. A second rotor assembly is positioned at the rotor axis. A second rotor quill shaft is operably connected to the second rotor assembly to drive rotation of the second rotor assembly about the rotor axis. The second rotor quill shaft is coaxial with the first rotor quill shaft and disposed inside of the static mast. A second rotor bearing is positioned between the second rotor assembly and the static mast to transfer loads from the second rotor assembly to the static mast.
摘要翻译：同轴双转子系统包括位于转子轴线处的第一转子组件。第一转子套筒轴在转子轴线处可操作地连接到第一转子组件，以驱动第一转子组件围绕转子轴线的旋转。非旋转静止桅杆沿着转子轴线延伸穿过第一转子轴线轴。第二转子组件位于转子轴线处。第二转子套筒轴可操作地连接到第二转子组件以驱动第二转子组件围绕转子轴线的旋转。第二转子套筒轴与第一转子套筒轴同轴并且设置在静态桅杆的内部。第二转子轴承定位在第二转子组件和静态桅杆之间，以将载荷从第二转子组件传递到静态桅杆。

96. 发明授权

US08967552B2 Direct-drive control of aircraft stability augmentation 有权
标题翻译：直升机控制飞机稳定性增强
公开(公告)号：US08967552B2
公开(公告)日：2015-03-03
申请号：US13655778
申请日：2012-10-19
申请人： Bell Helicopter Textron Inc.
发明人： Charles E. Covington , Carlos A. Fenny , Brady G. Atkins
IPC分类号： B64C13/40 , B64C27/59 , B64C27/605 , B64C27/00
CPC分类号： B64C27/59 , B64C27/605 , B64C2027/004 , Y10T74/18056
摘要： According to one embodiment, a stability augmentation system includes a master linkage, a stability augmentation motor, and three linkages. A first linkage is coupled to the master linkage and operable to receive movements representative of pilot commands from a pilot command system. A second linkage is coupled between the stability augmentation motor and the master linkage and operable to receive movements representative of augmentation commands from the stability augmentation motor. A third linkage is coupled to the master linkage and operable to transmit movements representative of blade position commands to a blade control system in response to the movements representative of pilot commands and the movements representative of augmentation commands.
摘要翻译：根据一个实施例，稳定性增强系统包括主联动装置，稳定性增加电动机和三个联动装置。第一联动装置耦合到主联动装置并且可操作以从导向指令系统接收代表导向指令的运动。第二联动装置耦合在稳定性增强电动机和主联动装置之间，并且可操作以从稳定性增强电动机接收代表增强指令的运动。第三联动装置联接到主联动装置并且可操作以响应于代表导向命令的运动和代表增加命令的运动而将代表刀片位置命令的运动传送到刀片控制系统。

97. 发明申请

US20140178199A1 System and Method for Linkage Length Adjustment 有权
标题翻译：连接长度调整的系统和方法
公开(公告)号：US20140178199A1
公开(公告)日：2014-06-26
申请号：US14136814
申请日：2013-12-20
申请人： Bell Helicopter Textron Inc.
发明人： Mark A. Wiinikka
IPC分类号： B64C27/59
CPC分类号： B64C27/51 , B64C27/008 , B64C27/32 , F16C11/0614
摘要： A rotor system has a rotor, an axis of rotation about which the rotor may be rotated, a linkage system having a first adjustable length portion and a second adjustable length portion, wherein the second adjustable length portion is configured to provide a relatively finer adjustment of an overall effective length of the linkage system as compared to the first adjustable length portion and wherein the rotor is configured to rotate about the axis in response to changing the overall effective length of the linkage system.
摘要翻译：转子系统具有转子，转子绕其转动的轴线，具有第一可调节长度部分和第二可调节长度部分的连杆系统，其中第二可调整长度部分构造成提供相对更精细的调整与第一可调节长度部分相比，联动系统的整体有效长度，并且其中转子构造成响应于改变连杆系统的整体有效长度而围绕轴线旋转。

98. 发明授权

US5304036A Autogyro aircraft 失效
标题翻译：自动飞机
公开(公告)号：US5304036A
公开(公告)日：1994-04-19
申请号：US626972
申请日：1990-12-12
申请人： Henry J. Groen , David L. Groen
发明人： Henry J. Groen , David L. Groen
IPC分类号： B64C27/43 , B64C27/59
CPC分类号： B64C27/021 , B64C27/43
摘要： An autogyro aircraft has freewheeling rotor blades that provide lift. A separate pusher propeller provides forward thrust. The rotor system (20) has a collective arm (30) as a control for selectively setting and maintaining a tension force on a collective cable to regulate the rotor blade angle of attack or pitch angle between a no-lift attitude and a positive lift angle. The collective arm (30) sets a tension on collective cable against a coil spring biasing. The collective arm is connected to pivot or tilt a pitch change horn assembly and, in turn, connected rotor blades. The collective arm can be selectively set and maintained and released and reset both on the ground and in flight.
摘要翻译：自动飞机具有提供电梯的续流转子叶片。单独的推进推进器提供向前推力。转子系统（20）具有作为控制的集体臂（30），用于选择性地设定和保持集合电缆上的张力，以调节转子叶片的迎角或无提升姿态与正提升角之间的倾角。集体臂（30）根据螺旋弹簧偏置设置集体电缆上的张力。集体臂连接以枢转或倾斜变桨角组件，并且连接转子叶片。集体臂可以在地面和飞行中选择性地设置和维护并释放和复位。

99. 发明授权

US5301900A Autogyro aircraft 失效
标题翻译：自动飞机
公开(公告)号：US5301900A
公开(公告)日：1994-04-12
申请号：US931018
申请日：1992-08-17
申请人： Henry J. Groen , David L. Groen
发明人： Henry J. Groen , David L. Groen
IPC分类号： B64C27/43 , B64C27/02 , B64C27/59 , B64C27/52 , B64C13/04
CPC分类号： B64C27/43 , B64C27/02
摘要： An autogyro has a teetering semi-rigid rotary wing with rigid rotor blades. The angle of attack (blade pitch) of the rotor blades is fully adjustable in flight continuously over an operational range, and varies along the blade length. A prerotator rotates the rotor blades up to takeoff speed at minimum drag, no lift and optimum engine efficiency. Engine power is disconnected from the rotor blades and their angle of attack is changed for optimum lift to facilitate smooth vertical takeoff. Rotor blade pitch is likewise adjusted during vertical landing. In flight, rotor blade angle of attack is varied to adjust autorotation, lift and drag at any flight airspeed. On the ground, the rotary wing is braked to prevent rotation.The autogyro may roll, pitch, or yaw, with complete independence of blade pitch with respect to all other relative motions. The pedals have disproportionate forward and backward motions. The autogyro has retractable gear capable of fail-safe gear-up landing.
摘要翻译：自动扶梯具有带刚性转子叶片的跷跷板半刚性旋翼。转子叶片的迎角（叶片间距）在飞行中在操作范围内连续完全调节，并沿着叶片长度变化。预旋转器将转子叶片以最小的阻力，无提升和最佳的发动机效率旋转起飞速度。发动机功率与转子叶片断开，并且它们的迎角发生变化，以获得最佳的升力，以促进平稳的垂直起飞。在垂直着陆期间，转子叶片桨距同样被调整。在飞行中，转子叶片的迎角受到各种变化，以适应任何飞行速度下的自转，升降和拖曳。在地面上，旋翼被制动以防止旋转。自动扶梯可以相对于所有其他相对运动完全独立于叶片俯仰，俯仰或偏航。踏板有不成比例的前进和后退动议。 autogyro具有能够进行故障安全装备着陆的伸缩装置。

100. 发明授权

US5190243A Device for the adjustment of the maneuver forces of movable members of an aircraft 失效
标题翻译：用于调整飞机可动部件的动力装置
公开(公告)号：US5190243A
公开(公告)日：1993-03-02
申请号：US905458
申请日：1992-06-29
申请人： Bruno Guimbal
发明人： Bruno Guimbal
IPC分类号： B64C13/28 , B64C27/59 , G05G5/22
CPC分类号： G05G5/22 , B64C13/28 , B64C27/59 , Y10T74/20396
摘要： A device for the adjustment of the maneuver forces of movable members of an aircraft. The device includes:a pivoting control column (6);a shaft (7) which is articulated to the column and which is able to pivot around its axis following an angular displacement of the column (6) in a first plane;a first link (8) which is provided between the shaft and at least one first movable member (9), and which gives rise to the displacement of the at least one first movable member;a connecting rod (10) which is articulated to the column and which is able to be displaced in translation parallel to its longitudinal axis following an angular displacement of the column (6) in a second plane;a second link (11) which is provided between the connecting rod and at least one second movable member (12), and which gives rise to the displacement of the at least one second movable member; andfriction unit (13) in order to apply the correct forces for the angular displacements of the column in the two planes, and which is arranged between the first and second links (8, 11). The device can be applied especially to the control of the cyclic plate of the rotor of a helicopter.
摘要翻译：用于调整飞机的可动部件的机动力的装置。该装置包括：枢转控制柱（6）; 轴（7），其铰接到所述柱并且能够在所述柱（6）在第一平面中的角位移之后围绕其轴线枢转; 第一连杆（8），其设置在所述轴与所述至少一个第一可动构件（9）之间，并且引起所述至少一个第一可移动构件的位移; 连杆（10），其连接到所述柱，并且能够在所述柱（6）在第二平面中的角位移之后平行于其纵向轴线平移地平移移位; 第二连杆（11），其设置在所述连杆与至少一个第二可移动部件（12）之间，并且引起所述至少一个第二可移动部件的位移; 和摩擦单元（13），以便对两个平面中的柱的角位移施加正确的力，并且布置在第一和第二连杆（8,11）之间。该装置可以特别适用于直升机转子的循环盘的控制。

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