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1. 发明申请

US20130134264A1 Electric Motor Powered Rotor Drive for Slowed Rotor Winged Aircraft 审中-公开
标题翻译：用于减速转子翼型飞机的电动马达驱动转子驱动
公开(公告)号：US20130134264A1
公开(公告)日：2013-05-30
申请号：US13445594
申请日：2012-04-12
申请人： Jay W. Carter, JR. , Jeffrey R. Lewis
发明人： Jay W. Carter, JR. , Jeffrey R. Lewis
IPC分类号： B64C27/22 , B64C9/00 , B64D35/00 , B64C27/26 , B64C27/28
CPC分类号： B64C27/025 , B64D2027/026
摘要： A rotor aircraft has an engine, a propeller, wings, and a rotor. An electric motor is coupled to the rotor drive shaft for applying torque to the rotor drive shaft. The electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected speed prior to liftoff of the aircraft. The wings are capable of providing substantially all of the lift required during forward flight at a cruise speed. The rotor being is capable of being trimmed to provide substantially zero lift and auto-rotate at cruise speed. Sensors sense flight conditions of the aircraft and provide signals to a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed. The controller also causes the electric motor to apply torque to the rotor drive shaft if the sensors indicate additional rotor speed is needed.
摘要翻译：转子飞机有发动机，螺旋桨，机翼和转子。电动机联接到转子驱动轴上以向转子驱动轴施加扭矩。电动机的尺寸被设计成提供所有的扭矩以在飞机起飞之前将转子预旋转至选定的速度。机翼能够以巡航速度提供在向前飞行期间所需的基本上所有的升力。转子能够被修整以提供基本上的零升程并且以巡航速度自动旋转。传感器感测飞行器的飞行状态，并向控制器提供信号，该控制器选择性地使电动机停止在巡航速度的自动转速期间向转子驱动轴施加扭矩。如果传感器指示需要额外的转子速度，则控制器还使电动机向转子驱动轴施加扭矩。

2. 发明授权

US07448571B1 Rotor collective pitch VS Mu to control flapping and mast/rotor tilt to control rotor RPM 有权
标题翻译：转子集合桨距VS Mu来控制摇摆和桅杆/转子倾斜以控制转子RPM
公开(公告)号：US07448571B1
公开(公告)日：2008-11-11
申请号：US11280064
申请日：2005-11-16
申请人： Jay W. Carter, Jr. , Jeffrey R. Lewis
发明人： Jay W. Carter, Jr. , Jeffrey R. Lewis
IPC分类号： B64C27/52
CPC分类号： B64C27/021 , B64C27/02 , B64C27/024
摘要： A method of operating a rotor aircraft involves measuring an airspeed of the aircraft and a rotational speed of the rotor. A controller determines a Mu of the rotor based on the airspeed of the aircraft and the rotational speed of the rotor. The controller varies the collective pitch of the rotor blades in relationship to the Mu, from an inertia powered jump takeoff, through high speed high advance ratio flight, through a low speed landing approach, to a zero or short roll flare landing. In addition as the rotor is unloaded and the rotor slows down, the controller maintains a minimum rotor RPM with the use of a tilting mast.
摘要翻译：操作转子飞行器的方法涉及测量飞行器的空速和转子的转速。控制器基于飞行器的空速和转子的转速确定转子的Mu。控制器通过惯性动力跳跃起飞，通过高速高速提升比飞行，通过低速着陆方式，将零转动叶片的集体桨距与Mu相关联，改变为零或短滚动光晕着陆。此外，当转子卸载并且转子减速时，控制器使用倾斜桅杆保持最小转子RPM。

3. 发明授权

US6155784A Variable pitch aircraft propeller 失效
标题翻译：变桨飞机螺旋桨
公开(公告)号：US6155784A
公开(公告)日：2000-12-05
申请号：US4692
申请日：1998-01-08
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C11/06 , B64C11/26 , B64C27/33 , B64C27/48
CPC分类号： B64C11/06
摘要： A propeller for aircraft has a tip-to-tip flex-beam spar and torsionally stiff hollow blades bonded to the spar throughout an outer portion of the blades. The spar has two end caps which are separated from each other at the hub and converge in the outer portion. The blades have an inner region which is not bonded to the spar, allowing an inner portion of the spar to twist during pitch changes. A counterweight is mounted to an arm extending from an inner end cuff of each blade. The counterweight is located out of the plane of rotation. The counterweight is also located on a side of a line opposite from the trailing edge, the line passing through the pivot axis perpendicular to the plane of rotation.
摘要翻译：飞机的螺旋桨具有尖端到尖端的弯梁梁和扭转刚性的中空叶片，其在叶片的外部部分结合到翼梁。翼梁具有两个端盖，它们在轮毂处彼此分离并在外部收敛。叶片具有未结合到翼梁的内部区域，允许翼梁的内部在桨距变化期间扭曲。配重安装到从每个叶片的内端箍延伸的臂上。配重位于旋转平面之外。配重也位于与后缘相反的线的一侧，该线通过垂直于旋转平面的枢转轴线。

4. 发明申请

US20120325340A1 Apparatus to eliminate back drive in push pull system of rotor aircraft and related methods 失效
标题翻译：用于消除转子飞机推拉系统背驱的装置及相关方法
公开(公告)号：US20120325340A1
公开(公告)日：2012-12-27
申请号：US13532213
申请日：2012-06-25
申请人： Jay W. Carter, JR. , M. Keith Robinson , Jeffrey R. Lewis
发明人： Jay W. Carter, JR. , M. Keith Robinson , Jeffrey R. Lewis
IPC分类号： F16K15/00
CPC分类号： B64C13/30 , B64C13/40 , B64C27/024 , B64C27/52 , Y10T137/7838
摘要： Apparatus and methods for eliminating back drive in a push pull type control system, are provided. An exemplary apparatus includes a control rod including a pair of spaced apart piston displacement members each configured to carry a check valve. The apparatus also includes a pair of opposite-face check valves each configured to seal against respective opposing face of a piston head to form a hydraulic lock, preventing back drive in the control system.
摘要翻译：提供了用于消除推拉式控制系统中的后退驱动的装置和方法。示例性装置包括控制杆，其包括一对间隔开的活塞位移构件，每个构件用于承载止回阀。该装置还包括一对相对面止回阀，每个相对面止回阀均构造成密封活塞头的相对面，以形成液压锁，防止控制系统中的后驱动。

5. 发明授权

US07677492B1 Automatic mechanical control of rotor blade collective pitch 有权
标题翻译：自动机械控制转子叶片集体间距
公开(公告)号：US07677492B1
公开(公告)日：2010-03-16
申请号：US11280036
申请日：2005-11-16
申请人： Jay W. Carter, Jr. , Jeffrey R. Lewis
发明人： Jay W. Carter, Jr. , Jeffrey R. Lewis
IPC分类号： B64C27/00
CPC分类号： B64C27/022 , B64C27/025
摘要： A rotary aircraft has a fuselage with wings and a rotor. The blades of the rotor are twistable about a pitch axis to vary collective pitch. A collective pitch shaft moves in an advancing direction to increase the collective pitch. Weights are mounted to the blades for outward movement along the blades in response to an increase in rotational speed of the blades. A linkage between each of the weights and the collective pitch shaft moves the collective pitch shaft in the advancing direction in response to an increase in rotational speed. A spring acting through a cam mechanism exerts a non linear force in opposition to the outward movement of the blades.
摘要翻译：旋转飞机具有机翼和转子的机身。转子的叶片围绕俯仰轴线是可扭转的，以改变总体间距。集体节距轴在前进方向上移动以增加集体节距。响应于叶片的转速的增加，重量被安装到叶片上以沿叶片向外运动。每个重物和集体节距轴之间的联动响应于转速的增加而使总倾斜轴沿前进方向移动。通过凸轮机构作用的弹簧相对于叶片向外的运动产生非线性力。

6. 发明授权

US07490792B1 Aircraft with rotor vibration isolation 有权
标题翻译：具有转子振动隔离的飞机
公开(公告)号：US07490792B1
公开(公告)日：2009-02-17
申请号：US11280127
申请日：2005-11-16
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C27/025 , B64C27/12 , B64C27/26 , B64C2027/004
摘要： A rotor aircraft has a fuselage with a rotor mounted above by a rotor shaft. An arm is pivotally engaged with a lower portion of the rotor shaft and pivotally engaged with the fuselage, enabling the rotor to move with little restriction vertically and horizontal in all directions relative to the fuselage as the rotor rotates in order to isolate rotor oscillations. An infinitely variable air spring is used to counter vertical and fore and aft loads. Damping in the form of elastomeric materials, piston seal friction, and fluid flow through an orifice may be added as required.
摘要翻译：转子飞机具有机身，转子由转子轴安装在上面。臂与转子轴的下部可枢转地接合并与机身枢转地接合，使得转子能够随着转子旋转而在相对于机身的所有方向上垂直和水平的方向上移动很小，以隔离转子振荡。无级变速空气弹簧用于对抗垂直和前后负载。根据需要可以加入弹性体材料，活塞密封件摩擦和通过孔的流体流动的阻尼。

7. 发明授权

US06527515B2 Rotor for rotary wing aircraft 有权
标题翻译：旋翼飞机转子
公开(公告)号：US06527515B2
公开(公告)日：2003-03-04
申请号：US09863655
申请日：2001-05-23
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C1100
CPC分类号： B64C27/473 , B64C2027/4736 , Y10S416/50
摘要： A rotor for rotary wing aircraft includes a number of features that reduce the collective forces required to control the pitch of the rotor. The spar caps of the spar become joined to one another at the same point where bonding begins between the blade and the spar. The tendency of blade to want to flatten out is minimized since the centrifugal force acting on the spar is located at or near the pitch change axis. Tip weights are located at or near the pitch change axis as well. In a preferred embodiment, the tip weights are located evenly in front of and behind the structural center of the inboard section of the spar. The blade of the rotor and the tip are not swept back.
摘要翻译：用于旋转翼飞行器的转子包括减少控制转子桨距所需的集体力量的许多特征。翼梁的翼梁帽在与叶片和翼梁之间开始粘合的同一点处相互连接。由于作用在翼梁上的离心力位于俯仰变化轴线处或附近，所以叶片希望平坦化的趋势被最小化。尖端重量也位于俯仰变化轴上或附近。在优选实施例中，尖端重量均匀地位于翼梁的内侧部分的结构中心的前面和后面。转子叶片和尖端不会扫过。

8. 发明授权

US06405980B1 Control system for rotor aircraft 有权
标题翻译：转子飞机控制系统
公开(公告)号：US06405980B1
公开(公告)日：2002-06-18
申请号：US09644405
申请日：2000-07-25
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C1328
CPC分类号： B64C27/02 , B64C27/027
摘要： A rotor aircraft has an adjusting mechanism that controls the sensitivity of the control stick relative to fore and aft tilt of the rotor. The control stick is pivotable between fore and aft directions as well as laterally about a control stick pivot point. A rotor linkage is connected between the control stick and the rotor rotor head. The rotor linkage assembly tilts the rotor head in response to tilting movement of the control stick. The linkage assembly has a control point that rotates at a radius about the control stick pivot point. An adjusting member located between the control stick and the linkage assembly can be moved to change the radius of the control point to the control stick pivot point. The change in radius corresponds to the amount of tilt that the rotor head make while the control stick moves between full aft and full forward positions. The control stick also controls ailerons and a horizontal stabilizer but these control services are not affected by the adjusting member.
摘要翻译：转子飞机具有调节机构，其控制控制棒相对于转子的前后倾斜的灵敏度。控制杆可以在前后方向之间枢转，并且围绕控制杆枢转点横向旋转。转子连杆连接在控制棒和转子转子头之间。转子连杆组件响应于控制棒的倾斜运动而使转子头倾斜。连杆组件具有以围绕控制杆枢转点的半径旋转的控制点。可以移动位于控制棒和连杆组件之间的调节构件，以将控制点的半径改变到控制杆枢转点。半径的变化对应于转子头在整个后部和全部向前位置之间移动时所产生的倾斜量。控制杆还控制副翼和水平稳定器，但这些控制服务不受调节构件的影响。

9. 发明授权

US6077041A Reduction drive and torque-limiting clutch for autogyro aircraft 失效
标题翻译：自动飞机的减速驱动和扭矩限制离合器
公开(公告)号：US6077041A
公开(公告)日：2000-06-20
申请号：US4499
申请日：1998-01-08
申请人： Jay W Carter, Jr.
发明人： Jay W Carter, Jr.
IPC分类号： B64C27/02 , B64D35/00 , A47C7/74
CPC分类号： B64D35/00 , B64C27/025
摘要： A rotary wing aircraft has an engine, an engine-driven shaft and a main rotor. A rotor drive shaft is mounted to the main rotor and extends substantially 90 degrees to the engine-driven shaft. A drive pulley is mounted to the engine-driven shaft. A driven pulley is operatively coupled to the rotor drive shaft. A drive belt extends around the drive and driven pulleys. A fluid cylinder has one end stationarily mounted to the engine and another end operatively coupled to the driven pulley to selectively move the driven pulley away from the drive pulley. This movement applies tension in the belt to cause the drive pulley to rotate the main rotor.
摘要翻译：旋翼飞机具有发动机，发动机驱动的轴和主转子。转子驱动轴安装在主转子上，并且大体上与发动机驱动轴成90度。驱动皮带轮安装在发动机驱动轴上。从动皮带轮可操作地联接到转子驱动轴。传动带围绕传动和从动皮带轮延伸。流体缸具有一端固定地安装在发动机上，另一端可操作地联接到从动滑轮，以选择性地将从动滑轮从驱动滑轮移开。该运动在皮带中施加张力以使驱动皮带轮旋转主转子。

10. 发明授权

US5944283A Crashworthy landing gear shock 失效
标题翻译： Crashworthy起落架震撼
公开(公告)号：US5944283A
公开(公告)日：1999-08-31
申请号：US985892
申请日：1997-12-05
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C25/60 , F16F9/06 , B64C25/58
CPC分类号： B64C25/00 , B64C25/60 , F16F9/06
摘要： A shock absorber, optionally operable as a retractable landing gear actuator, includes a sealed cylinder divided by a cylinder head to define an upper chamber and a lower chamber, the lower chamber further divided by a piston having a piston rod passing in sealed manner through the lower cylinder end. The cylinder head includes one or more orifices, the effective opening of each orifice controlled by a valve, the valve having a stem attached to and passing through the upper cylinder end to the atmosphere, such that the pressure between the piston and the cylinder head is limited to a certain value above atmospheric pressure, regardless of the velocity or position of the piston. The valve is forced toward the closed position by a spring against a stop such that it is always at least partially open. During hard or crash landings, high fluid pressure on the piston or in the upper chamber forces the valve further open.
摘要翻译：可选地可操作为可伸缩起落架致动器的减震器包括由气缸盖分隔以限定上室和下室的密封圆筒，所述下室还包括活塞，所述活塞具有密封方式通过所述活塞杆下气缸端。气缸盖包括一个或多个孔，由阀控制的每个孔的有效打开，阀具有附接到上气缸端并通过上气缸端到大气的杆，使得活塞和气缸盖之间的压力为限制在大气压以上的一定值，而与活塞的速度或位置无关。阀门通过弹簧抵抗关闭位置而被迫朝着关闭位置，使其总是至少部分打开。在硬或碰撞着陆期间，活塞或上部腔室中的高流体压力迫使阀门进一步打开。

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