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11. 发明授权

US5868355A Fuselage door for pressurized aircraft 失效
标题翻译：机身门用于加压飞机
公开(公告)号：US5868355A
公开(公告)日：1999-02-09
申请号：US985557
申请日：1997-12-05
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B63B19/08 , B64C1/14
CPC分类号： B64C1/1423 , B63B19/08 , B64C1/14
摘要： A fuselage door for a pressurized aircraft fuselage in which the hoop tension loads caused by cabin pressure are carried through the door rather than around the door. Stationary interlocking moldings in the door and fuselage door seat transfer loads through the door-fuselage intersection. The interlocking portions of the moldings have a sloped engaging portion having an angle such that the inward directed force component of tension due to a pressure differential is less than the outward directed force from cabin pressure on the door.
摘要翻译：用于加压飞机机身的机身门，其中由机舱压力引起的环箍张力负载通过门而不是围绕门。门内的固定联锁模具和机身门座通过门机身交叉口传递负载。模制品的互锁部分具有倾斜的接合部分，该倾斜的接合部分具有角度，使得由于压力差引起的张力的内向力分量小于从门上的舱室压力的向外的力。

12. 发明授权

US5727754A Gyroplane 失效
标题翻译：陀螺仪
公开(公告)号：US5727754A
公开(公告)日：1998-03-17
申请号：US521690
申请日：1995-08-31
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C27/02
CPC分类号： B64C27/02
摘要： An improved gyroplane having an improved rotor blade with an edgewise stiffness (El) of at least 80,000 pounds inch.sup.2 per pound of aircraft gross weight and blade weights of sufficient size to store a minimum of 100 foot pounds of rotational kinetic energy per pound of gross weight of the gyroplane while the rotor blade pitch is set to minimum lift during blade prerotation. Then a clutch driving the rotor is disengaged and the rotor blade pitch is changed to a lift condition to enable the gyroplane to climb to an altitude of at least fifty feet. The speed and thrust of a propeller is increased to achieve an increasing a horizontal velocity to maintain altitude, first with the rotor blade providing most of the lift and until the wings provide all the lift. To maximize velocity an improved flight control method is utilized. With this method, the angle of attack of the rotor disc is decreased and the pitch of the rotor blade is reduced to decrease rotor blade rotational speed to minimize drag during flight. During horizontal flight while the rotor blade is loaded, the wing is maintained at a constant angle of attack and the horizontal stabilizer is fixed and does not move. (It's angle of attack stays at generally zero degrees.) After the blade is unloaded during horizontal flight, the angle of attack of the rotor disc and the horizontal stabilizer are kept parallel to each other and maintained generally at a zero angle of attack.
摘要翻译：一种改进的陀螺仪，其具有改进的转子叶片，其具有每磅飞机总重量至少为80,000磅英寸2的边缘刚度（E1）和足够尺寸的叶片重量，以在每磅毛重中存储至少100英尺磅的旋转动能的转子叶片间距在叶片预旋转期间设定为最小提升。然后，驱动转子的离合器被分离，并且转子叶片间距变为升高条件，以使陀螺仪爬升到至少五十英尺的高度。增加螺旋桨的速度和推力以实现水平速度的增加以维持高度，首先是转子叶片提供大部分升降机，直到机翼提供所有升降机。为了最大化速度，利用改进的飞行控制方法。通过这种方法，减小了转子盘的迎角，并且减小了转子叶片的间距，从而降低了转子叶片的旋转速度，以最大程度地减少飞行过程中的阻力。在水平飞行期间，当转子叶片被装载时，机翼保持恒定的迎角，水平稳定器是固定的并且不移动。（它的迎角保持在一般为零度）。在水平飞行期间卸载叶片后，转子盘和水平稳定器的迎角保持彼此平行并保持一般为零的迎角。

13. 发明授权

US07510377B1 Rotor aircraft tilting hub with reduced drag rotor head and mast 有权
标题翻译：转子飞机倾斜轮毂减少拖动转子头和桅杆
公开(公告)号：US07510377B1
公开(公告)日：2009-03-31
申请号：US11280117
申请日：2005-11-16
申请人： Jay W. Carter, Jr. , M. Keith Robinson , George D. Mitchell
发明人： Jay W. Carter, Jr. , M. Keith Robinson , George D. Mitchell
IPC分类号： B63H3/02
CPC分类号： B64C27/024 , B64C39/04
摘要： A rotor aircraft has a tilting hub for cyclic control operated by either a tilting spindle or swash plate mounted to the upper end of the drive shaft. A spinner housing with two separate half portions encloses the hub. The blades of the rotor have root portions that are integrally joined to the separate half portions. During a collective pitch change, the half portions rotate relative to each other, but at advance ratios greater than about 0.7, when the collective can be held constant, the spinner half portions can be in perfect alignment. Concentric control sleeves surround the drive shaft for changing collective pitch as well as cyclic pitch.
摘要翻译：转子飞机具有用于循环控制的倾斜轮毂，其通过安装到驱动轴的上端的倾斜主轴或斜盘操作。具有两个分开的半部分的旋转器壳体封闭毂。转子的叶片具有与分离的半部分一体地连接的根部。在组合间距变化期间，半部分相对于彼此旋转，但是当预定比大于约0.7时，当集体可以保持恒定时，旋转器半部可以完全对准。同心控制套管围绕驱动轴，用于改变集体节距以及循环间距。

14. 发明授权

US06524068B2 Variable pitch aircraft propeller control with two-speed transmission 有权
标题翻译：变速飞机螺旋桨控制与双速传动
公开(公告)号：US06524068B2
公开(公告)日：2003-02-25
申请号：US09863636
申请日：2001-05-23
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C2700
CPC分类号： B64C11/305 , B64D35/00
摘要： A variable pitch aircraft propeller control uses a two-speed planetary gearbox between a turbine engine and an adjustable pitch propeller. For maximum efficiency, the rotation rate of the propeller is high at aircraft take-off to generate maximum static thrust. However, when at high altitude and at high speed, the propeller rotation rate is reduced to hold the vector sum of the aircraft forward speed and the propeller rotational tip speed at the speed that results in the highest efficiency for the propeller. The two-speed transmission supplies these two gear ratios. At takeoff and low altitude flight, a low gear ratio is used. At high altitude, a high gear ratio is used. The gear ratio maybe manually selected by the pilot, or automatically changed by the propeller controller to obtain the best combined efficiency for the engine and the propeller.
摘要翻译：变桨距飞机螺旋桨控制器使用涡轮发动机和可调螺距螺旋桨之间的双速行星齿轮箱。为了最大的效率，飞机起飞时螺旋桨的转速高，产生最大静力推力。然而，当在高空和高速时，螺旋桨旋转速度被降低以保持飞行器前进速度和螺旋桨旋转尖端速度的矢量和速度，从而达到螺旋桨的最高效率。双速变速器提供这两个变速比。在起飞和低空飞行时，使用低速比。在高空时，使用高档位。齿轮比可以由飞行员手动选择，或由螺旋桨控制器自动更改，以获得发动机和螺旋桨的最佳组合效率。

15. 发明授权

US06513752B2 Hovering gyro aircraft 有权
公开(公告)号：US06513752B2
公开(公告)日：2003-02-04
申请号：US09862940
申请日：2001-05-22
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C2722
CPC分类号： B64C27/82 , B64C27/02 , B64C27/025 , B64C27/26
摘要： A fixed wing rotorcraft uses differential thrust between wing mounted propellers to provide counter torque when the rotor is being powered by a power source. The rotorcraft is comprised of a fuselage to which fixed wings are attached. A rotor is attached on an upper side of the fuselage and provides lift at low speeds while the wings provide a majority of the lift at high speeds. When at high speeds the rotor may be slowed to reduce advancing tip speed and retreating blade stall. Forward thrust and counter torque is provided by propellers mounted on either side of the fuselage or even on the wings.

16. 发明授权

US06435453B1 High speed rotor aircraft 有权
标题翻译：高速转子飞机
公开(公告)号：US06435453B1
公开(公告)日：2002-08-20
申请号：US09641364
申请日：2000-08-18
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C2702
CPC分类号： B64C27/02
摘要： An improved method of operating rotorcraft capable of achieving high speeds such that stability is maintained as the craft speed exceeds 0.75 times the rotor tip speed. These high speeds are achieved by varying collective pitch, including to negative values, to maintain acceptable levels of flapping at high aircraft forward speeds and low rotor rotation rates, or adjusting or maintaining the rotor rotation rate by automatically controlling the tilt of the rotor disk relative to the airstream or aircraft, or a combination of these techniques. More specifically, by utilizing these techniques the forward aircraft speeds can be high enough, and the rotor rotation rates low enough, that an advance ratio, Mu, greater than 0.75 can be achieved while maintaining rotor stability.
摘要翻译：一种改进的能够实现高速度的旋翼航空器的方法，使得当飞行速度超过转子尖端速度的0.75倍时，维持稳定性。这些高速度通过改变总体间距（包括负值）来实现，以在高飞机前进速度和低转子旋转速度下保持可接受的振荡水平，或通过自动控制转子盘相对的倾斜来调节或维持转子旋转速率气流或飞机，或这些技术的组合。更具体地说，通过利用这些技术，前进飞机的速度可以足够高，并且转子旋转速度足够低，可以在保持转子稳定性的同时实现大于0.75的提前比率Mu。

17. 发明授权

US6024325A Rotor for rotary wing aircraft 失效
标题翻译：旋翼飞机转子
公开(公告)号：US6024325A
公开(公告)日：2000-02-15
申请号：US4498
申请日：1998-01-08
申请人： Jay W. Carter, Jr.
发明人： Jay W. Carter, Jr.
IPC分类号： B64C27/46 , B64C27/52
CPC分类号： B64C27/46
摘要： A rotor for rotary wing aircraft has a tip to tip flex-beam spar and torsionally stiff hollow blades bonded to the spar throughout the tip-most portion of the blades. The spar spaced-apart spar caps which have a dual beam cross section in the region not bonded to the blades so that the spar is twistable for pitch control. The rotor spindle and controls pass through a central hole between the spar caps. An intermediate section of the rotor has shear webs bonded above and below spaced-apart spar caps, providing a stiff box beam cross section. The spar caps join each other outboard of the intermediate section. The collective control for pitch change employs a coil spring mounted between a pitch horn and a hub.
摘要翻译：用于旋转翼飞行器的转子具有尖端，以使尖翼梁顶端和尖端部分顶端的翼梁和扭转刚性的中空叶片结合到翼梁上。翼梁间隔开的翼梁帽，其在未结合到叶片的区域中具有双梁横截面，使得翼梁可扭转以进行俯仰控制。转子主轴和控制器通过翼梁盖之间的中心孔。转子的中间部分具有结合在间隔开的翼梁帽上方和下方的剪切腹板，提供了一个刚性的箱梁截面。翼梁帽在中间部分的外侧彼此连接。用于间距变化的集体控制采用螺旋弹簧安装在桨距喇叭和轮毂之间。

18. 外观设计

USD381952S Gyroplane 失效
公开(公告)号：USD381952S
公开(公告)日：1997-08-05
申请号：US45457
申请日：1995-10-20
申请人： Jay W. Carter, Jr.
设计人： Jay W. Carter, Jr.

19. 发明授权

US08739679B2 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：US08739679B2
公开(公告)日：2014-06-03
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： B64C13/00 , F15B7/00
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。

20. 发明申请

US20130134253A1 Power 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转子驱动
公开(公告)号：US20130134253A1
公开(公告)日：2013-05-30
申请号：US13305441
申请日：2011-11-28
申请人： Jay W. Carter, JR.
发明人： Jay W. Carter, JR.
IPC分类号： B64C27/00
CPC分类号： B64C27/12 , B64C27/26
摘要： A rotor aircraft has an engine having an output shaft. At least one propeller is driven by the engine to provide forward thrust to the aircraft. Wings provide lift while in forward flight. A rotor is driven by rotor drive mechanism, which selectively provides torque to the rotor drive shaft from the engine while in a first mode. The rotor drive mechanism selectively provides torque to the rotor drive shaft to rotate at a speed independent of a speed of the output shaft of the engine while in a second mode. In one embodiment, the rotor drive mechanism is a variable speed transmission powered by the engine. In another embodiment, the rotor drive mechanism is an electric motor.
摘要翻译：转子飞机具有具有输出轴的发动机。至少一个螺旋桨由发动机驱动，向飞机提供推力。翅膀在向前飞行时提供电梯。转子由转子驱动机构驱动，转子驱动机构在第一模式中选择性地向发动机提供转子驱动轴。在第二模式中，转子驱动机构选择性地向转子驱动轴提供扭矩，以与发动机的输出轴的速度无关的速度旋转。在一个实施例中，转子驱动机构是由发动机驱动的变速传动装置。在另一个实施例中，转子驱动机构是电动马达。

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