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    METHOD FOR IMPROVING GROUND TRAVEL CAPABILITY AND ENHANCING STEALTH IN UNMANNED AERIAL VEHICLES
    34.
    发明申请
    METHOD FOR IMPROVING GROUND TRAVEL CAPABILITY AND ENHANCING STEALTH IN UNMANNED AERIAL VEHICLES 有权
    改善地面行驶能力和增强无人驾驶车辆的稳定性的方法

    公开(公告)号：US20130214089A1

    公开(公告)日：2013-08-22

    申请号：US13769839

    申请日：2013-02-19

    Applicant: Borealis Technical Limited

    Inventor： Joseph Cox ,  Rodney T. Cox ,  Isaiah W. Cox

    IPC: B64C25/40

    CPC classification number: B64C39/024 ,  B64C25/405 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/22 ,  Y02T50/823

    Abstract: A method for improving ground movement capability and enhancing stealth in unmanned aerial vehicles is provided. The present method comprises providing, in an unmanned aerial vehicle equipped with wheels, one or more onboard drive means capable of translating torque through the vehicle wheels and controllable to move the unmanned aerial vehicle on the ground without reliance on the unmanned aerial vehicle main motive power source. The onboard drive means is controllably powered by a power source with substantially no acoustic signature to move the unmanned aerial vehicle quietly on the ground with only a minimal audible or visible footprint. This method provides a significant expansion of ground movement capability and expands the potential ground uses of unmanned aerial vehicles, particularly in military applications. The present method can also be applied to move any manned aerial vehicle or aircraft on the ground with only minimal audible or visible footprints.

    Abstract translation: 提供了一种提高无人机的地面运动能力和增强隐身的方法。 本方法包括在配备有车轮的无人驾驶飞行器中提供一个或多个车载驱动装置，其能够通过车轮平移扭矩并且可控制地将无人驾驶飞行器移动到地面上，而不依赖于无人驾驶飞行器主动力 资源。 车载驱动装置由具有基本上没有声学特征的电源可控地供电，以无限可听或可见的足迹静止地移动无人驾驶飞行器在地面上。 这种方法大大扩展了地面运动能力，并扩大了无人机的潜在地面用途，特别是在军事应用中。 本方法也可以应用于将任何载人飞行器或飞机移动到地面上，只有最小的可听见的或可见的脚印。

    Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
    35.
    发明授权
    Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft 有权
    降低视力旋翼航空器的可视性旋翼航空器和控制飞行的方法

    公开(公告)号：US07104862B2

    公开(公告)日：2006-09-12

    申请号：US11189605

    申请日：2005-07-26

    Applicant: Michael A. Dammar

    Inventor： Michael A. Dammar

    IPC: A63H27/12

    CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

    Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

    Abstract translation: 旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。 当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。 飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。 飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。 俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

    Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft
    36.
    发明申请
    Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft 失效
    降低视力旋翼航空器的可视性旋翼航空器和控制飞行的方法

    公开(公告)号：US20040251377A1

    公开(公告)日：2004-12-16

    申请号：US10855275

    申请日：2004-05-26

    Inventor： Michael A. Dammar

    IPC: B64C027/22

    CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

    Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

    Abstract translation: 旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。 当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。 飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。 飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。 俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

    Method and system for flying an aircraft
    37.
    发明授权
    Method and system for flying an aircraft 有权
    飞机飞行方法和系统

    公开(公告)号：US06793171B1

    公开(公告)日：2004-09-21

    申请号：US10406047

    申请日：2003-04-02

    Applicant: Walter D. Clark

    Inventor： Walter D. Clark

    IPC: B64D1100

    CPC classification number: B64C39/024 ,  B64C17/00 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/22

    Abstract: A method for flying an aircraft includes flying the aircraft at a first approximately level position and changing the flight of the aircraft from the first approximately level position to a climbing position. The method includes changing the flight of the aircraft from the climbing position to a second approximately level position to achieve a weightless state during the change to the second approximately level position and rolling the aircraft during the weightless state using one or more rolling control surfaces of the aircraft to establish a bank for a turn without creating adverse yaw. The aircraft does not include a deflectable spoiler, fin or rudder to counter adverse yaw. The rolling control surfaces of the aircraft may comprise elevons of the aircraft.

    Abstract translation: 用于飞行飞行器的方法包括以第一近似水平位置飞行飞行器，并且将飞行器的飞行从第一近似水平位置改变到攀爬位置。 该方法包括将飞行器的飞行从爬升位置改变到第二近似水平位置，以在改变到第二近似水平位置期间实现失重状态，并且在失重状态期间使用一个或多个滚动控制表面滚动飞行器 飞机建立一个转弯的银行，而不会造成不利的偏航。 飞机不包括可偏转的扰流板，翅片或方向舵以抵御不利的偏航。 飞行器的滚动控制表面可以包括飞机的升降机。

    Stealthy duffel bag airplane
    38.
    发明申请
    Stealthy duffel bag airplane 失效
    隐形行李袋飞机

    公开(公告)号：US20030192985A1

    公开(公告)日：2003-10-16

    申请号：US10408981

    申请日：2003-04-08

    Inventor： Jay Lipeles

    IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

    CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

    Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

    Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为一个小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

    Apparatus and method for flight control of an aircraft
    39.
    发明授权
    Apparatus and method for flight control of an aircraft 失效
    飞机飞行控制的装置和方法

    公开(公告)号：US06568635B2

    公开(公告)日：2003-05-27

    申请号：US09898631

    申请日：2001-07-02

    Applicant: Billy R. Carpenter

    Inventor： Billy R. Carpenter

    IPC: B64C2900

    CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

    Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces.

    Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 使用进气口，向外排气和放气的前表面上的不同升力来控制和稳定飞行中的飞机，避免了空气动力学控制面的需要。

    Apparatus and method for flight control of an aircraft
    40.
    发明申请
    Apparatus and method for flight control of an aircraft 失效
    飞机飞行控制的装置和方法

    公开(公告)号：US20030001046A1

    公开(公告)日：2003-01-02

    申请号：US09898631

    申请日：2001-07-02

    Inventor： Billy R. Carpenter

    IPC: B64C013/16

    CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

    Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces

    Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 前进表面上带有进气口，向导排气和排气的不同升降机用于在飞行过程中控制和稳定飞机，避免了空气动力学控制面的需要

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