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    Apparatus and method for flight control of an aircraft
    181.
    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。

    Convertible vertical take-off and landing miniature aerial vehicle
    182.
    发明授权
    Convertible vertical take-off and landing miniature aerial vehicle 失效
    可转式垂直起降小型飞行器

    公开(公告)号：US06502787B1

    公开(公告)日：2003-01-07

    申请号：US10082814

    申请日：2002-02-22

    Applicant: Ronald Martin Barrett

    Inventor： Ronald Martin Barrett

    IPC: B64C2720

    CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

    Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment and a lower fuselage segment that extend in opposite directions from a rotor guard assembly. A rotor rotates within the rotor guard assembly between the fuselage segments. Plural turning vanes extend from the rotor guard assembly beneath the rotor. Moreover, plural grid fins extend radially from the lower fuselage segment below the turning vanes. The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins.

    Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件沿相反方向延伸的上部机身段和下部机身段。 转子保护组件内的转子在机身段之间旋转。 多个转向叶片从转子下方的转子保护组件延伸。 而且，多个格栅翅片从转向叶片下方的下部机身段径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片在水平飞行模式和垂直飞行模式之间悬停和转换。

    Apparatus and method for flight control of an aircraft
    183.
    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

    Sonotube compatible unmanned aerial vehicle and system
    186.
    发明授权
    Sonotube compatible unmanned aerial vehicle and system 失效
    Sonotube兼容无人机和系统

    公开(公告)号：US6056237A

    公开(公告)日：2000-05-02

    申请号：US882368

    申请日：1997-06-25

    Applicant: Richard L. K. Woodland

    Inventor： Richard L. K. Woodland

    IPC: B64C3/40 ,  B64C3/56 ,  B64C5/12 ,  B64C39/02 ,  B64D1/02 ,  B64D7/08 ,  B64D33/02 ,  F41G3/02 ,  F42B12/36 ,  F42B15/10 ,  F41G7/00 ,  B64C1/00

    CPC classification number: B64C3/40 ,  B64C3/56 ,  B64C39/024 ,  B64C5/12 ,  B64D1/02 ,  B64D33/02 ,  B64D7/08 ,  F41G3/02 ,  F42B12/365 ,  F42B15/105 ,  F42B15/22 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/185 ,  B64C2201/203 ,  Y02T50/145

    Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability.

    Abstract translation: 本发明通常由声纳管相容的无人驾驶飞行器装置（以下称为无人机）和用于发射和控制无人机的系统组成。 无人机通常包括模块化部分，包括鼻部，有效载荷部分，机翼和燃料箱部分以及动力装置部分。 模块化部分通过均匀的锁定密封环和相关部件连接到相邻部分。 本发明包括一种能够进行预编程，通信或遥测任务编程的非常小的，便携式的，弹道发射的，自主的或半自主控制的车辆的装置。 可以在飞行中携带，使用或部署各种有效载荷包，包括应急用品，传感器和天线组件。 便携式操作通过使用发射罐装置来实现。 发射罐包括可伸缩发射稳定腿，涡轮发动机排气孔和各种天线。 发射罐装置可选地包括修改型“A”，“B”或“C”型超声波发射罐。 本发明的系统还包括便携式命令，控制，通信，计算机和智能（C4I）控制和感测分析控制台。 控制台最好是坚固耐用，防水，防震，并且包括必要的控制和分析计算机，输入/输出设备，天线以及用于车辆和任务控制的相关硬件和软件。 C4I控制台和/或发射罐可以通过适于人的便携性的背包来运输。

    Active feedback loop to control body pitch in STOL/VTOL free wing aircraft
    187.
    发明授权
    Active feedback loop to control body pitch in STOL/VTOL free wing aircraft 失效
    主动反馈回路，以控制STOL / VTOL自由翼飞机的车身俯仰

    公开(公告)号：US5769359A

    公开(公告)日：1998-06-23

    申请号：US468420

    申请日：1995-06-06

    Applicant: Elbert L. Rutan ,  Christophe Chevallier

    Inventor： Elbert L. Rutan ,  Christophe Chevallier

    IPC: B64C3/38 ,  B64C29/00 ,  B64C39/02 ,  B64C39/04 ,  B64C13/16

    CPC classification number: B64C3/385 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165

    Abstract: An aircraft control system for controlling an aircraft, particularly a free wing aircraft in low speed or hover regimes. An air speed sensor measures air speed of the aircraft and outputs an air speed signal to a control processor which processes the air speed signal with a speed control input signal. A control actuator actuates an aircraft control surface in response to the control surface control signal. The air speed sensor may include a shaft mounted impeller located in an airstream of the aircraft. A rotational speed sensor, coupled to the impeller, measures a rotational speed of the impeller and outputs a rotational speed signal as the air speed signal. In an alternative embodiment, the air speed sensor may include a vane located in an airstream of the aircraft and deflected in response to air flow in the airstream. In another embodiment, the speed sensor may include an angular position sensor which measures an angle between a free wing and the aircraft fuselage and outputs an angle measurement signal as the air speed signal. The aircraft control surface may comprises a control boom pivotally attached to a fuselage of the aircraft of a trim tab pivotally attached to a fuselage of the aircraft.

    Abstract translation: 用于控制飞机的飞机控制系统，特别是在低速或悬停状态下的自由翼飞机。 空气速度传感器测量飞行器的空气速度，并将空气速度信号输出到控制处理器，该处理器利用速度控制输入信号处理空气速度信号。 响应于控制表面控制信号，控制致动器致动飞行器控制表面。 空气速度传感器可以包括位于飞行器的空气流中的轴安装的叶轮。 耦合到叶轮的转速传感器测量叶轮的转速并输出转速信号作为空气速度信号。 在替代实施例中，空气速度传感器可以包括位于飞行器的空气流中的叶片，并响应气流中的空气流而偏转。 在另一个实施例中，速度传感器可以包括角度位置传感器，其测量自由翼与飞行器机身之间的角度，并输出角度测量信号作为空气速度信号。 飞行器控制表面可以包括枢转地附接到枢转地附接到飞行器的机身的装饰片的飞行器的机身上的控制臂。

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