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    Gyrostabilized self propelled aircraft
    41.
    发明申请
    Gyrostabilized self propelled aircraft 有权
    Gyrostabilized自推进飞机

    公开(公告)号：US20040129828A1

    公开(公告)日：2004-07-08

    申请号：US10390222

    申请日：2003-03-17

    Inventor： Nicolae Bostan

    IPC: B64C015/00 ,  B64C029/00

    CPC classification number: B64C17/06 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

    Abstract: An unmanned air vehicle comprises a fuselage that defines aerodynamic flight surfaces, an engine mounted to the fuselage having an engine shaft arranged to rotate about a longitudinal axis with respect to the fuselage, and a propeller mounted to the engine shaft so as to rotate to thereby provide thrust. The aircraft also comprises a gyroscopic stabilization member coupled to the shaft such that rotation of the engine shaft results in rotation of the gyroscopic member. Thus, there is more stability during the entire flight envelope. In one embodiment, the gyroscopic stabilization member is comprised of a ring that is attached to the outer ends of the blades of the propeller and the ring is also selected so as to have a mass that will result in the gyroscopic stabilization member having a sufficient angular momentum so as to gyroscopically stabilize the aircraft.

    Abstract translation: 无人驾驶飞行器包括限定空气动力学飞行表面的机身，安装到机身上的发动机，其具有被布置为围绕相对于机身的纵向轴线旋转的发动机轴，以及安装到发动机轴上以便旋转的螺旋桨 提供推力。 飞机还包括联接到轴的陀螺稳定构件，使得发动机轴的旋转导致陀螺仪构件的旋转。 因此，在整个飞行包络中有更多的稳定性。 在一个实施例中，陀螺稳定构件包括附接到螺旋桨的叶片的外端的环，并且环也被选择为具有将导致陀螺稳定构件具有足够角度的质量 动力，以便陀螺仪稳定飞机。

    Vertical takeoff and landing aerial vehicle
    42.
    发明申请
    Vertical takeoff and landing aerial vehicle 有权
    垂直起降飞机

    公开(公告)号：US20030052222A1

    公开(公告)日：2003-03-20

    申请号：US10191733

    申请日：2002-07-08

    Inventor： John M. Plump ,  Neil R. Gupta

    IPC: B64C029/00

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

    Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.

    Abstract translation: 一种包括具有纵向轴线的环形机身的航空器以及沿着纵向轴线在机身的前缘和后缘之间延伸的管道，同轴地安装在机身的管道内的第一和第二反向旋转的变桨距转子组件 机身，以及至少一个固定在环形机身上的鸭翼，其前缘位于机身的导管之外并且在机身的前缘的轴向前方，其中，所述鸭翼的至少一部分包括控制表面 具有可变的迎角。 本发明提供一种能够垂直起飞并垂直着陆的飞行器，在固定的空间点上长时间悬停，并在密闭区域内操作。 飞行器还具有在悬停和高速前进飞行之间转换的能力。

    Flight control system for a hybrid aircraft in the roll axis
    43.
    发明授权
    Flight control system for a hybrid aircraft in the roll axis 有权
    用于混合飞机在滚动轴上的飞行控制系统

    公开(公告)号：US06431494B1

    公开(公告)日：2002-08-13

    申请号：US09907006

    申请日：2001-07-17

    Applicant: W. Douglas Kinkead ,  Mark W. Scott

    Inventor： W. Douglas Kinkead ,  Mark W. Scott

    IPC: B64C1316

    CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165

    Abstract: A flight control system includes a blending algorithm which evaluates the current flight regime and determines the effectiveness of the flight controls to effect the rotational moment of a hybrid vehicle about the roll axis. Gain schedules for both roll cyclic and aileron control provide a quantitative measure of control effectiveness. Based on the respective gain schedules, the algorithm determines how much of the control commands should be sent to each control surface. The result is that for a given control command, the same amount of roll moment will be generated regardless of flight regime. This simplifies the underlying flight control law since the commands it generates are correct regardless of flight regime.

    Abstract translation: 飞行控制系统包括混合算法，其评估当前飞行状态并且确定飞行控制器实现混合动力车辆围绕滚动轴线的旋转力矩的有效性。 滚动循环和副翼控制的增益计划提供了控制有效性的定量测量。 基于相应的增益计划，该算法确定应将多少控制命令发送到每个控制表面。 结果是对于给定的控制命令，不管飞行情况如何，将产生相同的滚动时刻。 这简化了潜在的飞行控制规则，因为它产生的命令是正确的，无论飞行情况如何。

    Anti-submarine warfare UAV and method of use thereof
    44.
    发明授权
    Anti-submarine warfare UAV and method of use thereof 失效
    反潜战无人机及其使用方法

    公开(公告)号：US06409122B1

    公开(公告)日：2002-06-25

    申请号：US09761076

    申请日：2001-01-17

    Applicant: Leland M. Nicolai

    Inventor： Leland M. Nicolai

    IPC: B64C3500

    CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

    Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

    Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。

    Flight vehicle
    46.
    发明授权
    Flight vehicle 失效
    飞行车

    公开(公告)号：US4037807A

    公开(公告)日：1977-07-26

    申请号：US588882

    申请日：1975-06-20

    Applicant: Thomas Johnston ,  Frederick Peter Youens

    Inventor： Thomas Johnston ,  Frederick Peter Youens

    IPC: B64C29/02 ,  B64C39/06

    CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162

    Abstract: A flight vehicle comprises a vehicle body with a duct having a longitudinal axis extending through the body, and a fan for inducing a flow of ambient air through the duct from an inlet end to an outlet end to provide a thrust acting along the axis of the duct. A system of control is provided for varying the attitude of the vehicle without re-directing or substantially re-directing the thrust whereby the vehicle is capable of controlled flight from a take-off mode in which the axis of the duct is vertical or substantially vertical, to a forward flight mode in which the axis of the duct is inclined to the vertical. A pair of wings are provided on the outer surface of the body, the wings being on opposite sides of the body and having no or substantially no dihedral.

    Abstract translation: 飞行器车辆包括具有延伸穿过主体的纵向轴线的管道的车体，以及用于引导环境空气从入口端到出口端流过管道的风扇，以提供沿着轴线的作用的推力 管。 提供一种控制系统，用于改变车辆的姿态而不重新引导或基本上重新引导推力，由此车辆能够从其中管道的轴线垂直或基本垂直的起飞模式控制飞行 ，到管道的轴线相对于垂直方向倾斜的向前飞行模式。 一对翅膀设置在身体的外表面上，翅膀位于身体的相对侧，并且没有或基本上没有二面体。

    DRONE
    47.
    发明公开
    DRONE 审中-公开

    公开(公告)号：US20230202652A1

    公开(公告)日：2023-06-29

    申请号：US17645752

    申请日：2021-12-23

    Applicant: OCTOFAN SAS

    Inventor： Pierre Convert

    IPC: B64C29/00 ,  B64C3/54 ,  B64C11/00 ,  B64C11/48 ,  B64C39/02 ,  B64C39/08

    CPC classification number: B64C29/0033 ,  B64C3/54 ,  B64C11/001 ,  B64C11/48 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/162

    Abstract: The aircraft comprises a fuselage defining a fuselage main axis. The fuselage comprises a docking system for fixing removable nacelles. The aircraft has wings equipped with tilting actuators for rotating wings about rotation axes parallel to the fuselage main axis and at least six propellers mechanically connected to the fuselage. The aircraft also has at least one cryo-hydrogen tank and at least one fuel cell for supplying power to the propellers, and
    A capacitor for supplying power to the propellers, charged by at least one fuel cell. This capacitor stores electrical energy greater than the energy needed by all the propellers for ten seconds of hovering flight. Each propeller is equipped with a tilting actuator for rotating the propeller about a rotation axis making an angle of less than 45 degrees with a plane perpendicular to the fuselage main axis. The fuselage having a forward and a rear portion defining a forward to rear order of the propellers, in cruise flight, the two forward propellers are activated to provide vertical thrust, the intermediate propellers between the forward and rearmost propellers are not activated and the two rearmost propellers are activated to provide horizontal thrust.

    THRUST VECTORED MULTICOPTERS
    48.
    发明申请
    THRUST VECTORED MULTICOPTERS 审中-公开

    公开(公告)号：US20190243385A1

    公开(公告)日：2019-08-08

    申请号：US16341978

    申请日：2017-10-18

    Applicant: DEAKIN UNIVERSITY

    Inventor： Sui Yang Khoo ,  Michael John Norton ,  Abbas Zahedi Kouzani

    IPC: G05D1/08 ,  B64C27/08 ,  B64C27/52 ,  B64C39/02 ,  B64C27/20 ,  G05B13/04 ,  G05D1/00

    CPC classification number: G05D1/0858 ,  B64C27/08 ,  B64C27/20 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/162 ,  G05B13/04 ,  G05D1/0088

    Abstract: A method of operating a multicopter comprising a body and n thrusters, each thruster independently actuated to vector thrust angularly relative to the body about at least a first axis, the method comprising modelling dynamics of the multicopter with a mathematical model comprising coupled, non-linear combinations of thruster variables, decoupling the mathematical model into linear combinations of thruster control variables, sensing at least one characteristic of multicopter dynamics, comparing the sensed data with corresponding target characteristic(s), computing adjustments in thruster control variables for reducing the difference between the sensed data and the target characteristic(s) according to a control algorithm, and actuating each thruster according to the computed thruster control variables to converge the multicopter towards the target characteristic(s), wherein the control algorithm is based on the decoupled mathematical model such that each thruster control variable can be adjusted independently.

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