公开(公告)号：US20150285165A1

公开(公告)日：2015-10-08

申请号：US14439502

申请日：2013-10-22

Applicant: EADS DEUTSCHLAND GMBH

Inventor： Juergen Steinwandel ,  Florian Stagliano ,  Jan Van Toor

IPC: F02D29/02 ,  B64D27/02 ,  B64C39/02 ,  B64D31/00 ,  B64D41/00

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.

Abstract translation: 无人机包括具有柴油或煤油内燃机的推进系统和用于发动机充气的充电装置。 推进系统可以是混合推进系统或并联混合推进系统。

公开(公告)号：US09145207B2

公开(公告)日：2015-09-29

申请号：US14008707

申请日：2012-03-27

Applicant: Jean-Marc Moschetta ,  Chinnapat Thipyopas

Inventor： Jean-Marc Moschetta ,  Chinnapat Thipyopas

IPC: B64C39/02 ,  B64C25/36 ,  B64D45/06

CPC classification number: B64C39/028 ,  B64C25/36 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/18 ,  B64D45/06

Abstract: An aerial micro-drone having a fixed wing supporting a propulsion device. The micro-drone has wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels is located in front of the center of gravity of the micro-drone. The center of gravity of the micro-drone is located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

Abstract translation: 一种具有支撑推进装置的固定翼的空中微型无人机。 微型无人机具有用于在地面上行进的轮子，其附接到机翼的一部分的侧端。 车轮的旋转轴线Y1位于微型无人机的重心的前方。 微型无人机的重心位于微型无人机的空气动力学中心前方。 车轮的旋转轴线Y1与推进装置的推力轴线对准，车轮的尺寸使其半径D / 2大于车轮的旋转轴线Y1和机翼的后缘之间的距离 。

公开(公告)号：US20150266575A1

公开(公告)日：2015-09-24

申请号：US14222158

申请日：2014-03-21

Applicant: Brandon Borko

Inventor： Brandon Borko

IPC: B64C39/02 ,  B64F1/12 ,  G05D1/10 ,  B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/20 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06 ,  B64F1/12 ,  B64F1/222 ,  G05D1/101

Abstract: A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and/or payload capacity.

Abstract translation: 一种用于促进自主着陆和起飞的自动着陆和起飞的系统，其具有在固定或移动着陆地点的协作车身，以及与着陆和起飞机构结合使用的自动存储系统，其存储和服务多个UAV 被描述。 该系统的主要特征在于，着陆机构可设置为具有卷轴，俯仰，偏航以及x，y和z的6个轴线，并与飞行中的空中车辆对准并截取，并相对于车辆的惯性极限使车辆减速。 飞行器和捕获机构设置有发射器和接收器，以协调车辆优先级，着陆机构和机动车辆之间的距离和角度。 着陆和起飞系统具有实时跟踪无人机的位置和方向的方法。 着陆机构将基本上与机动车辆的底座对准。 对于小型无人机，起重能力有限。 通过使着陆板执行着陆操作的精确调整来减少感测和计算要求，可以增加飞行时间和/或有效载荷。

公开(公告)号：US20150225071A1

公开(公告)日：2015-08-13

申请号：US14176960

申请日：2014-02-10

Applicant: Northrop Grumman Systems Corporation

Inventor： Thomas S. Tighe

IPC: B64C3/32 ,  B64C3/38 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: A multi-engine aircraft is disclosed which is convertible from horizontal flight mode to a vertical flight mode. The aircraft comprises an aircraft fuselage defining a fuselage longitudinal axis, and the first and second wing attached to the fuselage. Each wing defines first and second wing segments. The first segments are translatable about the fuselage longitudinal axis, from a horizontal mode position adjacent the second wing segments to vertical fight mode wherein the first wing segment are substantially offset from the second wing segments. An aircraft propulsion unit is attached to each of the first and second wing segments. The propulsion units attached to a common wing being disposed in substantial axial alignment when the aircraft operates in a horizontal flight mode, and being substantially offset when the aircraft operates in a vertical flight mode. A senor unit is connected to a forward portion of the fuselage.

Abstract translation: 公开了一种可从水平飞行模式转换为垂直飞行模式的多引擎飞机。 该飞机包括一个定义机身纵向轴线的飞机机身，以及连接到机身的第一和第二翼。 每个翼限定第一和第二翼段。 第一段可绕机身纵向轴线平移，从邻近第二翼段的水平模式位置到垂直起搏模式，其中第一翼段基本上偏离第二翼段。 飞机推进单元附接到第一和第二翼段中的每一个。 当飞机以水平飞行模式操作时，连接到共同翼的推进单元被布置成基本上轴向对准，并且当飞机以垂直飞行模式操作时基本上偏移。 传感器单元连接到机身的前部。

公开(公告)号：US20150183514A1

公开(公告)日：2015-07-02

申请号：US14643857

申请日：2015-03-10

Applicant: DZYNE Technologies, Inc.

Inventor： MARK ALLAN PAGE ,  MATTHEW ROBERT MCCUE ,  ROBERT ANTHONY GODLASKY

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/38 ,  B64C3/34 ,  B64C5/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

公开(公告)号：US20150028155A1

公开(公告)日：2015-01-29

申请号：US14378633

申请日：2013-02-13

Applicant: Johannes Reiter

Inventor： Johannes Reiter

IPC: B64C27/00 ,  B64C3/38 ,  B64C29/00

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C3/385 ,  B64C27/00 ,  B64C27/001 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00 ,  B64C29/0075 ,  B64C29/02 ,  B64C37/00 ,  B64C39/008 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: The present invention relates to a device for generating aerodynamic lift and in particular an aircraft (100) for vertical take-off and landing. A wing arrangement (110) comprises at least one propulsion unit (111), wherein the propulsion unit (111) comprises a rotating mass which is rotatable around a rotary axis (117). The wing arrangement (110) is mounted to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis (112) of the wing arrangement (110) and such that the wing arrangement (110) is rotatable with respect to the fuselage (101) around a further rotary axis that differs to the longitudinal wing axis (112). An adjusting mechanism adjusts a tilting angle of the wing arrangement (110) around the longitudinal wing axis (112) under influence of a precession force (Fp) which forces the wing arrangement (110) to tilt around the longitudinal wing axis (112).

Abstract translation: 本发明涉及一种用于产生空气动力升降装置，特别涉及用于垂直起飞和着陆的飞机（100）。 机翼装置（110）包括至少一个推进单元（111），其中推进单元（111）包括围绕旋转轴线（117）旋转的旋转块。 机翼装置（110）被安装到机身（101），使得机翼装置（110）围绕机翼装置（110）的纵向翼轴线（112）可倾斜，并且使得机翼装置（110）可旋转 相对于与纵向翼轴（112）不同的另一旋转轴线的机身（101）。 调节机构在促使机翼装置（110）围绕纵向机翼轴线（112）倾斜的进动力（Fp）的影响下调节机翼装置（110）围绕纵向翼轴线（112）的倾斜角度。

公开(公告)号：US08561937B2

公开(公告)日：2013-10-22

申请号：US12906096

申请日：2010-10-17

Applicant: Hosein Goodarzi

Inventor： Hosein Goodarzi

IPC: B64C27/00 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146

Abstract: The various embodiments of the present invention provide an unmanned aerial vehicle comprising a hemispherical body, a brushless type electrical, a propeller, a plurality of wingtip devices, a plurality of servo motors and each of the plurality of the servo motors is connected to each of the plurality of the wingtip devices respectively, a plurality of carbon rods, and a casing. The brushless type electrical motor provides a lifting force for a vertical take-off and landing (VTOL) and the plurality of wing tip devices are classified into three types of wing tip devices and the three types of wing tip devices are controlled by the respective servo motors to control yaw, pitch and roll movements thereby stabilizing and controlling the movement of an aircraft.

Abstract translation: 本发明的各种实施例提供一种无人驾驶飞行器，其包括半球体，无刷电，螺旋桨，多个翼尖装置，多个伺服马达，多个伺服马达中的每一个连接到 多个翼尖装置，多个碳棒，以及壳体。 无刷式电动机为垂直起降提供提升力（VTOL），并且多个翼尖装置分为三种类型的翼尖装置，三种类型的翼尖装置由相应的伺服机构 用于控制偏航，俯仰和滚动运动的电机，从而稳定和控制飞行器的运动。

公开(公告)号：US08473125B2

公开(公告)日：2013-06-25

申请号：US13410229

申请日：2012-03-01

Applicant: Michael Rischmuller ,  Frederic D'haeyer

Inventor： Michael Rischmuller ,  Frederic D'haeyer

IPC: G06F13/00

CPC classification number: A63H27/12 ,  A63H30/04 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2203/00 ,  G05D1/0202 ,  G08C17/02 ,  G08C2201/93

Abstract: The respective motors of the drone (10) can be controlled to rotate at different speeds in order to pilot the drone both in attitude and speed. A remote control appliance produces a command to turn along a curvilinear path, this command comprising a left or right turning direction parameter and a parameter that defines the radius of curvature of the turn. The drone receives said command and acquires instantaneous measurements of linear velocity components, of angles of inclination, and of angular speeds of the drone. On the basis of the received command and the acquired measurements, setpoint values are generated for a control loop for controlling motors of the drone, these setpoint values controlling horizontal linear speed and inclination of the drone relative to a frame of reference associated with the ground so as to cause the drone to follow curvilinear path (C) at predetermined tangential speed (u).

Abstract translation: 无人机（10）的各个电机可以被控制为以不同的速度旋转，以便以姿态和速度引导无人机。 远程控制装置产生沿着曲线路径转动的命令，该命令包括左转或右转转方向参数和限定转弯曲率半径的参数。 无人机接收到所述命令，并获得无人机的线速度分量，倾角和角速度的瞬时测量值。 根据接收到的命令和采集的测量结果，产生用于控制无人机的电动机的控制回路的设定值，这些设定值控制无人机相对于与地面相关的参考系的水平线速度和倾角，因此 以使无人机以预定切向速度（u）跟随曲线路径（C）。

公开(公告)号：US08337156B2

公开(公告)日：2012-12-25

申请号：US12824514

申请日：2010-06-28

Applicant: Dmitry Sergeevich Khmel

Inventor： Dmitry Sergeevich Khmel

IPC: B64C11/30

CPC classification number: B64C11/306 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: The invention relates to aeronautical engineering, in particular to methods of flight due to creating of forces on air propellers, namely using thrust vectoring of direction and amount of force created by air propellers of opposite rotation with the axis, mainly in the direction of flight, in the expanded range of speeds, from 50 m/s to high near-sonic speed of flight. The invention may be applied for horizontal flight and maneuvering in flight on vertical take-off aircrafts using rotation of main rotors from the vertical stand of rotor axes during the take-off to almost horizontal position of rotor axes in horizontal flight, thus both the rotation of rotors and the change of position of an aircraft together with its rotors may be applied, and it may be also used in the horizontal take-off aircrafts with almost horizontal position of axes during the horizontal flight, including the planes with airscrew propellers.

Abstract translation: 本发明涉及航空工程，特别涉及由于在空气螺旋桨上产生力而引起的飞行方法，即使用主要在飞行方向上与轴线相反旋转的空气推进器产生的方向和力的量的推力矢量， 在扩展的速度范围内，从50米/秒到高近似声速的飞行。 本发明可以应用于垂直起飞飞机中的水平飞行和机动飞行，其在起飞期间从转子轴的垂直支架转动到水平飞行中的转子轴线的几乎水平位置，从而旋转 可以应用转子和飞机与其转子的位置的变化，并且还可以在水平飞行中具有几乎水平的轴线位置的水平起飞飞机中使用，包括具有螺旋桨螺旋桨的平面。

公开(公告)号：US20120286102A1

公开(公告)日：2012-11-15

申请号：US13433276

申请日：2012-03-28

Applicant: Pranay Sinha ,  Jeffrey Kyle Gibboney ,  JoeBen Bevirt ,  Piotr Esden-Tempski ,  Christopher Allen Forrette ,  Gregory Mainland Horn

Inventor： Pranay Sinha ,  Jeffrey Kyle Gibboney ,  JoeBen Bevirt ,  Piotr Esden-Tempski ,  Christopher Allen Forrette ,  Gregory Mainland Horn

IPC: B64C13/20 ,  B64C27/26

CPC classification number: B64C29/02 ,  B64C15/00 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/165

Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle which controls the attitude of the vehicle during takeoff and landing by alternating the thrust of engines, which are separated in at least two dimensions relative to the horizontal during takeoff, and which may also control regular flight in some aspects by the use of differential thrust of the engines. A tailless airplane which uses a control system that takes inputs for a traditional tailed airplane and translates those inputs to provide control utilizing non-traditional control methods.

Abstract translation: 一种适用于垂直起飞和着陆的载人/无人机，使用相同的发动机起飞和着陆以及向前飞行。 一种飞行器，其适于在垂直方向上与翼起飞，而不是水平飞行姿态，以垂直姿态起飞，然后转变到水平飞行路径。 一种飞行器，其在起飞和着陆期间通过交替发动机的推力来控制车辆的姿态，发动机的推力在起飞期间相对于水平在至少两个维度上分离，并且还可以通过使用 发动机差动推力。 一种无尾飞机，它使用控制系统，为传统的尾翼飞机提供输入，并转换这些输入，以提供使用非传统控制方法的控制。