公开(公告)号：US07931239B2

公开(公告)日：2011-04-26

申请号：US11838040

申请日：2007-08-13

Applicant: Brad Pedersen ,  Peter Spirov

Inventor： Brad Pedersen ,  Peter Spirov

IPC: B64C13/20

CPC classification number: G05D1/0816 ,  B60V1/06 ,  B60V1/10 ,  B64C15/02 ,  B64C27/08 ,  B64C27/20 ,  B64C39/001 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/10 ,  B64C2201/108 ,  B64C2201/146 ,  B64D27/24 ,  G05D1/0016 ,  G05D1/0022 ,  G05D1/0858

Abstract: A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control.

Abstract translation: 稳态飞行气垫船优选地使用至少两对反向旋转管道风扇来产生类似气垫船的升降机，并且利用稳态悬停控制系统来创建易于控制的飞行器。 稳态悬停控制系统通过真正的线控飞行控制和线控系统控制为飞行器提供真正的动态平衡。

公开(公告)号：US20110017865A1

公开(公告)日：2011-01-27

申请号：US12922895

申请日：2009-03-17

Applicant: Michael Achtelik ,  Jan Stumpf ,  Daniel Gurdan ,  Klaus-Michael Doth

Inventor： Michael Achtelik ,  Jan Stumpf ,  Daniel Gurdan ,  Klaus-Michael Doth

IPC: B64C27/08

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64D47/08

Abstract: The invention relates to a rotary-wing aircraft (100), comprising at least four rotors (110), which are disposed on girder elements (120a, 120b), wherein said rotors (110) and girder elements (120a, 120b) are disposed such that a free field of vision (S) is defined along a longitudinal axis (L) of said rotary-wing aircraft (100) at least between two terminal rotors.

Abstract translation: 本发明涉及一种旋转翼飞机（100），其包括至少四个转子（110），其设置在大梁元件（120a，120b）上，其中所述转子（110）和梁元件（120a，120b） 使得至少在两个终端转子之间沿着所述转翼飞行器（100）的纵向轴线（L）限定自由视野（S）。

公开(公告)号：US20100230547A1

公开(公告)日：2010-09-16

申请号：US12486023

申请日：2009-06-17

Applicant: Steven K. Tayman

Inventor： Steven K. Tayman

IPC: B64C27/24

CPC classification number: B64C27/24 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/108

Abstract: Systems and methods for transitioning an aircraft between helicopter and fixed wing flight modes are provided. In one embodiment, an aircraft comprises a plurality of wings each having a spar and a flap; a flap actuator configured to move the flap with respect to the spar; and a center section rotatably coupled to each spar. The center section includes at least one spar actuator configured to rotate at least one of the wings about a rotational axis of the spar when the aircraft transitions between helicopter and fixed wing flight modes.

Abstract translation: 提供了在直升机和固定翼飞行模式之间转换飞机的系统和方法。 在一个实施例中，飞机包括多个翼，每个翼具有翼梁和翼片; 翼片致动器，其构造成相对于翼梁运动翼片; 以及可旋转地联接到每个翼梁的中心部分。 中心部分包​​括至少一个翼梁致动器，其构造成当飞机在直升机和固定翼飞行模式之间转换时围绕翼梁的旋转轴线旋转至少一个翼。

公开(公告)号：US20100163681A1

公开(公告)日：2010-07-01

申请号：US12622177

申请日：2009-11-19

Applicant: Michael PASTELAK

Inventor： Michael PASTELAK

IPC: B64D37/02 ,  B60K15/03

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64D37/02 ,  Y02T50/44

Abstract: Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a spiral tubing disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV).

Abstract translation: 系统和方法提供了用于储存燃料并将燃料供应给车辆的柔性燃料气囊组件。 柔性燃料气囊组件可以包括：燃料气囊，包括设置成存储燃料并将燃料从其供应的燃料抵抗膜连接在其上的歧管组件; 以及螺旋管，其设置在所述燃料囊内并且设置成防止所述燃料囊的任何两侧或更多侧彼此折叠，并允许大部分燃料以不间断的方式从所述燃料囊供应到所述歧管组件 直到燃料的大部分从燃料囊移除。 柔性燃料囊可用于无人驾驶飞行器（UAV），其可以是以下任何一种：有机飞行器（OAV），微型飞行器（MAV），无人地面车辆（UGV）或无人战斗 机动车（UCAV）。

公开(公告)号：US07712701B1

公开(公告)日：2010-05-11

申请号：US11351775

申请日：2006-02-10

Applicant: Adam S. Ehrmantraut ,  Andrew M. Maust ,  Peter K. Johnson

Inventor： Adam S. Ehrmantraut ,  Andrew M. Maust ,  Peter K. Johnson

IPC: B64C29/00 ,  B64C27/10

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146

Abstract: An unmanned aerial vehicle having counterrotating ducted rotors that are driven by electric motors. The vehicle has a low weight and a small profile. The unmanned aerial vehicle is suitable for a number of different tasks, including control, surveillance and reconnaissance, communication, and other tasks without exposing personnel to dangerous situations. The vehicle is particularly suited for entering buildings and other enclosed structures and spaces such as caves. The unmanned aerial vehicle can also be equipped for potential offensive actions.

Abstract translation: 具有由电动机驱动的反转管状转子的无人驾驶飞行器。 车辆重量轻，外形小巧。 无人驾驶飞行器适合多种不同的任务，包括控制，监视和侦察，通讯等任务，不会使人员处于危险状况。 车辆特别适用于进入建筑物和其他封闭结构和空间，如洞穴。 无人机也可配备潜在的进攻行动。

公开(公告)号：US20100096490A1

公开(公告)日：2010-04-22

申请号：US12288307

申请日：2008-10-18

Applicant: Kevin Patrick Gordon

Inventor： Kevin Patrick Gordon

IPC: B64C27/04 ,  B64C1/06 ,  B64C1/08 ,  B64C37/02 ,  G05D1/00 ,  B64C19/00 ,  B64C17/00

CPC classification number: G05D1/102 ,  B64C27/10 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148

Abstract: The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment.

Abstract translation: 本发明是可由可互换电动机或燃料动力内燃机驱动的无人飞行直升机飞机平台（“飞机平台”）。 飞机平台由一个轻质的外骨架围拢，保护转子叶片与外部物体接触。 飞机平台使用位于飞机平台底部的重物，可以远程移动以调整重心，以便在任何方向上导航。 飞机平台在其底部有一个位置，可以添加或移除附件，从而允许飞机平台用于多种不同的目的。 飞机平台可以使用手持控制单元进行远程飞行和操作，也可以通过位于人体携带附件中的飞行员飞行员进行飞行和操作。

公开(公告)号：US20100044499A1

公开(公告)日：2010-02-25

申请号：US12230119

申请日：2008-08-22

Applicant: Zenon Dragan ,  Orville Olm ,  Greg Wood

Inventor： Zenon Dragan ,  Orville Olm ,  Greg Wood

IPC: B64C27/08

CPC classification number: B64C27/10 ,  B64C1/30 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108

Abstract: A rotary wing aircraft is provided having at least three rotor pairs. Each rotor pair has an upper rotor and a lower rotor. During operation, the upper rotor and lower rotor rotate around a shared rotor axis with the upper rotor rotating in a first direction and the lower rotor rotating in an opposite direction By independently controlling the speed of rotation of each upper rotor and each lower rotor the aircraft can be made to ascend, descend, move forward, move backward, move side to side, yaw right and yaw left by only varying the relative speeds of rotations of the upper rotors and lower rotors.

Abstract translation: 提供具有至少三个转子对的旋转翼飞机。 每个转子对具有上转子和下转子。 在操作期间，上转子和下转子围绕共享转子轴线旋转，上转子沿第一方向旋转，下转子沿相反方向旋转通过独立地控制每个上转子和每个下转子的转速，飞机 可以通过改变上转子和下转子的相对旋转速度，使其上升，下降，向前移动，向后移动，向右偏转和向左偏转。

公开(公告)号：US20100021288A1

公开(公告)日：2010-01-28

申请号：US12178242

申请日：2008-07-23

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: F01D25/12

CPC classification number: B64D13/006 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64D2013/0614 ,  Y02T50/56

Abstract: Electronic equipment frequently requires cooling to maintain the integrity and reliability of the equipment, and to elongate the life expectancy of the equipment. When in operation, the fan of a UAV creates airflow comprising outside air directed across the duct of the UAV. Utilizing this airflow generated by the fan of a UAV to provide heat transfer from a equipment enclosure accomplishes efficient heat transfer. The methods described herein for transferring heat from an equipment enclosure using an airflow generated by a fan of a UAV may be employed for UAVs having a variety of duct shapes, and having equipment enclosures inside the duct or in detachable equipment enclosures located on the duct of the UAV.

Abstract translation: 电子设备经常需要冷却以保持设备的完整性和可靠性，并延长设备的预期寿命。 当操作时，无人机的风扇产生气流，其包括被引导穿过无人机的管道的外部空气。 利用由无人机的风扇产生的这种气流来提供来自设备外壳的热量传递，从而实现有效的热传递。 本文所述的用于使用由UAV的风扇产生的气流从设备外壳传递热量的方法可以用于具有各种管道形状的UAV，并且在管道内部或在位于管道上的可拆卸设备外壳中具有设备外壳 无人机。

公开(公告)号：US20090314882A1

公开(公告)日：2009-12-24

申请号：US11492490

申请日：2006-07-25

Applicant: Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

Inventor： Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

IPC: B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械起动组件和发射台。 优选实施例包括容器和容器盖，其中MAV夹在盖上。 还设置在容器盖上的是起动组件。 将附加的MAV作为发射台的盖子从容器中取出，放在地面上，MAV以起动机构启动并启动。 这种布置可最大限度地减少操作人员的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的电源线的依赖。

公开(公告)号：US07631834B1

公开(公告)日：2009-12-15

申请号：US11737591

申请日：2007-04-19

Applicant: Samuel Alan Johnson ,  William Dennis Burkard ,  Robert H. Mimlitch, III ,  Robert Henry Mimlitch, Jr. ,  David Anthony Norman

Inventor： Samuel Alan Johnson ,  William Dennis Burkard ,  Robert H. Mimlitch, III ,  Robert Henry Mimlitch, Jr. ,  David Anthony Norman

IPC: B64C27/08 ,  B64C29/00 ,  B64C39/00 ,  B64C27/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/148

Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.

Abstract translation: 本公开涉及分配用于支持这种空中机器人的导电细丝或系统，方法和软件的空中机器人。 一个远程供电的空中机器人系统包括空中机器人和电源。 空中机器人包括主体，第一螺旋桨，其联接到主体并且可操作以向空中机器人提供推力，联接到主体的可旋转的卷轴，以及通过卷轴的旋转从卷轴分配的导电细丝是一个方向 并通过在另一方向上的线轴的旋转来取回。 电源通过导电细丝与天线机器人耦合并远离，其中导电细丝可操作以使用来自电源的功率为第一螺旋桨供电。