公开(公告)号：US07014141B2

公开(公告)日：2006-03-21

申请号：US10194814

申请日：2002-07-12

Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: B64C13/20 ,  B64C13/00

CPC classification number: F41G3/02 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06 ,  Y02T50/82

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

公开(公告)号：US20050226727A1

公开(公告)日：2005-10-13

申请号：US11071890

申请日：2005-03-02

Applicant: Brian Dennis ,  Kenneth Hillen

Inventor： Brian Dennis ,  Kenneth Hillen

IPC: F03D1/00

CPC classification number: B64C11/44 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

Abstract: Apparatuses and methods for controlling the motion of a propeller blade are disclosed. In one embodiment, the apparatus can include a first motor that rotates a propeller about a first axis with a first shaft. A first signal transmission portion, fixed relative to the first motor, can transmit signals to a second signal transmission portion that rotates with the first shaft. A second motor can be carried by the first shaft and can receive signals from the second signal transmission portion. The second motor can drive blades of the propeller about a second axis generally transverse to the first axis via a second shaft to vary the pitch of the blades.

Abstract translation: 公开了用于控制螺旋桨叶片运动的装置和方法。 在一个实施例中，该装置可以包括第一马达，第一马达使螺旋桨围绕第一轴线与第一轴旋转。 相对于第一电动机固定的第一信号传输部分可以将信号发送到与第一轴一起旋转的第二信号传输部分。 第二电动机可以由第一轴承载并且可以从第二信号传输部分接收信号。 第二马达可以通过第二轴驱动螺旋桨的叶片大致横过第一轴线的第二轴线，以改变叶片的桨距。

公开(公告)号：US20050218260A1

公开(公告)日：2005-10-06

申请号：US10951041

申请日：2004-09-23

Applicant: David Corder ,  Jeffrey Koessler ,  George Webb

Inventor： David Corder ,  Jeffrey Koessler ,  George Webb

IPC: B64C3/56 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/201

Abstract: An air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

Abstract translation: 一架空中飞机包括在飞行期间从机身部署的可部署的机翼，电梯和垂直翼片。 飞机可以包括用于操作电梯的控制系统，通信系统和用于为系统供电的电池。 此外，飞机可以包括与机身中的接口相配合的有效载荷模块。 有效载荷模块可以包括各种有效载荷中的任何一种，包括相机，传感器和/或雷达发射器。 该飞机可能是动力或无动力的，并且可能非常小，例如小于10kg（22磅）的量级。 飞机可以以低成本从事各种功能，例如监视或作为诱饵。 飞机的可部署表面可以被配置成以预定的顺序部署，允许飞机在以翻滚模式发射之后自动进入受控飞行。

公开(公告)号：US20050178892A1

公开(公告)日：2005-08-18

申请号：US10756024

申请日：2004-01-12

Applicant: J. Box ,  Jules Kish

Inventor： J. Box ,  Jules Kish

IPC: B64C27/14 ,  B64C39/02 ,  B64D35/02 ,  B64D35/00

CPC classification number: B64C27/14 ,  B64C39/028 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D35/02

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The 1 transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration an offset star-spur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction planetary gear configuration. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

Abstract translation: 与微型涡轮发动机结合使用的用于推进飞机机体（例如基于螺旋桨的固定翼飞行器或基于转子的垂直升降飞机）或用于各种其它应用的传动系统。 微型涡轮发动机的输出轴优选地在72,000RPM和150,000RPM之间的转速下工作，输出功率在150HP和5HP之间（最优选地在50,000RPM和200,000RPM之间的扩展范围内工作，并且输出 功率在200 HP和5 HP之间）。 两个还原阶段提供优选具有至少19的值，最优选大于24的减小率。1传输系统的尺寸最小，最好具有小于12英寸的最大直径。 传动系统的两个阶段可以包括许多构造的任何一个（或多个部分），包括一个在线的卧式结构，一个星形星形配置，一个偏移星形齿轮配置，一个偏移复合惰轮 配置，内联牵引内齿轮配置和在线牵引行星齿轮配置。 优选地，传动系统的输入级是自平衡的，使得第一轴可以被支撑而没有轴承，并且通过外径引导的花键联接机构可操作地联接到微型涡轮发动机的输出轴。 对于垂直升降应用，可以使用单个牵引台以及锥齿轮组件或其他轴传动机构来提供必要的RPM减小。

公开(公告)号：US20050151014A1

公开(公告)日：2005-07-14

申请号：US10759541

申请日：2004-01-16

Applicant: Brian McGeer

Inventor： Brian McGeer

IPC: B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64C1/00

CPC classification number: B64F1/04 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06

Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了用于发射，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞机部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：US20050082422A1

公开(公告)日：2005-04-21

申请号：US10690284

申请日：2003-10-21

Applicant: Glenn Tierney

Inventor： Glenn Tierney

IPC: B64B1/30 ,  B64C39/00 ,  B64C39/02 ,  B64C27/00

CPC classification number: B64C39/005 ,  B64B1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/165

Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

公开(公告)号：US20040245385A1

公开(公告)日：2004-12-09

申请号：US10853194

申请日：2004-05-26

Applicant: ION AMERICA CORPORATION

Inventor： James Frederick McElroy ,  K.R. Sridhar

IPC: B64D041/00

CPC classification number: H01M8/186 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/165 ,  B64D27/24 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04007 ,  H01M8/2475 ,  H01M2250/20 ,  Y02E60/528 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62 ,  Y02T90/32 ,  Y02T90/36 ,  Y10S429/901

Abstract: A neutrally buoyant airship, such as a blimp, contains a lifting body which allows the airship to remain neutrally buoyant in air and a fuel cell located in the airship. A method of generating power in the neutrally buoyant airship, comprising providing a fuel and a oxidizer to a solid oxide fuel cell to generate power, and providing heat from the fuel cell to a remotely located lifting body, wherein the lifting body allows the airship to remain neutrally buoyant in air.

Abstract translation: 一个中性浮力的飞艇，如飞艇，包含一个提升机体，允许飞艇在空气中保持中性浮力，而位于飞艇上的燃料电池。 一种在中性浮力飞艇中产生动力的方法，包括向固体氧化物燃料电池提供燃料和氧化剂以产生动力，并将热量从燃料电池提供到位于远处的提升体，其中提升体允许飞艇 在空气中保持中性浮力。

公开(公告)号：US20040232282A1

公开(公告)日：2004-11-25

申请号：US10758940

申请日：2004-01-16

Inventor： Brian D. Dennis

IPC: B64C037/00

CPC classification number: B64F1/06 ,  B63B27/26 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由飞行中的恢复线捕获，该过程可以由具有保持器的线捕获装置辅助，该保持器具有两个间隔开足够大的距离以接收恢复线，例如捕获 恢复线增加了安全性。 线捕获装置可以可操作地安装在飞行器的提升表面上。

公开(公告)号：US06726148B2

公开(公告)日：2004-04-27

申请号：US10255182

申请日：2002-09-26

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: B64F500

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F02B75/34

Abstract: A method of shipping a disassembled miniature, unmanned aircraft capable of handling data, the aircraft having remote guidance, an onboard microprocessor for managing flight, wing area of at least eight hundred square inches, a wingspan of at least eight feet, and weighing under fifty-five pounds. The aircraft includes a data handling module. The aircraft is disassembled into separate components including at a minimum the wing, the fuselage, and the data handling module. The fuselage and possibly other lesser components are packed in a first shipping container. The wing is packed in a second shipping container. The data handling module is packed in a third shipping container. The first and second containers are shipped by overnight courier, while the third container is either shipped the same way or alternatively travels as unchecked luggage aboard a commercial airliner.

Abstract translation: 运送能够处理数据的分解的微型无人飞机，具有远程引导的飞行器，用于管理飞行的机载微处理器，至少八百平方英寸的机翼面积，至少八英尺的翼展，并且重量在五十 - 英镑 飞机包括一个数据处理模块。 飞机被拆卸成单独的部件，包括至少机翼，机身和数据处理模块。 机身和可能的其他较小的部件被包装在第一运输容器中。 机翼包装在第二个运输集装箱。 数据处理模块包装在第三个运输容器中。 第一个和第二个集装箱是通过隔夜快递运送的，而第三个集装箱运输方式相同，或者作为一个商业客机上的未检查行李。

公开(公告)号：US20040031880A1

公开(公告)日：2004-02-19

申请号：US10275211

申请日：2003-08-04

Inventor： Reiner Stemme ,  Konrad Kauffmann

IPC: B64D027/00

CPC classification number: B64D27/023 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/165

Abstract: The invention relates to a propulsion system for aircraft, especially for high-flying and long-distance flying unmanned aircraft, to the aircraft itself and to a method for controlling aircraft. Said propulsion system has a first jet turbine engine and a second jet turbine engine (22, 24). The invention also provides that the first jet turbine engine is a turbine engine (22) and the second jet turbine engine is an airscrew turbine engine (24). Said airscrew turbine engine (24) remains non-operational at least during the process for starting the aircraft (10).

Abstract translation: 本发明涉及一种用于飞机的飞机推进系统，特别是用于高空飞行和长距离飞行无人飞行器的飞机本身以及用于控制飞行器的方法。 所述推进系统具有第一喷气涡轮发动机和第二喷气涡轮发动机（22,24）。 本发明还提供了第一喷气涡轮发动机是涡轮发动机（22），第二喷气涡轮发动机是涡旋式涡轮发动机（24）。 至少在起动飞行器（10）的过程中，所述螺旋桨涡轮发动机（24）保持不可操作。