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：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：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。

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。

公开(公告)号：US20030222173A1

公开(公告)日：2003-12-04

申请号：US10347157

申请日：2003-01-17

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler ,  Clifford Jackson

IPC: B64F001/12

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/104 ,  B64C2201/148 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02

Abstract: A method and an apparatus for capturing a flying object (5) are revealed. The apparatus includes a generally linear fixture (2), such as a length of rope; a means for suspending (1) the fixture (2) across the path of the flying object (5); and one or more hooks (19) on the flying object (5). The method involves suspending the fixture (2) such that its orientation includes a component normal to the flying object's line of approach; striking the fixture (2) with the flying object (5), which causes the flying object (5) to rotate and decelerate, while the fixture (2) slides along a surface of the flying object (5) into a hook (19); capturing the fixture (2) in the hook (19); and retrieving the flying object (5) from the fixture (2).

公开(公告)号：US20030066932A1

公开(公告)日：2003-04-10

申请号：US10255186

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: B64C001/00

CPC classification number: B64C39/028 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02D2200/703

Abstract: A miniature, unmanned aircraft having interchangeable data handling modules, such as sensors for obtaining digital aerial imagery and other data, and radio transmitters and receivers for relaying data. The aircraft has a microprocessor for managing flight, remote control guidance system, and electrical supply system. The data handling modules have an aerodynamic housing and manual fasteners enabling ready installation and removal. One or more data acquiring sensors or data transferring apparatus and support equipment such as batteries and communications and power cables are contained within the module. A plurality of different modules are preferably provided. Each module, when attached in a preferred location below the wing, does not significantly alter the center of gravity of the airframe. Preferably, each module contains the supervisory microprocessor so that the microprocessor need not be part of the airframe.

Abstract translation: 具有可互换数据处理模块的微型无人飞机，例如用于获得数字航空图像和其他数据的传感器，以及用于中继数据的无线电发射机和接收机。 飞机有一个用于管理飞行，遥控引导系统和电力供应系统的微处理器。 数据处理模块具有空气动力学外壳和手动紧固件，可以实现安装和拆卸。 模块内包含一个或多个数据采集传感器或数据传输设备以及诸如电池和通信和电力电缆的支持设备。 优选地提供多个不同的模块。 当每个模块安装在机翼下方的首选位置时，不会显着改变机身的重心。 优选地，每个模块包含管理微处理器，使得微处理器不需要是机身的一部分。

公开(公告)号：US20030060944A1

公开(公告)日：2003-03-27

申请号：US10255187

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: G06F017/00

CPC classification number: F02D41/2406 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  F02B75/34 ,  F02D35/0069 ,  F02D2200/0414 ,  F02D2200/703 ,  F02D2400/06 ,  F02D2400/11 ,  G05D1/101

Abstract: A power and communications connection arrangement for a miniature, unmanned aircraft having data handling capability. The aircraft has a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The latter may be any of a sensor for gathering environmental data, sensing aircraft altitude or attitude, a data relay station, or any combination of these. The data handling apparatus is part of a removable module mounted to and detachable from the aircraft. The connection arrangement includes stationary power and communications terminals fixed to the module, and corresponding free power and data cables completing respective power circuits and communications links within the aircraft. In the preferred embodiment, the microprocessor, at least one sensor, and a battery pack are located in the module, and a radio transceiver, a GPS receiver, controls such as rudder and elevator, and other sensors are located in the airframe.

公开(公告)号：US20030057325A1

公开(公告)日：2003-03-27

申请号：US10255182

申请日：2002-09-26

Inventor： Ernest A. Carroll

IPC: B64C001/00

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：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。