公开(公告)号：US20100019098A1

公开(公告)日：2010-01-28

申请号：US12179690

申请日：2008-07-25

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。

公开(公告)号：US07575192B1

公开(公告)日：2009-08-18

申请号：US11305711

申请日：2005-12-16

Applicant: Jules G. Kish

Inventor： Jules G. Kish

IPC: B64D35/00

CPC classification number: B64D35/00 ,  B64C27/12 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/165 ,  F02C6/206 ,  F02C7/36 ,  F05D2250/82 ,  F16H1/22 ,  Y02T50/671

Abstract: A transmission system for use with a microturbine engine that includes an input shaft operably coupled to the output shaft of the microturbine engine. The output shaft of the microturbine engine and the input shaft of the transmission system operate at a rotational speed in a range between 50,000 and 250,000 RPM with an output power between 200 and 5 HP. The transmission system includes a gear train having a first gear that interfaces to a second gear, the first and second gears employing teeth with opposite handed helix-angled surfaces that apply axial forces to the input shaft during both normal operation and start-up operations, which pushes the input shaft toward the output shaft of the microturbine engine. Preferably, the helix-angled surfaces on respective normal drive sides of the teeth produce an axial force during normal operation that will not be overcome with the axial force produced by the mass time acceleration of the first gear. The gear train interfaces to a starter-generator preferably through the second gear. The gear train preferably provides a reduction ratio having a value greater than 24.

Abstract translation: 一种与微型涡轮发动机一起使用的传动系统，其包括可操作地联接到微型涡轮发动机的输出轴的输入轴。 微型涡轮发动机的输出轴和变速器系统的输入轴在50,000和250,000 RPM之间的转速下运行，输出功率在200和5 HP之间。 传动系统包括齿轮系，该齿轮系具有与第二齿轮相接合的第一齿轮，第一和第二齿轮采用具有相反的双螺旋角倾斜表面的齿，在正常操作和启动操作过程中将轴向力施加到输入轴， 其将输入轴推向微型涡轮发动机的输出轴。 优选地，齿的相应正常驱动侧上的螺旋角度表面在正常操作期间产生轴向力，这将不会被第一档的质量时间加速度产生的轴向力所克服。 齿轮系优选地通过第二齿轮与起动器发电机接口。 齿轮系优选地提供具有大于24的值的减速比。

公开(公告)号：US07270296B2

公开(公告)日：2007-09-18

申请号：US10756024

申请日：2004-01-12

Applicant: J. William Box ,  Jules G. Kish

Inventor： J. William Box ,  Jules G. Kish

IPC: 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 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。传动系统的尺寸最小，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：US07261257B2

公开(公告)日：2007-08-28

申请号：US10996799

申请日：2004-11-23

Applicant: Elie Helou, Jr.

Inventor： Elie Helou, Jr.

IPC: B64C1/22

CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

公开(公告)号：US20070023582A1

公开(公告)日：2007-02-01

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel Steele ,  Joseph Chovan

Inventor： Daniel Steele ,  Joseph Chovan

IPC: B64C13/20

CPC classification number: B64D7/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165

Abstract: A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.

Abstract translation: 一种小型，可重复使用的拦截无人机（UAV），无人机的航空电子控制系统，无人机的设计方法和无人机的控制方法，阻止小规模空中，水和地面威胁。 无人机包括具有集成武器和航空电子平台的高性能机身。 无人机的设计首先涉及选择合适的武器，然后设计拦截机体，以通过机身操纵实现武器瞄准。 无人机使用以车辆为中心的航空电子控制系统，因此提供了对UAV的高度自主控制。 情境感知处理器可以访问一套不同的传感器，可以智能地（自主地）执行各种任务场景。 与情境感知处理器可操作地集成的飞行控制处理器包括飞行员控制器和用于飞行和操纵无人机的自动驾驶仪控制器。

公开(公告)号：US07152827B2

公开(公告)日：2006-12-26

申请号：US10759541

申请日：2004-01-16

Applicant: Brian T. McGeer

Inventor： Brian T. McGeer

IPC: B64C3/56

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.

公开(公告)号：US07114680B2

公开(公告)日：2006-10-03

申请号：US10759742

申请日：2004-01-16

Applicant: Brian D. Dennis

Inventor： Brian D. Dennis

IPC: B64F1/04

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

Abstract: Methods and apparatuses for launching and capturing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The aircraft can then be retrieved from the recovery line. The boom can be retracted when not in use to reduce the volume it occupies.

Abstract translation: 描述了用于发射和捕获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，飞行器可以从包括可扩展起重臂的装置发射。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 然后可以从回收线检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。

公开(公告)号：US07104495B2

公开(公告)日：2006-09-12

申请号：US11269395

申请日：2005-11-08

Applicant: Brian T. McGeer

Inventor： Brian T. McGeer

IPC: B64F5/00

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：US20060151667A1

公开(公告)日：2006-07-13

申请号：US10758948

申请日：2004-01-16

Applicant: Brian Dennis ,  Andreas von Flotow

Inventor： Brian Dennis ,  Andreas von Flotow

IPC: B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/06

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

Abstract translation: 描述了发射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，飞行器可以从包括可扩展起重臂的装置发射。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

公开(公告)号：US07070145B2

公开(公告)日：2006-07-04

申请号：US11042666

申请日：2005-01-24

Applicant: G. Douglas Baldwin

Inventor： G. Douglas Baldwin

IPC: B64C27/28

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Abstract translation: 公开的飞行技术包括具有第一端和第二端的悬挂结构，升降单元和有效载荷单元。 提升单元包括机舱和尾巴，并且枢转地联接到悬架结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。