公开(公告)号：US20100012790A1

公开(公告)日：2010-01-21

申请号：US12426162

申请日：2009-04-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/04

CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract translation: 一架垂直起降（VTOL）的空中客车。 机动车可以载人或无人驾驶。 在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。 陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。 在一个实施例中，机身固定地附接到被覆盖的螺旋桨。 在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

公开(公告)号：US07542828B2

公开(公告)日：2009-06-02

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel W. Steele ,  Joseph R. Chovan

Inventor： Daniel W. Steele ,  Joseph R. Chovan

IPC: G01C23/00 ,  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：US20090026314A1

公开(公告)日：2009-01-29

申请号：US11782850

申请日：2007-07-25

Applicant: ELIE HELOU, JR.

Inventor： ELIE HELOU, JR.

IPC: B64C1/20 ,  B64C1/00

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：US07481396B2

公开(公告)日：2009-01-27

申请号：US11398375

申请日：2006-06-14

Applicant: Jules G. Kish

Inventor： Jules G. Kish

IPC: B64C35/00

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（或部分）构造，包括在线卧轴构造，直列星星构造，偏移星形支路构造，偏移化合物 惰轮构造，在线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：US07357352B2

公开(公告)日：2008-04-15

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas E. Speer ,  Richard D. Jones

Inventor： Thomas E. Speer ,  Richard D. Jones

IPC: B64C37/02 ,  B64D5/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20070108345A1

公开(公告)日：2007-05-17

申请号：US11510920

申请日：2006-08-28

Applicant: William McDonnell

Inventor： William McDonnell

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract translation: 一种发射和检索无人机（无人机）的方法（10）。 优选的发射方法是将无人机（10）运送到高度，使用类似于用来搭载高层游客的伞（8）。 无人机被丢弃，并在潜水中获得足够的空速，执行上升到等级控制飞行。 回收的首选方法是使UAV飞入并锁定在悬挂拖线（4）上或悬挂在拖绳上的电缆，然后被绞盘回到船（2）。

公开(公告)号：US20070102565A1

公开(公告)日：2007-05-10

申请号：US11270342

申请日：2005-11-09

Applicant: Thomas Speer ,  Richard Jones

Inventor： Thomas Speer ,  Richard Jones

IPC: B64C29/00 ,  B64C37/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

公开(公告)号：US20070075185A1

公开(公告)日：2007-04-05

申请号：US11603810

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

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 a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

公开(公告)号：US07182297B2

公开(公告)日：2007-02-27

申请号：US10758294

申请日：2004-01-15

Applicant: Clifford Jackson

Inventor： Clifford Jackson

IPC: B64C13/28

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165

Abstract: Methods and apparatuses for supporting aircraft components, including actuators are disclosed. An apparatus in accordance with one embodiment of the invention includes an actuator housing having an actuator receptacle that securely yet releasably receives an actuator. The actuator receptacle can include conformal walls that conform at least in part to the shape of the actuator and can accordingly squeeze the actuator and properly align the actuator. At least one of the actuator walls can further include a projection that is releasably received in a corresponding recess of the actuator. One of both of these features can releasably secure the actuator relative to the aircraft, reducing and/or eliminating the likelihood that the actuator will be misaligned and/or mispositioned relative to the aircraft during installation and/or replacement.

Abstract translation: 公开了用于支持飞机部件（包括致动器）的方法和装置。 根据本发明的一个实施例的装置包括具有可靠地可释放地接收致动器的致动器插座的致动器壳体。 致动器容器可以包括至少部分地符合致动器的形状的适形壁，并且可以相应地挤压致动器并且正确对准致动器。 致动器壁中的至少一个还可以包括可释放地容纳在致动器的相应凹部中的突起。 这两个特征之一可以相对于飞行器可释放地固定致动器，减少和/或消除在安装和/或更换期间致动器相对于飞行器不对准和/或错位的可能性。

公开(公告)号：US07021586B2

公开(公告)日：2006-04-04

申请号：US10782253

申请日：2004-02-19

Applicant: John G. Bolling

Inventor： John G. Bolling

IPC: B64C1/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft is responsive to sensed forces acting on a refueling receptacle of the aircraft by a separate refueling probe, to control movements of the aircraft as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft with the refueling probe.

Abstract translation: 用于无人驾驶飞机的飞行中加油系统响应于通过单独的加油探针作用在飞机的加油容器上的感测力，以控制飞机在被加油时的运动，以减小感测力的大小，从而 保持飞机与加油探头的耦合。