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51. 发明授权

US07699267B2 Cargo aircraft 有权
标题翻译：货机
公开(公告)号：US07699267B2
公开(公告)日：2010-04-20
申请号：US11782850
申请日：2007-07-25
申请人： Elie Helou, Jr.
发明人： Elie Helou, Jr.
IPC分类号： B64C1/22
CPC分类号： 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
摘要： 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.
摘要翻译：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。

52. 发明申请

US20090026309A1 Aircraft 审中-公开
标题翻译：飞机
公开(公告)号：US20090026309A1
公开(公告)日：2009-01-29
申请号：US12056463
申请日：2008-03-27
申请人： Michael SCHWARZ
发明人： Michael SCHWARZ
IPC分类号： B64C1/00
CPC分类号： B64D27/20 , B64C39/024 , B64C2201/021 , B64C2201/048
摘要： The invention relates to an aircraft having a first propulsion unit with an air inlet above the fuselage of the aircraft and a second propulsion unit with an air inlet below the fuselage of the aircraft, the fuselage of the aircraft having recesses for receiving the propulsion units which are arranged such that the first and the second propulsion unit are arranged above one another in the plane set by the longitudinal and vertical axis of the aircraft. The propulsion unit comprises an engine, a housing having an air inlet, devices for the releasable fastening of the propulsion unit to the fuselage of the aircraft as well as devices for establishing a releasable connection of electric supply and data lines as well as fuel lines between the propulsion unit and the fuselage of an aircraft.
摘要翻译：本发明涉及一种具有第一推进单元的飞机，该第一推进单元具有在飞行器的机身上方的空气入口，以及具有在飞行器的机身下方具有空气入口的第二推进单元，飞行器的机身具有用于接收推进单元的凹部被布置成使得第一和第二推进单元在由飞行器的纵向和纵向轴线设置的平面中彼此上下布置。推进单元包括发动机，具有空气入口的壳体，用于将推进单元可释放地紧固到飞行器的机身的装置以及用于建立电力供应和数据线的可释放连接的装置以及在推进单元和机身的机身。

53. 发明申请

US20060231675A1 Gyro-stabilized air vehicle 有权
公开(公告)号：US20060231675A1
公开(公告)日：2006-10-19
申请号：US11384167
申请日：2006-03-17
申请人： Nicolae Bostan
发明人： Nicolae Bostan
IPC分类号： B64C29/00
CPC分类号： 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
摘要： 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.

54. 发明申请

US20060214051A1 REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT 有权
标题翻译：减少可视性转轮和控制可视性转轮的飞行方法
公开(公告)号：US20060214051A1
公开(公告)日：2006-09-28
申请号：US11189623
申请日：2005-07-26
申请人： Michael Dammar
发明人： Michael Dammar
IPC分类号： B64C27/22
CPC分类号： B64C39/00 , B64C27/00 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/046 , B64C2201/048 , B64C2201/104 , B64C2201/108 , B64C2201/123 , B64C2201/127 , B64C2201/146 , B64C2201/22
摘要： A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.
摘要翻译：旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

55. 发明授权

US07097136B2 Immersible unmanned air vehicle and system for launch, recovery, and re-launch at sea 失效
标题翻译：潜艇无人机和发射，恢复和重新发射的系统
公开(公告)号：US07097136B2
公开(公告)日：2006-08-29
申请号：US10823434
申请日：2004-04-13
申请人： Robert A. Ruszkowski, Jr.
发明人： Robert A. Ruszkowski, Jr.
IPC分类号： B64C35/00
CPC分类号： B64C1/062 , B63G8/28 , B63G8/30 , B63G13/00 , B64C35/00 , B64C37/00 , B64C39/024 , B64C2001/0045 , B64C2201/048 , B64C2201/084 , B64C2201/121 , B64C2201/127 , B64C2201/141 , B64C2201/205 , F41F3/07 , F42B15/20
摘要： A sea-launched and recovered unmanned aircraft is disclosed. The aircraft is jet-powered and has features and systems to maintain watertight integrity such that it may be released from a submerged submarine or dropped into a body of water by a ship or an aircraft. The aircraft is buoyant and remains at or near the water surface before its rockets are ignited. The rockets propel the air vehicle out of the sea and accelerate it to flying speed at which time a jet engine is started and the rockets are jettisoned. The air vehicle performs its mission independently or in conjunction with other ones of the air vehicles. The air vehicle then returns to an assigned splashdown point at sea via, for example, an engine-off “whip-stall” maneuver. A submarine or ship may retrieve the air vehicle and readies it for another mission.
摘要翻译：披露了一架海上发射和回收的无人机。飞机是喷气式动力的，并具有保持水密完整性的特征和系统，使得其可以从潜水艇释放或由船或飞机落入水体。这架飞机是浮力的，并且在其火箭点火之前保持在水面或附近。火箭将空中车辆推出海面，并将其加速到飞行速度，此时起飞喷气发动机，火箭被抛弃。机动车辆独立地或与其他机动车辆一起执行任务。然后，空中飞行器通过例如发动机关闭“鞭炮”操纵返回到海上指定的飞溅点。潜艇或船只可以检索空中飞行器并准备进行另一个飞行任务。

56. 发明授权

US07090166B2 Methods and apparatuses for launching unmanned aircraft, including methods and apparatuses for transmitting forces to the aircraft during launch 有权
标题翻译：用于发射无人机的方法和装置，包括在发射期间向飞机传递力的方法和装置
公开(公告)号：US07090166B2
公开(公告)日：2006-08-15
申请号：US10758948
申请日：2004-01-16
申请人： Brian D. Dennis , Andreas H. von Flotow
发明人： Brian D. Dennis , Andreas H. von Flotow
IPC分类号： B64F1/06
CPC分类号： B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/102 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64C2201/201 , B64F1/06
摘要： 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.
摘要翻译：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。

57. 发明授权

US07059931B2 Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft 失效
公开(公告)号：US07059931B2
公开(公告)日：2006-06-13
申请号：US10855275
申请日：2004-05-26
申请人： Michael A. Dammar
发明人： Michael A. Dammar
IPC分类号： A63H27/00
CPC分类号： B64C39/00 , B64C27/00 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/046 , B64C2201/048 , B64C2201/104 , B64C2201/108 , B64C2201/123 , B64C2201/127 , B64C2201/146 , B64C2201/22
摘要： A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

58. 发明授权

US07059564B2 Methods and apparatuses for capturing and recovering unmanned aircraft, including a cleat for capturing aircraft on a line 有权
标题翻译：用于捕获和恢复无人机的方法和装置，包括用于在线上捕获飞机的防滑板
公开(公告)号：US07059564B2
公开(公告)日：2006-06-13
申请号：US10758940
申请日：2004-01-16
申请人： Brian D. Dennis
发明人： Brian D. Dennis
IPC分类号： B64F1/02
CPC分类号： 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
摘要： 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.
摘要翻译：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。

59. 发明申请

US20060032971A1 TAILBOOM-STABILIZED VTOL AIRCRAFT 失效
标题翻译： TAILBOOM稳定的垂直起降飞机
公开(公告)号：US20060032971A1
公开(公告)日：2006-02-16
申请号：US11042666
申请日：2005-01-24
申请人： G. Baldwin
发明人： G. Baldwin
IPC分类号： B64C27/22
CPC分类号： B64C29/02 , B64C29/0033 , B64C39/024 , B64C2201/021 , B64C2201/024 , B64C2201/048 , B64C2201/104 , B64C2201/108 , B64C2201/128 , B64C2201/165
摘要： 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.
摘要翻译：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。

60. 发明申请

US20050230536A1 METHODS AND APPARATUSES FOR CAPTURING AND STORING UNMANNED AIRCRAFT, INCLUDING METHODS AND APPARATUSES FOR SECURING THE AIRCRAFT AFTER CAPTURE 有权
标题翻译：用于捕获和存储未经规定的飞机的方法和装置，包括用于在捕获之后保护飞机的方法和装置
公开(公告)号：US20050230536A1
公开(公告)日：2005-10-20
申请号：US10758943
申请日：2004-01-16
申请人： Brian Dennis , Clifford Jackson , Brian McGeer
发明人： Brian Dennis , Clifford Jackson , Brian McGeer
IPC分类号： B64C39/02 , B64F1/02 , B64F1/06
CPC分类号： B64C39/024 , B64C2201/042 , B64C2201/044 , B64C2201/048 , B64C2201/084 , B64C2201/102 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64C2201/201 , B64C2201/205 , B64F1/06
摘要： Methods and apparatuses for capturing, recovering, disassembling, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the boom can be extended to deploy a recovery line to capture the aircraft in flight, a process that can be aided by a line capture device having retainers in accordance with further aspects of the invention. The aircraft can then be returned to its launch platform, disassembled, and stored, again with little or no direct manual contact between the operator and the aircraft, for example, by capturing a first wing of the aircraft and securing a second wing before releasing the first.
摘要翻译：描述了用于捕获，恢复，拆卸和存储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，吊杆可以被延伸以部署回收线以在飞行中捕获飞行器，这是根据本发明的其它方面能够由具有保持器的线捕获装置辅助的过程。然后，飞机然后可以返回到其发射平台，拆卸和存储，再次与操作者和飞机之间的很少或没有直接的手动接触，例如通过捕获飞行器的第一翼并且在释放之前固定第二翼第一。

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