公开(公告)号：WO2012173632A1

公开(公告)日：2012-12-20

申请号：PCT/US2011/040981

申请日：2011-06-17

Applicant: SING, Robert, L.

Inventor： SING, Robert, L.

IPC: B64F1/22 ,  B64D9/00 ,  B64F1/28 ,  B64D45/00 ,  B64C13/18

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

Abstract translation: 自维持无人机飞机运输和观察系统（5）包括一个仅用于运输（12）的喷气式无人机（10架）舰队。 无人机（10）从外围地区的独立机场运营，以降低土地成本，避免住宅和商业区域的不安。 导航使用GPS卫星（16）的指导进行自动化，飞机（10）可在起飞期间由液压弹射器（13）辅助以减少燃料有效载荷。 观察部件（18）包括能够观察船舶，船舶和其他来源的天气状况和紧急信号的传感器。 系统（5）可以包括一个大型能源生产中心和多英亩蔬菜，草药花卉生产中心（26）。 能源生产中心包括太阳能电池板（30），燃料电池（38）和电池（44）。 因此，系统（5）不需要连接到公共事业电网。

公开(公告)号：WO2009150478A1

公开(公告)日：2009-12-17

申请号：PCT/GR2009/000037

申请日：2009-06-10

Applicant: KALIVAS, Ioannis

Inventor： KALIVAS, Ioannis

IPC: B64C39/02 ,  B64D1/16 ,  A62C3/02 ,  B64C27/20

CPC classification number: B64C39/024 ,  A62C3/0207 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/108 ,  B64D1/16

Abstract: The new method used with the new aircraft for forest fire extinguishing is a concept which consists of a new means by which the new method of fire extinction, especially forested areas, will be applied and consists of an aircraft that will fly with the help of 4 turbine engines of vertical reaction and with the support of propellers it will transport to the fire front water and materials for extinguishment and due to its peculiar shape it will be able to remain close to the fire and combat it with water, with an impulsive force of large amounts of gas that exit from its turbine engines, amounts that will contain oxygen, as well as be enriched with carbon monoxide or other extinguishing material that it possesses and will lower the temperature locally with the air currents that will be produced. This construction allows small speeds, and even idling in the air, which benefits the purpose of the fire extinction and allows the aircraft to land in small areas or close to the fire without danger but also to escape immediately if the direction of the wind changes etc. It can constructed in small, medium, or large sizes.

Abstract translation: 用于森林灭火新型飞机的新方法是一种概念，其中包括采用新的灭火方法，特别是森林地区的新手段，并将由飞机在4号飞机 涡轮发动机的垂直反作用和螺旋桨的支撑，它将运输到火前的水和材料灭火，由于其特殊的形状，它将能够保持靠近火并用水冲击，具有冲击力 大量从其涡轮发动机排出的气体，将含有氧的量，以及富含一氧化碳或其拥有的其它灭火材料，并且将随着将产生的气流局部降低温度。 这种结构允许小的速度，甚至在空中空转，这有利于灭绝的目的，并允许飞机在没有危险的情况下在小区域或靠近火的地方降落，但是如果风的方向改变等等也立即逃离 它可以以小，中或大尺寸构造。

公开(公告)号：WO2006083368A3

公开(公告)日：2007-06-14

申请号：PCT/US2005042674

申请日：2005-11-22

Applicant: HELOU ELIE JR

Inventor： HELOU ELIE 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 ,  Y02T50/433

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位于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：WO2006083368A2

公开(公告)日：2006-08-10

申请号：PCT/US2005/042674

申请日：2005-11-22

Applicant: HELOU, Elie, Jr.

Inventor： HELOU, Elie, Jr.

IPC: B64D9/00

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位于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：WO2005014390A3

公开(公告)日：2006-03-23

申请号：PCT/US2004001033

申请日：2004-01-17

Applicant: INSITU GROUP ,  DENNIS BRYAN D ,  JACKSON CLIFFORD ,  MCGEER BRIAN T ,  ROESELER CORY ,  VONFLOTOW ANDREAS H

Inventor： DENNIS BRYAN D ,  JACKSON CLIFFORD ,  MCGEER BRIAN T ,  ROESELER CORY ,  VONFLOTOW ANDREAS H

IPC: B64F1/00 ,  B63B27/10 ,  B63B27/16 ,  B63B27/26 ,  B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft (140) and other flight devices or projectiles are described. In one embodiment, the aircraft (140) can be assembled from a container (111) with little or no manual engagement by an operator. The container (111) can include a guide structure to control motion of the aircraft components. The aircraft (140) can be launched from an apparatus that includes an extendable boom (103). The boom (103) can be extended to deploy a recovery line (853) to capture the aircraft (140) in flight. The aircraft (140) can then be returned to its launch platform, disassembled, and stored in the container (111), again with little or no direct manual contact between the operator and the aircraft (140).

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储无人机（140）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（140）可以由操作者很少或没有手动接合的容器（111）组装。 容器（111）可以包括用于控制飞行器部件的运动的引导结构。 飞机（140）可以从包括可伸缩吊杆（103）的装置发射。 悬臂（103）可以延伸以部署回收线（853）以在飞行中捕获飞行器（140）。 然后，飞机（140）可以在操作员和飞行器（140）之间很少或没有直接的手动接触的情况下再次返回到其发射平台，拆卸并存储在容器（111）中。

公开(公告)号：WO2005019029A2

公开(公告)日：2005-03-03

申请号：PCT/US2004/016776

申请日：2004-05-27

Applicant: DAMMAR, Michael, A.

Inventor： DAMMAR, Michael, A.

IPC: B64D

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。 飞机可以通过固定无线电发射机进行控制，该发射机发出俯仰，滚动，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。

公开(公告)号：WO2003078246A1

公开(公告)日：2003-09-25

申请号：PCT/SG2003/000035

申请日：2003-02-19

Applicant: MICRO AUTONOMOUS SYSTEMS, LLC ,  SINGAPORE TECHNOLOGIES DYNAMICS PTE LTD ,  BARRETT, Ronald, Martin

Inventor： BARRETT, Ronald, Martin

IPC: B64C29/02

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment (12) and a lower fuselage segment (14) that extend in opposite directions from a rotor guard assembly (16). A rotor (52) rotates within the rotor guard assembly (16) between the fuselage segments(12, 14). Plural turning vanes (28) extend from the rotor guard assembly (16) beneath the rotor (52). Moreover, plural grid fins (26) extend radially from the lower fuselage segment (14) below the turning vanes (28). The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins (26).

Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件（16）沿相反方向延伸的上部机身段（12）和下部机身段（14）。 转子（52）在机身段（12,14）之间的转子保护组件（16）内旋转。 多个转动叶片（28）从转子（52）下方的转子保护组件（16）延伸。 此外，多个格栅（26）从转向叶片（28）下方的下部机身段（14）径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片（26）悬停并在水平飞行模式和垂直飞行模式之间转换。

公开(公告)号：WO00068077A1

公开(公告)日：2000-11-16

申请号：PCT/US2000/007237

申请日：2000-03-16

IPC: B64C29/02 ,  B64C39/02 ,  B64D1/08 ,  B64D1/22 ,  B64D9/00

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D1/08 ,  B64D1/22

Abstract: Apparatus for transporting a load (24) between source and destination locations, comprising an aircraft having a body (11), power plant (12) carried by the body (11) to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure (14-15) that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means (22) connected to the aircraft to elevate the load (24) from the source location, transport the elevated and air-borne load (24) generally horizontally, and set the load (24) down at the destination location, the body (11) and power plant (12) configured for vertical flight mode to elevate and set down the load (24), and for generally horizontal flight mode to transport the elevated load (24) generally horizontally below the level of the aircraft body (11).

Abstract translation: 用于在源和目的地之间运输负载（24）的设备，包括具有主体（11）的飞行器，由主体（11）承载的发电厂（12），以大致垂直地并且大致水平地驱动飞机 还具有翼片结构（14-15），其具有沿飞行方向保持的前缘; 以及连接到飞行器的负载拾取，携带和设置装置（22）以从源位置提升负载（24），大体水平地输送高空和空载负载（24），并设定负载（ 24）在目的地位置，主体（11）和配置用于垂直飞行模式的发电厂（12）升高和降低负载（24），并且为了大体上水平飞行模式通常运送升高的负载（24） 水平地低于飞机主体（11）的水平面。

公开(公告)号：WO99038769A1

公开(公告)日：1999-08-05

申请号：PCT/SE1999/000099

申请日：1999-01-25

IPC: B64C27/52 ,  B64C39/02 ,  B64C27/06 ,  B64C29/02

CPC classification number: B64C39/024 ,  B64C27/52 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165

Abstract: An unmanned rotor carried aerial vehicle comprises a propulsion unit (5) and a carrier (7) suspended from the propulsion unit. The propulsion unit (5) is connected to the carrier (7) via a cardan-like joint (9) for permitting limited tilting of the propulsion unit relative to the carrier in two orthogonal directions corresponding to the roll and pitch directions of the vehicle and for preventing relative movement between the propulsion unit and the carrier in the yaw direction of the vehicle.

Abstract translation: 无人驾驶的转子承载的飞行器包括推进单元（5）和从推进单元悬挂的载体（7）。 推进单元（5）通过万向节接头（9）连接到载体（7），用于允许推进单元相对于载体在与车辆的滚动和俯仰方向对应的两个正交方向上受到有限的倾斜，并且 用于防止在车辆的偏航方向上的推进单元和载体之间的相对运动。