公开(公告)号：US08492692B2

公开(公告)日：2013-07-23

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B12/56 ,  F42B15/01 ,  F42B15/08 ,  H04B1/59 ,  F42B15/00 ,  H04B1/00

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：US20130175390A1

公开(公告)日：2013-07-11

申请号：US13567015

申请日：2012-08-04

Applicant: Adam Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Hollman

Inventor： Adam Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Hollman

IPC: B64D27/26 ,  B64C19/00 ,  B64D9/00

CPC classification number: B64C1/30 ,  A63H27/001 ,  A63H27/02 ,  B64C15/00 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64D1/14 ,  B64D9/00 ,  B64D27/26

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract translation: 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。

公开(公告)号：US08314374B2

公开(公告)日：2012-11-20

申请号：US11455709

申请日：2006-06-20

Applicant: Burak Uzman

Inventor： Burak Uzman

IPC: F41G7/20 ,  F41G7/24 ,  F41G7/30

CPC classification number: F42B12/365 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  F41G7/30 ,  F42B15/01 ,  F42B15/10 ,  G05D1/0038

Abstract: A lightweight, man-portable weapon delivery system includes a fuselage, and first and second wings mounted to opposing sides of the fuselage. The system includes an electric motor for driving a propeller for providing thrust to propel the system. The electric motor is mounted to the fuselage, and configured to be remotely started by a user. The system includes an imaging device mounted to the system and configured to capture images of a theater of operations of the system. The system includes a communication circuit in communication with the imaging device and configured to transmit the images from the imaging device to the user for viewing the theater of operations of the system for remotely steering the system. The communication circuit is configured to receive commands from the user for steering the system into the target. The system includes a payload configured to store the ordnance.

Abstract translation: 轻便的便携式武器传送系统包括机身，以及安装在机身相对两侧的第一和第二翼。 该系统包括用于驱动螺旋桨以提供推力以推动系统的电动马达。 电动机安装在机身上，并被配置为由用户远程启动。 该系统包括安装到系统并被配置为捕获系统的操作剧场的图像的成像装置。 该系统包括与成像装置通信的通信电路，并且被配置为将图像从成像装置传输到用户，以观看用于远程转向系统的系统的操作剧场。 通信电路被配置为从用户接收命令以将系统转向目标。 系统包括配置为存储军械的有效载荷。

公开(公告)号：US20120211588A1

公开(公告)日：2012-08-23

申请号：US13465220

申请日：2012-05-07

Applicant: Kevin Reed Lutke ,  Aaron J. Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron J. Kutzmann

IPC: B64D5/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/206

Abstract: Methods and systems are provided which may allow a first vehicle to recover a second air vehicle while both are moving. The first vehicle and the second air vehicle may be traveling at different velocities. An attachment member of the second air vehicle may attach to a recovery member of the first vehicle while the first vehicle and the second air vehicle are traveling at different velocities. The recovery member attached to the second air vehicle may move relative to and along an exterior surface of the first vehicle in a direction substantially parallel to a direction of travel of the first vehicle.

Abstract translation: 提供了方法和系统，其可以允许第一车辆在移动时都恢复第二空中车辆。 第一车辆和第二空中车辆可以以不同的速度行驶。 当第一车辆和第二空中车辆以不同的速度行驶时，第二空中车辆的附接构件可以附接到第一车辆的回收构件。 附接到第二空气车辆的回收构件可以在与第一车辆的行进方向基本平行的方向上相对于第一车辆的外表面移动并沿其移动。

公开(公告)号：US08226039B2

公开(公告)日：2012-07-24

申请号：US13347624

申请日：2012-01-10

Applicant: Andreas H. von Flotow ,  Tyler Patrick Horton

Inventor： Andreas H. von Flotow ,  Tyler Patrick Horton

IPC: B64C1/00

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

Abstract: Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.

公开(公告)号：US20110281679A1

公开(公告)日：2011-11-17

申请号：US12982109

申请日：2010-12-30

Applicant: Daniel Larrabee ,  Thomas Northrop Wormer ,  Matt Rhode ,  Eric Serani ,  Josh Marshman ,  Cody Humbarger ,  Daniel Gaide ,  Derek Hillery ,  Alec Velazco ,  Eric Petersen ,  Jean Nicolas Koster

Inventor： Daniel Larrabee ,  Thomas Northrop Wormer ,  Matt Rhode ,  Eric Serani ,  Josh Marshman ,  Cody Humbarger ,  Daniel Gaide ,  Derek Hillery ,  Alec Velazco ,  Eric Petersen ,  Jean Nicolas Koster

IPC: F16H3/72 ,  F16H57/08

CPC classification number: B64D35/08 ,  B60K6/365 ,  B60K6/48 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/165 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026 ,  F16H3/72 ,  Y02T10/6221 ,  Y02T50/44 ,  Y02T50/64

Abstract: Provided are alternative hybrid transmission systems for marine, or two wheeled land vehicles, as well as propulsion systems and vehicles comprising such transmission systems, to improve various propulsion systems using a combination of at least two power sources with the option for simultaneous or alternating power input from two or more power sources, while providing desired characteristics or components. Such characteristics or components can include, but are not limited to: power, torque, acceleration, cruising speed or power, fuel efficiency, battery charging, endurance, power sizing, weight, capacity, efficiency, speed, mechanically and/or electrically added system requirements, design, fuel selection, functional design, structural design, lift to drag ratio, weight, and/or other desired characteristic or component.

Abstract translation: 提供用于海洋或两轮陆地车辆的替代混合动力传动系统以及包括这种传动系统的推进系统和车辆，以改善使用至少两个动力源的组合的各种推进系统以及用于同时或交替动力输入的选项 来自两个或更多个电源，同时提供期望的特性或部件。 这些特征或组件可以包括但不限于：功率，扭矩，加速度，巡航速度或功率，燃料效率，电池充电，耐久性，功率尺寸，重量，容量，效率，速度，机械和/或电气附加系统 要求，设计，燃料选择，功能设计，结构设计，提升阻力比，重量和/或其他所需特性或部件。

公开(公告)号：US20110248123A1

公开(公告)日：2011-10-13

申请号：US13140233

申请日：2009-12-01

Applicant: Abraham Abershitz

Inventor： Abraham Abershitz

IPC: B64C39/02 ,  B64C39/10 ,  B64C5/00

CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187

Abstract: The present invention relates to an unmanned air vehicle (105), comprising a body having front (121) and rear (122) sections with at least one pair of end plates (110) connected to said body, wherein one end plate within said at least one pair of end plates is connected to the left side of said body and another end plate within said at least one pair of end plates is connected to the right side of said body, each end plate having upper and lower sections (111,112), wherein: a) said upper section is positioned above a mean line of said body; b) said lower section is positioned below said mean line of said body; and c) a ratio of the area of said upper section to the area of said lower section is less than 1.

Abstract translation: 本发明涉及一种无人驾驶飞行器（105），其包括具有前部（121）和后部（122）部分的主体，所述主体部分具有连接到所述主体的至少一对端板（110），其中，所述内部 至少一对端板连接到所述主体的左侧，并且在所述至少一对端板内的另一个端板连接到所述主体的右侧，每个端板具有上部和下部（111,112）， 其中：a）所述上部分位于所述主体的平均线之上; b）所述下部部分位于所述主体的平均线下方; 和c）所述上部区域与所述下部区域的面积之比小于1。

公开(公告)号：US08002216B2

公开(公告)日：2011-08-23

申请号：US12139402

申请日：2008-06-13

Applicant: Darwin Kent Decker

Inventor： Darwin Kent Decker

IPC: B64C13/24 ,  B64D27/24

CPC classification number: B64D27/24 ,  B64C11/305 ,  B64C17/06 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64D2211/00 ,  F02K5/00 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: A solar powered air vehicle that can stay aloft for indefinite periods of time. The vehicle employs photovoltaic solar cells for primary power and high speed counter-rotating flywheels for energy storage and steering of the vehicle. The flywheels are placed in the wing to reduce airfoil drag. A control law provides three-axis stabilized control of the vehicle by controlling propeller pitch to vary the speeds of the flywheels.

Abstract translation: 太阳能动力的空中飞行器，可以在高处保持无限期的时间。 车辆采用光伏太阳能电池用于主电力和高速反向旋转飞轮，用于车辆的储能和转向。 飞轮放置在机翼中以减少机翼拖动。 控制规则通过控制螺旋桨桨距来改变飞轮的速度来提供对车辆的三轴稳定控制。

公开(公告)号：US20110144834A1

公开(公告)日：2011-06-16

申请号：US12805434

申请日：2010-07-30

Applicant: Geoffrey S. Sommer

Inventor： Geoffrey S. Sommer

IPC: B64C37/02 ,  G05D1/00

CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

公开(公告)号：US20110001001A1

公开(公告)日：2011-01-06

申请号：US12865429

申请日：2009-02-02

Applicant: Ashley Christopher Bryant

Inventor： Ashley Christopher Bryant

IPC: B64C29/00 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A vertical take-off and landing (VTOL) flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms (56) are employed, the arms (56) of fore and aft propulsion units (52,54; 53,55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51 ; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Only one propulsion unit (21) may be mounted at each extremity and additional fan units (48,83) may be used.

Abstract translation: 垂直起降（VTOL）飞翼飞机具有一对推进矢量推进单元（2,3; 4,5），其安装在飞行器俯仰轴线（PA）的前后，位于横梁（6,7） ）在机翼结构（1）的相对两端，前部单元（2; 4）和下方的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当使用臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61）相互配合。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 每个末端只安装一个推进单元（21），并且可以使用附加的风扇单元（48,83）。