公开(公告)号：US09120555B2

公开(公告)日：2015-09-01

申请号：US12804988

申请日：2010-08-02

Applicant: Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

Inventor： Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

IPC: B64C3/38 ,  B64C17/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  H04B7/185

CPC classification number: B64C3/38 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C17/00 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

Abstract translation: 跨度加载，高度灵活的飞翼，具有安装在延伸梁上的机翼后部的水平控制表面，以形成局部俯仰控制装置。 机翼的五个翼展翼段中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它翼段产生其自己的电梯，以最小化段间负载。 翼形二面体通过单独控制由悬臂上的控制表面组成的局部俯仰控制装置来控制，使得内侧和外侧翼段节距相对于彼此变化，因此相对的内侧和外侧升力变化。

公开(公告)号：US20150225079A1

公开(公告)日：2015-08-13

申请号：US14054080

申请日：2013-10-15

Applicant: Douglas L. Starck ,  Errica M. Starck

Inventor： Douglas L. Starck ,  Errica M. Starck

IPC: B64C29/00 ,  B64C39/10 ,  B64D27/16

CPC classification number: B64C39/10 ,  B64C29/0066 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/22 ,  B64D27/16 ,  Y02T50/12 ,  Y02T50/44

Abstract: An aircraft having a vertical take-off and landing (“VTOL”) propulsion system aircraft, smaller than a standard manned aircraft and remotely or autonomously piloted. The aircraft comprises a symmetrical airfoil shape for the center body section that consists of ribs and spars maintaining an open area in the center. Situated within the open area of the center of the aircraft resides a duct system consisting of a ducted fan and five outlet vents. The main outlet vent functions as the exhaust exiting the aft portion of the aircraft, with the remaining four ducts used for the VTOL capabilities exiting the underside of the aircraft. The aircraft can have a range of wingspan, which can be scaled to satisfy needs and requirements, with a blended wing body that incorporates the inlet and duct system.

Abstract translation: 具有垂直起飞和着陆（“VTOL”）推进系统飞机的飞机，小于标准载人飞机，远程或自主驾驶。 该飞行器包括对称的翼型形状，用于中心体部分，其由在中心保持开放区域的肋和翼梁组成。 位于飞机中心开放区域内的管道系统由管道风扇和五个出风孔组成。 主出口排气口作为离开飞机尾部的排气口，剩余的四个管道用于从飞机底面离开的垂直起降能力。 飞机可以具有一系列的翼展，其可以通过混合的翼体结合入口和管道系统而被缩放以满足需要和要求。

公开(公告)号：US08905358B2

公开(公告)日：2014-12-09

申请号：US13140233

申请日：2009-12-01

Applicant: Abraham Abershitz

Inventor： Abraham Abershitz

IPC: B64C3/58 ,  B64C39/10 ,  B64C39/00 ,  B64C39/02

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

Abstract: An unmanned air vehicle includes a body having front and rear sections with at least one pair of end plates connected to the body, wherein one end plate within the at least one pair of end plates is connected to the left side of the body and another end plate within the at least one pair of end plates is connected to the right side of the body, each end plate having upper and lower sections, wherein: a) the upper section is positioned above a mean line of the body; b) the lower section is positioned below the mean line of the body; and c) a ratio of the area of the upper section to the area of the lower section is less than 1.

Abstract translation: 一种无人驾驶飞行器包括具有连接到主体的至少一对端板的前部和后部的主体，其中至少一对端板内的一个端板连接到主体的左侧，另一端 所述至少一对端板中的板连接到所述主体的右侧，每个端板具有上部和下部，其中：a）所述上部位于所述主体的平均线之上; b）下部位于身体的平均线之下; 和c）上部区域与下部区域的面积的比率小于1。

公开(公告)号：US08827206B2

公开(公告)日：2014-09-09

申请号：US13655382

申请日：2012-10-18

Applicant: Gatewing NV

Inventor： Maarten Maurits Van Speybroeck ,  Peter Hendrik Cosyn ,  Maarten Willem Vandenbroucke

IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

CPC classification number: B64C3/187 ,  A63H27/00 ,  B64C3/20 ,  B64C3/24 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127

Abstract: A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.

Abstract translation: 适用于图像采集，监视或其他应用的无人驾驶飞机的单翼包括肋框架和泡沫，其中肋框架在模制期间被整合以获得刚度和强度。 泡沫具有用于保持电气和/或电子部件的容器。 泡沫构成冲击侧的无人驾驶飞机的外层。 机翼可以低成本和低复杂性大量生产，当在民用区域中使用时增加抗冲击性和安全性，并且是可拆卸的和一次性的，从而能够重复使用电气和/或电子部件。

公开(公告)号：US20140054423A1

公开(公告)日：2014-02-27

申请号：US13954218

申请日：2013-07-30

Applicant: Aurora Flight Sciences Corporation

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

IPC: B64D27/26 ,  B64C39/02

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.

公开(公告)号：US20130228645A1

公开(公告)日：2013-09-05

申请号：US13655382

申请日：2012-10-18

Applicant: GATEWING NV

Inventor： Maarten Maurits Van Speybroeck ,  Peter Hendrik Cosyn ,  Maarten Willem Vandenbroucke

IPC: B64C3/18

CPC classification number: B64C3/187 ,  A63H27/00 ,  B64C3/20 ,  B64C3/24 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127

Abstract: A single wing for an unmanned aircraft adapted for image acquisition, surveillance or other applications consists of a ribbed frame and a foam wherein the ribbed frame is integrated during molding for stiffness and strength. The foam has a container for holding the electric and/or electronic components. The foam constitutes the outer layer of the unmanned aircraft at impact side. The wing can be produced at low cost and low complexity in large volumes, increases the impact resistance and safety when used in civil areas, and is removable and disposable thereby enabling reuse of the electric and/or electronic components.

Abstract translation: 适用于图像采集，监视或其他应用的无人驾驶飞机的单翼包括肋框架和泡沫，其中肋框架在模制期间被整合以获得刚度和强度。 泡沫具有用于保持电气和/或电子部件的容器。 泡沫构成冲击侧的无人驾驶飞机的外层。 机翼可以低成本和低复杂性大量生产，当在民用区域中使用时增加抗冲击性和安全性，并且是可拆卸的和一次性的，从而能够重复使用电气和/或电子部件。

公开(公告)号：US08408489B2

公开(公告)日：2013-04-02

申请号：US13466327

申请日：2012-05-08

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C15/00

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.

Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。

公开(公告)号：US08308106B2

公开(公告)日：2012-11-13

申请号：US13200466

申请日：2011-09-23

Applicant: Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin

IPC: B64D27/24 ,  B64D27/00

CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。

公开(公告)号：US20110062278A1

公开(公告)日：2011-03-17

申请号：US12818826

申请日：2010-06-18

Applicant: EVAN R. ULRICH ,  DARRYLL J. PINES ,  JOSEPH PARK ,  STEVEN GERARDI

Inventor： EVAN R. ULRICH ,  DARRYLL J. PINES ,  JOSEPH PARK ,  STEVEN GERARDI

IPC: B64C3/38

CPC classification number: B64C27/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/028

Abstract: Micro/nano mono-wing aircraft with the wing configured as a winged seed (Samara) is uniquely suited for autonomous or remotely controlled operation in confined environments for surrounding images acquisition. The aircraft is capable of effective autorotation and steady hovering. The wing is flexibly connected to a fuselage via a servo-mechanism which is controlled to change the wing's orientation to control the flight trajectory and characteristics. A propeller on the fuselage rotates about the axis oriented to oppose a torque created about the longitudinal axis of the fuselage and is controlled to contribute in the aircraft maneuvers. A controller, either ON-board or OFF-board, creates input command signals to control the operation of the aircraft based on a linear control model identified as a result of extensive experimentations with a number of models.

Abstract translation: 具有配置为翼状种子（Samara）的翼的微/纳单翼飞机特别适用于围绕图像采集的有限环境中的自主或远程控制操作。 该飞机能够有效的自转和稳定的悬停。 机翼通过伺服机构灵活地连接到机身，伺服机构被控制以改变机翼的方向以控制飞行轨迹和特性。 机身上的推进器围绕轴线旋转，以抵抗围绕机身的纵向轴线产生的扭矩，并被控制以在飞机机动中作出贡献。 控制器，无论是板载还是板外，都会创建输入命令信号，以便根据多个模型的广泛实验确定的线性控制模型来控制飞机的运行。

公开(公告)号：US20110006151A1

公开(公告)日：2011-01-13

申请号：US12487907

申请日：2009-06-19

Applicant: Randal W. Beard

Inventor： Randal W. Beard

IPC: B64D3/00 ,  B64D17/00 ,  B64F1/02

CPC classification number: B64D3/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/182

Abstract: A method, apparatus, system, and computer system to facilitate aerial recovery of an air vehicle are disclosed. In various embodiments, a drogue is established in a drogue recovery orbit and an air vehicle is recovered with the drogue. Establishment of the drogue in a drogue recovery orbit may include establishment of a mothership in a mothership recovery orbit or actuating control surfaces on the drogue. Recovering the air vehicle may include maneuvering the drogue and the air vehicle in a cooperative manner to facilitate recovery of the air vehicle or utilizing a homing device on the drogue to guide the air vehicle. The various techniques disclosed may be modified to compensate for wind.

Abstract translation: 公开了一种促进空中交通工具空中恢复的方法，装置，系统和计算机系统。 在各种实施方案中，在锥套回收轨道中建立锥套，并且用锥套回收空气载体。 在潜艇恢复轨道上设置潜水员可能包括在母舰恢复轨道上建立母舰或在水手上启动控制面。 恢复飞行器车辆可以包括以合作的方式操纵锥套和空中飞行器，以便于空中交通工具的恢复，或利用锥套上的归位装置引导空中交通工具。 可以修改所公开的各种技术以补偿风。