公开(公告)号：US20120267472A1

公开(公告)日：2012-10-25

申请号：US13376446

申请日：2010-06-02

Applicant: Arie Pratzovnick ,  Shmuel Ron

Inventor： Arie Pratzovnick ,  Shmuel Ron

IPC: H01Q1/28 ,  G06F17/50 ,  B64C39/02 ,  G01S1/04 ,  B64C3/00 ,  B64C1/00

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

Abstract: A sensor/emitter arrangement (M1-M3) is integrated into the fuselage (120) structure of a specially designed air vehicle (100), in which the air vehicle is configured for optimizing operation of the sensor/emitter arrangement (M1-M3) with respect to at least azimuthal lines of sight radiating along a azimuthal reference plane of the air vehicle (100). The azimuthal reference plane intersects the air vehicle fuselage (120). In at least some embodiments, the fuselage (120) is formed with a plurality of oblate cross-sections that facilitate maximizing the room available for a sensor/emitter array (172, 174, 176) that is elongated along an elongate axis that may be aligned with the azimuthal reference plane. In at least some embodiments one or more such elongate axes may be inclines to the longitudinal (roll) axis and the pitch axis of the air vehicle (100). In at least some embodiments, the air vehicle may have a blunt aft end incorporating an elongate aft-facing sensor/emitter array (172, 174, 176).

Abstract translation: 传感器/发射器装置（M1-M3）集成在专门设计的空中飞行器（100）的机身（120）结构中，其中，空中飞行器配置成优化传感器/发射器装置（M1-M3）的操作， 相对于沿着所述空中交通工具（100）的方位角参考平面辐射的至少方位视线。 方位角参考平面与机动车辆机身（120）相交。 在至少一些实施例中，机身（120）形成有多个扁平横截面，其有助于最大化可用于沿着细长轴线延伸的传感器/发射器阵列（172,174,176）的房间，该细长轴线可以是 与方位角参考平面对齐。 在至少一些实施例中，一个或多个这样的细长轴线可以倾斜到空中车辆（100）的纵向（滚动）轴线和俯仰轴线。 在至少一些实施例中，空中交通工具可以具有并入一个延伸的面向后面的传感器/发射器阵列（172,174,176）的平头后端。

公开(公告)号：US20120199698A1

公开(公告)日：2012-08-09

申请号：US13226179

申请日：2011-09-06

Applicant: Peter Geoffrey THOMASSON ,  Robert Idris JONES ,  David Ian Alistair POLL

Inventor： Peter Geoffrey THOMASSON ,  Robert Idris JONES ,  David Ian Alistair POLL

IPC: G05D1/00 ,  G08G5/04 ,  B64C13/16

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0094 ,  G05D1/0825

Abstract: A gust-insensitive unmanned air vehicle (UAV) for imaging the ground, comprising a substantially neutrally stable air frame having a fuselage and at least three wings which include control surfaces. The wings are arranged in symmetrical relation about the fuselage and confer the UAV with a roll stability about a longitudinal axis of the fuselage for any roll angle. The UAV also includes a propulsion device for propelling the UAV in flight, an image sensor for imaging the ground, and a flight control system for controlling the in-flight operation of the UAV. The flight control system includes flight control sensors and is operative to render the UAV gust insensitive in response to inputs from the flight control sensors.

Abstract translation: 一种用于对地面进行成像的阵风不敏感的无人驾驶飞行器（UAV），其包括具有机身的基本中性稳定的空气框架和包括控制表面的至少三个机翼。 机翼围绕机身以对称关系布置，并赋予无人机以任何滚动角度的关于机身的纵向轴线的滚动稳定性。 无人机还包括用于在飞行中推进无人机的推进装置，用于对地面进行成像的图像传感器以及用于控制无人机的飞行操作的飞行控制系统。 飞行控制系统包括飞行控制传感器，并且可操作以响应于来自飞行控制传感器的输入而使UAV阵风不敏感。

公开(公告)号：US20100308161A1

公开(公告)日：2010-12-09

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

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.

公开(公告)号：US20100140389A1

公开(公告)日：2010-06-10

申请号：US12627104

申请日：2009-11-30

Applicant: Gerald Gleed ,  Dean Alders

Inventor： Gerald Gleed ,  Dean Alders

IPC: B64C1/00

CPC classification number: B64C3/38 ,  B64C3/40 ,  B64C39/024 ,  B64C39/066 ,  B64C2201/028 ,  B64C2211/00 ,  B64D27/02

Abstract: An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.

Abstract translation: 一种空气车辆，其仅包括一个薄且基本上平坦的翼，翼是细长的并且优选地是菱形的，以及可拆卸地联接到翼的舱，用于围绕垂直于翼的主表面的轴线相对旋转， 支持飞行器的推进器。 推进器可以是具有用于静电提升的卡斯特风管的螺旋桨。

公开(公告)号：US07487937B2

公开(公告)日：2009-02-10

申请号：US11394018

申请日：2006-03-30

Applicant: Peter G. Ifju ,  Bret K. Stanford ,  Roberto Albertani

Inventor： Peter G. Ifju ,  Bret K. Stanford ,  Roberto Albertani

IPC: B64C3/38 ,  B64C3/52 ,  B64C1/26 ,  B64C31/028

CPC classification number: B64C3/18 ,  B64C3/42 ,  B64C3/44 ,  B64C3/52 ,  B64C39/028 ,  B64C2201/028 ,  Y02T50/14

Abstract: An airfoil for a micro air vehicle that includes components enabling the airfoil to adjust the angle of attack (AOA) of the airfoil in response to wind gusts, thereby enabling the airfoil to provide smooth flight. The airfoil may include a first compliant region positioned between an inboard section and a first outboard section and may include a second compliant region between a second outboard section and the inboard section. The compliant regions enable the first and second outboard sections to bend about a leading edge section and move relative to an inboard section. This action creates smoother flight due to numerous aerodynamic advantages such as a change in the angle of attack and improved wind gust rejection due to adaptive washout as a result of the airfoil flexing, twisting and decambering.

Abstract translation: 一种用于微型飞行器的翼型件，其包括能够使翼型件响应于阵风而调节翼型的迎角（AOA）的部件，从而使翼型件能够提供平稳的飞行。 翼型件可以包括位于内侧部分和第一外侧部分之间的第一顺应性区域，并且可以包括第二外侧部分和内侧部分之间的第二顺应区域。 顺从区域使得第一和第二外侧部分能够围绕前缘部分弯曲并且相对于内侧部分移动。 由于翼型的弯曲，扭转和回旋的结果，由于许多空气动力学优点，例如迎角的变化和改善的阵风排除，由于适应性冲洗，这种动作产生更平滑的飞行。

公开(公告)号：US20090014596A1

公开(公告)日：2009-01-15

申请号：US12058466

申请日：2008-03-28

Applicant: Jerome Pearson ,  Gerald M. Gregorek ,  Harry B. Wykes

Inventor： Jerome Pearson ,  Gerald M. Gregorek ,  Harry B. Wykes

IPC: B64C3/50 ,  B64C3/38

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

Abstract: A long endurance powered aircraft includes a central spar, a propeller coupled to the central spar, and a wing coupled to the central spar. The wing includes a first spar and an opposing second spar. Leading ends of the first and second spars are coupled to the central spar and trailing ends of the first and second spars selectively diverge from the central spar to define a morphing wing configured change shape to optimize aircraft flight parameters in response to changes in at least one flight condition.

Abstract translation: 长寿命的动力飞机包括一个中心翼梁，一个连接到中央翼梁的螺旋桨，以及一个与中心翼梁连接的翼。 翼包括第一翼梁和相对的第二翼梁。 第一和第二翼梁的前端连接到第一和第二翼梁的中心翼梁和后端，从中心翼梁选择性地分离，以限定变形翼构造的变形形状，以响应于至少一个 飞行情况。

公开(公告)号：US20070252034A1

公开(公告)日：2007-11-01

申请号：US11603815

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：US07281681B2

公开(公告)日：2007-10-16

申请号：US10600258

申请日：2003-06-20

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

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

IPC: 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. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

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。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：US20050178885A1

公开(公告)日：2005-08-18

申请号：US10758294

申请日：2004-01-15

Applicant: Clifford Jackson

Inventor： Clifford Jackson

IPC: B64C3/56 ,  B64C7/00 ,  B64C13/20 ,  B64C39/02

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：US06931247B2

公开(公告)日：2005-08-16

申请号：US09789450

申请日：2001-02-20

Applicant: Earl C. Cox ,  Kyle D. Swanson

Inventor： Earl C. Cox ,  Kyle D. Swanson

IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  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 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

Abstract translation: 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。