公开(公告)号：WO2016055990A1

公开(公告)日：2016-04-14

申请号：PCT/IL2014/051077

申请日：2014-12-09

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： SHEPSHELOVICH, Michael ,  ABRAMOV, Danny

IPC: B64C3/14 ,  B64C3/50

CPC classification number: G05D1/0808 ,  B64C3/14 ,  B64C3/50 ,  B64C9/20 ,  B64C9/323 ,  B64C39/024 ,  B64C2201/187 ,  B64D31/06 ,  B64D45/04 ,  Y02T50/14 ,  Y02T50/32

Abstract: Methods are provided for operating an air vehicle, the air vehicle including fixed wings configured to provide mild stall characteristics including a post-stall regime, and a propulsion system capable of generating a controllable thrust, the thrust being variable at least between an idle thrust and a maximum thrust. During a landing maneuver, the air vehicle is caused to attain an angle of attack corresponding to said post-stall regime, and during the landing maneuver, there is concurrently generated a thrust level of said thrust greater than said idle thrust to provide a thrust vector having a thrust lift force component at landing. Corresponding control systems are also provided, and air vehicles including such control systems are also provided.

Abstract translation: 提供了用于操作空中飞行器的方法，所述空中飞行器包括被配置为提供包括后停止状态的温和失速特性的固定翼和能够产生可控推力的推进系统，该推力至少在空转推力和 最大推力。 在着陆操作期间，使空中飞行器达到对应于所述后失速状态的攻角，并且在着陆操作期间，同时产生所述推力的推力水平大于所述空转推力以提供推力矢量 在着陆时具有推力提升力分量。 还提供了相应的控制系统，还提供了包括这种控制系统的机动车辆。

公开(公告)号：WO2014053298A1

公开(公告)日：2014-04-10

申请号：PCT/EP2013/068994

申请日：2013-09-13

Applicant: SENSEFLY S.A.

Inventor： BEYELER, Antoine ,  KLAPTOCZ, Adam ,  ROBERTS, James F. ,  ZIMMERMANN, Loic ,  ZUFFEREY, Jean-Christophe

IPC: B64C1/26

CPC classification number: B64C1/26 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/20

Abstract: This invention relates to a connection set that is used to attach and transfer force and torque between a wing (2a, 2b), comprising a lifting surface and a control surface (9) connected together by a hinge, and the central body (1 ) of an aircraft, which contains a servo-motor (10) used for actuating said control surface (9). The wing (2a, 2b) is connected to the central body (1 ) using a connection set comprised of two components. First, an attachment mechanism (3, 4, 5, 6) is used to align the wings (2a, 2b) relative to the central body (1 ) and to transfer the aerodynamic forces acting on the wing (2a, 2b) to the central body (1 ), preventing the wing (2a, 2b) from bending at its connection point. Second, a torque coupling mechanism (7, 8) is used to actuate the control surfaces that are present on the wings using servomotors (10) that are embedded within the central body (1 ). The connection set is engaged and disengaged using a single motion and does not require additional connection of electrical cables or mechanical fixations.

Abstract translation: 本发明涉及一种用于在包括提升表面和通过铰链连接在一起的控制表面（9）的翼（2a，2b）之间附接和传递力和扭矩的连接组件，以及中心体（1） 其包含用于致动所述控制表面（9）的伺服电动机（10）。 翼（2a，2b）使用由两个部件组成的连接组件连接到中心体（1）。 首先，使用附接机构（3,4,5,6）来相对于中心体（1）对准翼（2a，2b）并将作用在机翼（2a，2b）上的空气动力传递到 中心体（1），防止机翼（2a，2b）在其连接点处弯曲。 第二，使用扭矩耦合机构（7,8）来使用嵌入在中心体（1）内的伺服电动机（10）致动存在于机翼上的控制表面。 连接组件使用单一动作进行接合和分离，不需要额外连接电缆或机械固定。

公开(公告)号：WO2014013270A1

公开(公告)日：2014-01-23

申请号：PCT/GB2013/051945

申请日：2013-07-19

Applicant: ELSON, Andrew, Charles

Inventor： DAVIDSON, Peter

IPC: B64C39/02 ,  B64D27/24

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of flying an unmanned aerial vehicle (50) at an elevated altitude comprising at least two wings (53) comprising solar-energy collectors (not shown), the method involving flying the vehicle (50) for an extended period of time with the wings (53), and therefore the solar collectors, angled towards the sun, so that the glancing angle of sunlight is greater than it would be if the vehicle (50) was flying with its wings (53) in a horizontal orientation, the vehicle (50) comprising means to reduce or eliminate the rate of change of compass bearing during flight.

Abstract translation: 一种在升高的高度上飞行无人驾驶飞行器（50）的方法，包括包括太阳能收集器（未示出）的至少两个翼部（53），所述方法包括使车辆（50）延长一段时间， 因此太阳能收集器朝向太阳倾斜，使得阳光的扫视角度大于如果车辆（50）以其水平方向与其翼（53）一起飞行的那样，则车辆（53） （50）包括用于减少或消除飞行中的罗盘方位变化率的装置。

公开(公告)号：WO2014013268A1

公开(公告)日：2014-01-23

申请号：PCT/GB2013/051942

申请日：2013-07-19

Applicant: ELSON, Andrew Charles

Inventor： ELSON, Andrew Charles

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle (10), the method comprising lifting the vehicle (10) by attachment to a lighter- than-air carrier (12) from a substantially ground-level location to an elevated altitude, wherein the vehicle (10) is prevented from entering its flight mode during ascent, causing the vehicle (10) to detach from the carrier (12) while the velocity of the vehicle (10) relative to the carrier (12) is substantially zero, the vehicle (10) thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种发射供电的无人驾驶飞行器（10）的方法，所述方法包括通过从基本上地面等级的位置附近到升高的高度的轻于空气的载体（12）来提升所述车辆（10），其中所述车辆 （10）在上升期间被阻止进入其飞行模式，使得车辆（10）相对于运载器（12）的速度基本上为零，车辆（10）从托架（12）脱离，车辆 10）此后随着其高度减小，其速度能够防止任何进一步的下降并且可以开始独立的持续飞行。

公开(公告)号：WO2014011255A2

公开(公告)日：2014-01-16

申请号：PCT/US2013034420

申请日：2013-03-28

Applicant: MORRISON CONSULTING GROUP INC W

Inventor： YATES WILLIAM M ,  USSERY ROBERT ,  YOUNG BRYON

IPC: G01C21/34 ,  B60W10/18 ,  B60W40/04 ,  B60W40/06

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/187 ,  B64D5/00 ,  B64D27/24

Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft.

Abstract translation: 电动飞机，包括飞行中可充电电动飞机，以及运行电动飞机的方法，包括通过使用独立于飞机和飞机附近飞行的无人驾驶飞行器（UAV）组件，在飞行中为电动飞机充电的方法。

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：WO2012145608A1

公开(公告)日：2012-10-26

申请号：PCT/US2012/034422

申请日：2012-04-20

Applicant: VOS, David, W. ,  JOURDAN, Damien, B.

Inventor： VOS, David, W. ,  JOURDAN, Damien, B.

IPC: G06F17/00

CPC classification number: G05D1/0676 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/187 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0056 ,  G08G5/006 ,  G08G5/0069 ,  G08G5/0086 ,  G08G5/0091 ,  G08G5/025

Abstract: A system for autonomously landing an aircraft may include a controller configured to control the aircraft, identify a landing destination for landing the aircraft, and land the aircraft at the landing destination. A computer-implemented method for autonomously landing an aircraft may include controlling the aircraft via a processor, identifying a landing destination for landing the aircraft via the processor, and landing the aircraft at the landing destination via the processor. An aircraft may include a system for autonomously landing the aircraft, the system including a controller configured to control the aircraft, identify a landing destination for landing the aircraft, and landing the aircraft at the landing destination.

Abstract translation: 用于自主着陆飞机的系统可以包括控制器，其被配置为控制飞行器，识别用于着陆飞行器的着陆目的地，并将飞机降落在着陆目的地。 用于自主着陆飞行器的计算机实现的方法可以包括经由处理器控制飞行器，识别经由处理器着陆飞行器的着陆目的地，以及经由处理器将飞机着陆在着陆目的地。 飞机可以包括用于自主着陆飞机的系统，该系统包括被配置为控制飞行器的控制器，识别用于着陆飞行器的着陆目的地，以及着陆飞机在着陆目的地。

公开(公告)号：WO2010070631A1

公开(公告)日：2010-06-24

申请号：PCT/IL2009/001128

申请日：2009-12-01

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  ABERSHITZ, Abraham

Inventor： ABERSHITZ, Abraham

IPC: B64C39/02

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：WO2006059324A1

公开(公告)日：2006-06-08

申请号：PCT/IL2005/001276

申请日：2005-11-30

Applicant: ISRAEL AIRCRAFT INDUSTRIES LTD. ,  SIRKIS, Omri

Inventor： SIRKIS, Omri

IPC: B64C9/18 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C9/18 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/201

Abstract: A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or completion of this maneuver, deep stall is induced, and the aircraft descends almost vertically to land on its upper side, thus minimizing impact loads or damage on its underside. In a particular aerodynamic arrangement configured for carrying out the method, a flap (24), which may be stowed during normal flight, is deployed in a manner such as to aerodynamically induce a negative pitching moment on the aircraft and deep stall.

Abstract translation: 提供了一种用于着陆固定翼飞机的方法，其中执行反演机动，使得飞机的背面面向地面，并且飞机的下侧面向远离地面。 在开始或完成这个机动之后，引起深度失速，飞机几乎垂直下降，降落在其上侧，从而最小化其下侧的冲击载荷或损坏。 在配置用于执行该方法的特定空气动力学配置中，可以以正常飞行中的方式存放的翼片（24）以空气动力学方式在飞行器和深度档位上引起负俯仰时刻。

公开(公告)号：WO2005084156A3

公开(公告)日：2006-02-16

申请号：PCT/US2004019746

申请日：2004-06-21

Applicant: AEROVIRONMENT INC

Inventor： MACCREADY PAUL B ,  HIBBS BART D ,  SWANSON KYLE D ,  CURTIN ROBERT F

IPC: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/02 ,  B64C39/10 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  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电力，同时以无阻碍的向下观看的方式支持通信平台。 飞机在机翼的前缘包括一个可延伸的板条，以及一个反光后缘。 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。 飞机还包括被配置为经由燃料电池提供动力的功率模块。 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。