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公开(公告)号：US20180354607A1
公开(公告)日：2018-12-13
申请号：US16042235
申请日：2018-07-23
申请人： Heka Aero LLC
发明人： Christopher Marot , Ricardo Romeu , Eric Holland
CPC分类号： B64C11/44 , B64C11/06 , B64C11/32 , B64C11/48 , B64C15/02 , B64C29/0033 , B64C2201/108 , B64C2201/162 , B64C2201/165 , F16M11/123 , F16M11/18
摘要： A fan for providing thrust including at least one blade, a hub adapted to carry the at least one blade, a hub motor adapted to rotate the hub 360 degrees about a first axis extending perpendicular to the at least one blade, a first mount adapted to carry the hub, and a first mount motor adapted to rotate the hub 360 degrees about a second axis perpendicular to the first axis and extending through the first mount first and second side securing points. The first mount may include a first mount first side securing point adapted to pivotally carry the hub, and a first mount second side securing point adapted to pivotally carry the hub.
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公开(公告)号：US20180155005A1
公开(公告)日：2018-06-07
申请号：US15706807
申请日：2017-09-18
申请人： AeroVironment, Inc.
IPC分类号： B64C3/38 , H04B7/185 , B64C17/00 , B64D31/06 , B64C39/10 , B64C15/02 , B64C3/52 , B64D27/24 , B64C39/02 , B64C3/42
CPC分类号： 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
摘要： 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.
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公开(公告)号：US20180057164A1
公开(公告)日：2018-03-01
申请号：US15425066
申请日：2017-02-06
申请人： INVENTEC APPLIANCES (PUDONG) CORPORATION , INVENTEC APPLIANCES CORP. , Inventec Appliances (Shanghai) Co. Ltd.
发明人： De-Zheng Lan , Shih-Chin Tseng , Shih-Kuang Tsai
CPC分类号： B64C39/024 , B64C15/02 , B64C2201/027 , B64C2201/042 , B64C2201/10 , B64C2201/108 , B64C2201/162 , B64D27/24 , B64D33/04 , F02K1/15 , F04D25/06 , F04D29/284 , F05D2240/90
摘要： An unmanned aerial vehicle (UAV) including a vehicle body and an airflow thruster is provided. The vehicle body has a center hub, an airflow guiding structure and an outer circumferential portion. An interior of the airflow guiding structure is interconnected between the center hub and the outer circumferential portion. The center hub has an airflow inlet. The outer circumferential portion has a plurality of lateral guiding outlets facing downward and corresponding to a gravity direction of the gravity direction of the unmanned aerial vehicle. The airflow thruster is disposed inside the center hub for generating a plurality of jet streams, such that the jet streams flow to the lateral guiding outlets through the airflow guiding structure to generate a propulsion.
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公开(公告)号：US20170361941A1
公开(公告)日：2017-12-21
申请号：US15184196
申请日：2016-06-16
发明人： Steven Louis Kiebles , David Michael Lax , Otto Y. Darias , Mark Lawrence Darnell , Sean Sanghyun Hwang , Christopher Daniel Holbert , Harry Kirk Mathews, JR. , Sridhar Adibhatla , Jeffrey Russell Bult , Thomas Charles Swager
CPC分类号： B64D31/06 , B64C15/02 , B64D45/00 , G05D1/0808 , G05D1/0816
摘要： Systems and methods for stabilizing an aircraft in response to a yaw movement are provided. In one embodiment, a method includes detecting a yaw movement of the aircraft. The yaw movement can cause a front portion of the aircraft to move towards a first side of the aircraft. The method can further include, in response to the yaw movement, initiating a trim process resulting in a thrust differential. The trim process can include increasing thrust in one or more engines on the first side of the aircraft and decreasing thrust in one or more engines on a second side of the aircraft. The method can include controlling the trim process based at least in part on a detected yaw movement of the aircraft.
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公开(公告)号：US20170145954A1
公开(公告)日：2017-05-25
申请号：US15219771
申请日：2016-07-26
CPC分类号： F02K1/002 , B64C15/02 , F02C9/18 , F02K1/28 , F02K1/46 , F02K3/02 , F05D2220/323 , F05D2220/328 , F05D2220/90 , F05D2270/173
摘要： A gas turbine engine system is disclosed herein. The gas turbine engine system includes an engine core configured to discharge air through an exhaust nozzle along a central axis and a thrust director arranged near the exhaust nozzle and configured to redirect the discharge air by applying flow to the discharge air near the exhaust nozzle.
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公开(公告)号：US09505488B2
公开(公告)日：2016-11-29
申请号：US14922420
申请日：2015-10-26
发明人： Marie-Claire Moune
摘要： An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped.
摘要翻译： 一种能量保护装置，包括用于在低能量情况下自动启动能量保护功能的激活单元，所述能量保护功能包括自动地接合自相关并自动地控制用于发动机的飞机的发动机以提供最大推力;辅助监控单元， 执行监视以检测飞机的至少一个发动机的保护模式的激活，尽管已经发送了激活命令，以及断开单元，在检测到这种情况的情况下自动断开自动停止， 自动停止导致触发保护功能的断开被停止。
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公开(公告)号：US20160207624A1
公开(公告)日：2016-07-21
申请号：US14997955
申请日：2016-01-18
申请人： Hi-Lite Aircraft
发明人： Jeffrey Hymer
CPC分类号： B64C29/005 , B64C15/02 , B64C29/0025 , B64D27/18 , B64D27/20
摘要： A fixed wing type Vertical Take-Off and Landing (VTOL) aircraft retains a conventional seating arrangement and utilizes a single point VTOL lift source, in the form of a counter-rotating centrifugal compressor assembly having co-axially aligned upper and lower impellers. Air is fed to the upper impeller through a central intake, and to the lower impeller through either a VTOL mode intake or a flight mode intake. Air is exhausted from the impellers through a plurality of main air outlets. Each main air outlet is fitted with a thrust augmentation duct that can be pivoted downward for VTOL, or rearward for forward flight. A controller alternately closes the flight mode intake when the thrust augmentation ducts are in the downwardly pointing VTOL position, and closes the VTOL mode intakes when the thrust augmentation ducts are in the rearwardly pointing flight position.
摘要翻译： 固定翼型垂直起飞和着陆（VTOL）飞机保留了常规的座椅布置，并且采用具有同轴对齐的上部和下部叶轮的反向旋转离心式压缩机组件形式的单点垂直升降机提升源。 空气通过中央进气口进入上叶轮，通过垂直起落架模式进气或飞行模式进气进入下叶轮。 空气通过多个主要空气出口从叶轮排出。 每个主出风口都装有一个推力增大管道，可以向下摆动以进行垂直升降，或者向后推进。 当推力增加管处于向下指示的垂直放置位置时，控制器交替地关闭飞行模式进气，并且当推力增加管处于向后指向的飞行位置时关闭垂直起落度模式进入。
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49.发明申请公开(公告)号：US20160194089A1
公开(公告)日：2016-07-07
申请号：US14322752
申请日：2014-07-02
摘要： Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.
摘要翻译： 可以使用喷射桨和/或移动质量块来控制车辆的姿态和/或姿态速率。 推力方向一般也可以使用喷射桨来控制。 喷射桨可以移动到和/或足够靠近排气流并且排出排气流，以改变推力方向。 除了或代替喷射桨之外，还可以使用活动的质量块。 可移动质量块的移动改变车辆的质心，产生改变车辆姿态的转矩。
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公开(公告)号：US20160068252A1
公开(公告)日：2016-03-10
申请号：US14838297
申请日：2015-08-27
申请人： AeroVironment Inc.
CPC分类号： 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
摘要： 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.
摘要翻译： 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。
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