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1. 发明申请

US20190217941A1 WING AND AIRCRAFT 审中-公开
公开(公告)号：US20190217941A1
公开(公告)日：2019-07-18
申请号：US16307672
申请日：2017-02-21
申请人： JAPAN AEROSPACE EXPLORATION AGENCY
发明人： Yoshine Ueda , Naoko Tokugawa
IPC分类号： B64C3/14 , B64C30/00
CPC分类号： B64C3/141 , B64C3/10 , B64C30/00 , B64C2003/149
摘要： [Object] To provide a wing achieving reduction of friction drag and easy to design and also easy to manufacture and an aircraft including such a wing.[Solving Means] A wing 1 is typically used as a main wing of an aircraft 100. The wing 1 is a swept-back wing having a swept-back angle A. The wing 1 is configured such that a surface pressure (pressure distribution (Cp)) on an upper surface of a vicinity of a leading edge 11 in a fluid increases from a wing root 17 to a wing tip 15. A cross-flow component of an external streamline of a surface of the wing 1 is reduced in the vicinity of the leading edge 11, and boundary layer transition is not easily induced in the vicinity of the leading edge 11. With this, friction drag caused by cross-flow instability can be reduced.

2. 发明申请

US20190127042A1 Fluid Systems That Include a Co-flow Jet 审中-公开
公开(公告)号：US20190127042A1
公开(公告)日：2019-05-02
申请号：US16135120
申请日：2018-09-19
申请人： Gecheng Zha
发明人： Gecheng Zha
IPC分类号： B64C3/14 , B64C21/02 , F15D1/00
CPC分类号： B64C3/141 , B64C3/10 , B64C3/36 , B64C21/025 , B64C29/0075 , B64C2003/143 , B64C2230/04 , B64C2230/06 , F15D1/0055
摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

3. 发明申请

US20180155017A1 VTOL AIRCRAFT WITH WINGS 审中-公开
公开(公告)号：US20180155017A1
公开(公告)日：2018-06-07
申请号：US15369870
申请日：2016-12-05
申请人： Jiann-Chung CHANG
发明人： Jiann-Chung CHANG
IPC分类号： B64C29/00 , B64C3/38
CPC分类号： B64C3/38 , B64C3/10 , B64C29/0075 , B64C39/08
摘要： A VTOL aircraft is provided with a fuselage, a pair of first thrust units, a pair of second thrust units, and a pair of first wings. The first thrust units and the second thrust units are tiltably mounted on the fuselage. The first wings are securely mounted on the fuselage, and each first wing has a root end and an outer end. The longitudinal length of the outer end is larger than that of the root end. Thus, when the VTOL aircraft is landing or taking off, the airflow can pass around the root ends of the first wings; when the VTOL aircraft is cruising or gliding, the wings can provide lift, so that the first thrust units and the second thrust units can operate in a low mode, which makes the VTOL aircraft save energy and land safely even when the thrust units are broken.

4. 发明申请

US20170057622A1 Wing Tip With Optimum Loading 审中-公开
标题翻译：翼尖具有最佳载荷
公开(公告)号：US20170057622A1
公开(公告)日：2017-03-02
申请号：US15148922
申请日：2016-05-06
申请人： Aviation Partners, Inc.
发明人： Louis B. Gratzer
IPC分类号： B64C23/06 , B64C27/46 , B64C3/10 , B64C11/18
CPC分类号： B64C23/069 , B64C3/10 , B64C11/18 , B64C27/463 , Y02T50/164
摘要： A wing tip designed for attachment to a winglet of an aircraft, the winglet coupled to a wing of the aircraft and having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.
摘要翻译：翼片设计用于附接到飞行器的小翼，小翼联接到飞行器的翼部，并且具有从机翼的前缘和后缘连续过渡的前缘和后缘。翼尖可以包括从小翼前缘到前端点的弯曲前缘，从小翼后缘到后端点的弯曲后缘，以及连接前端点和后端点的端段。端段可以从尾端点以端部段角度扫掠到前端点。

5. 发明申请

US20160375981A1 ASYMMETRIC AIRCRAFT AND THEIR LAUNCH AND RECOVERY SYSTEMS FROM SMALL SHIPS 审中-公开
标题翻译：不平衡飞机及其小型起重机和恢复系统
公开(公告)号：US20160375981A1
公开(公告)日：2016-12-29
申请号：US15111133
申请日：2015-01-13
申请人： ADVANCED PRODUCT DEVELOPMENT, LLC
发明人： William Randall McDonnell
IPC分类号： B64C3/10 , B64F1/04 , B64F1/22 , B64F1/02
CPC分类号： B64C3/10 , B63H9/0685 , B64C39/024 , B64C2201/028 , B64C2201/082 , B64C2201/182 , B64C2201/205 , B64C2201/208 , B64F1/02 , B64F1/04 , B64F1/222 , Y02T50/12 , Y02T50/826
摘要： An asymmetric aircraft (1) and an aircraft (1) that can operate from small ships (8) and be stored in high density with three aircraft or more in one helicopter hangar (107) without needing a landing gear or wing fold. These aircraft slide into and out of the hangar on dollies (90) like circuit boards in a computer and are launched and recovered using a large towed parafoil (6).
摘要翻译：一架不对称的飞机（1）和一架可从小型船只运行的飞机（1），并在一架直升机机库（107）内以三个或更多的飞机高密度存储，无需起落架或机翼折叠。这些飞机在计算机上像电路板一样滑入和移出机库（90）的机库，并使用大型拖缆机（6）发射和恢复。

6. 发明授权

US09327828B2 Spin resistant aircraft configuration 有权
标题翻译：防旋转飞机配置
公开(公告)号：US09327828B2
公开(公告)日：2016-05-03
申请号：US13946572
申请日：2013-07-19
申请人： ICON Aircraft, Inc.
发明人： Matthew Gionta , Jon Karkow , John Roncz , Dieter Koehler , David Lednicer
IPC分类号： B64C23/06 , B64C21/00 , B64C21/10 , B64C3/10 , B64C3/58 , B64C35/00
CPC分类号： B64C21/10 , B64C3/10 , B64C3/58 , B64C5/02 , B64C21/00 , B64C23/06 , B64C35/001 , B64C35/008 , Y02T50/12 , Y02T50/162
摘要： A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.
摘要翻译：公开了用于使飞机防旋转的构造和系统。飞机对旋转的阻力是通过将失速室限制在与机身相邻并远离翼尖的机翼区域来实现的。促成这种约束的翼特征包括但不限于一个或多个袖口，失速条，涡流发生器，翼扭，机翼扫掠和水平稳定器。单独或组合地，由本发明体现的飞行器配置特征使得飞机通过约束失速单元来防旋转，这使得飞机的控制表面保持操作以控制飞行器。

7. 发明授权

US09180974B2 Aircraft with an integral aerodynamic configuration 有权
标题翻译：具有整体空气动力学配置的飞机
公开(公告)号：US09180974B2
公开(公告)日：2015-11-10
申请号：US13812602
申请日：2011-04-07
申请人： Mihail Aslanovich Pogosyan , Aleksandr Nikolaevich Davidenko , Mihail Yurievich Strelets , Vladimir Aleksandrovich Runishev , Aleksey Zaharovich Tarasov , Aleksey Kirillovich Shokurov , Sergey Yurievich Bibikov , Leonid Evgenievich Krylov , Pavel Borisovich Moskalev
发明人： Mihail Aslanovich Pogosyan , Aleksandr Nikolaevich Davidenko , Mihail Yurievich Strelets , Vladimir Aleksandrovich Runishev , Aleksey Zaharovich Tarasov , Aleksey Kirillovich Shokurov , Sergey Yurievich Bibikov , Leonid Evgenievich Krylov , Pavel Borisovich Moskalev
IPC分类号： B64D33/00 , B64D27/20 , B64C3/10 , B64C5/02 , B64D33/02 , B64C15/02 , B64D7/00
CPC分类号： B64D27/20 , B64C3/10 , B64C5/02 , B64C15/02 , B64D7/00 , B64D33/02 , B64D2033/0286 , Y02T50/12 , Y02T50/44
摘要： The invention relates to multimode aircraft operated at supersonic and subsonic flight speeds in a wide range of flight altitudes. The invention is particularly applicable in multimode super-maneuverable aircraft capable of cruising at supersonic speed and having low radar signature. The technical effect to be achieved by the invention is to provide an aircraft which has low radar signature, is super-maneuverable at high angles of attack, has high aerodynamic efficiency at supersonic speeds while keeping high aerodynamic efficiency at subsonic modes, and can accommodate bulky cargo in its internal compartments. The integral aerodynamic configuration aircraft comprises fuselage (1) with strake (2), wing with panels (3) smoothly blended into fuselage (1), all-moving horizontal tail (AMHT) (4), and all-moving vertical tail (AMVT) (5). Mid-fuselage is flattened and formed longitudinally by a set of aerodynamic profiles. Engines are arranged in engine nacelles (6) spaced apart from each other horizontally, and centerlines of engines are oriented at an acute angle to the plane of symmetry of the aircraft in the direction of flight. Strake (2) comprises controlled pivoting portions (8).
摘要翻译：本发明涉及在大范围的飞行高度中以超音速和亚音速飞行速度操作的多模飞机。本发明特别适用于能够以超音速巡航并具有低雷达特征的多模超机动飞机。本发明要实现的技术效果是提供一种具有低雷达标志的飞机，在高攻角下是超级机动的，在超音速下具有高空气动力学效率，同时在亚音速模式下保持高空气动力学效率，并且可以容纳大体积货物在其内部隔间。整体空气动力学配置飞机包括机身（1），带有行星（2），机翼与面板（3）平滑地混合到机身（1），全移动水平尾翼（AMHT）（4）和全移动垂直尾翼（AMVT （5）。中部机身被平坦化并且通过一组空气动力学轮廓纵向地形成。发动机布置在水平间隔开的发动机舱（6）中，并且发动机的中心线与飞行器的飞行方向的对称平面成锐角。肩带（2）包括受控的枢转部分（8）。

8. 发明申请

US20150232204A1 AEROSPACE PLANE SYSTEM 审中-公开
标题翻译：航空平面系统
公开(公告)号：US20150232204A1
公开(公告)日：2015-08-20
申请号：US14390470
申请日：2013-04-04
申请人： Commercial Aerospace Plane Pty Limited
发明人： Nick Alexander
IPC分类号： B64G1/40 , B64D37/00 , B64C3/10
CPC分类号： B64G1/40 , B64C3/10 , B64C15/00 , B64C17/10 , B64D33/02 , B64D37/00 , B64D37/34 , B64D2033/026 , B64G1/002 , B64G1/14 , B64G1/405 , B64G1/58 , B64G1/62 , Y02T50/44
摘要： An aerospace plane (1) having an elongate body (2) supports a pair of wings (3). The wings are adapted to extend away from said body in opposing directions. A landing gear assembly is operatively associated with said body to be moveable from a retracted position where said assembly is substantially locatable within said body and an extended position were said assembly extends at least partially away from said body. At least one engine (10) is adapted to generate thrust. At least one stabilizer is adapted to assist with movement of said aerospace plane. The at least one engine is locatable at least partially within an intake housing (14) to direct air into said at least one engine. The intake housing having at least one door portion to open or close the intake housing to moderate the amount of air flowing into said intake housing and thereby said engine.
摘要翻译：具有细长主体（2）的航空航天飞机（1）支撑一对翼（3）。翼适于在相反方向上远离所述身体延伸。起落架组件可操作地与所述主体相关联，以便可从所述组件基本上定位在所述主体内的缩回位置移动，并且所述组件的延伸位置至少部分地远离所述主体延伸。至少一个发动机（10）适于产生推力。至少一个稳定器适于协助所述航空航天飞机的运动。所述至少一个发动机至少部分地位于进气室（14）内以将空气引导到所述至少一个发动机中。进气室具有至少一个门部分，用于打开或关闭进气室，以缓和流入所述进气室的空气量，从而抑制所述发动机。

9. 发明授权

US08690096B2 Aircraft with dual flight regimes 失效
标题翻译：双飞行机构
公开(公告)号：US08690096B2
公开(公告)日：2014-04-08
申请号：US12802104
申请日：2010-05-29
申请人： Alberto Alvarez Calderon F.
发明人： Alberto Alvarez Calderon F.
IPC分类号： B64C27/22
CPC分类号： B64C29/0025 , B64C3/10 , B64C29/0033 , B64C39/08 , Y02T50/12
摘要： The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area than the front wing. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform.
摘要翻译：这架飞机具有两种截然不同的节能飞行机制：一种是垂直飞行系统，由两个大型双叶片转子支撑，低叶片载荷位于右侧和左侧纵向吊臂上。悬臂在前翼的外侧区域和后翼的内侧区域之间延伸，后翼的横跨面积比前翼大。另一个飞行机构是高速到高亚音速马赫数，飞机由机翼升力支持，高翼载荷，转子停止和流动，最小的局部阻力与悬臂相邻。飞机的重心，空气动力学中心和转子中心的纵向位置非常接近。前翼优选地被扫掠，后翼优选地是W平面形状。

10. 发明申请

US20140061377A1 Spear Tactical RFID Unmanned Aircraft System (UAS) 审中-公开
标题翻译：矛战术RFID无人机系统（UAS）
公开(公告)号：US20140061377A1
公开(公告)日：2014-03-06
申请号：US13682816
申请日：2012-11-21
申请人： Donald Earl Smith
发明人： Donald Earl Smith
IPC分类号： B64F1/02 , B64F1/06 , G06K7/10 , B64F1/04
CPC分类号： B64C3/10 , B64C39/024 , B64C39/028 , B64C2201/084 , B64C2201/182 , B64D47/08 , B64F1/02 , B64F1/04 , B64F1/06 , G06K7/10366
摘要： This disclosure relates generally to the field of unmanned aircraft systems (UAS), specifically to launch, fly and land unmanned aerial vehicles (UAV). This disclosure describes a system comprised of a UAV, a portable launch pad, a telescoping landing net and an integrated RFID system. This system provides a unique combination of UAV performance and payload capabilities with integrated Radio Frequency Identification Device (RFID) electronic systems capable of withstanding extreme weather conditions including high winds in remote locations.
摘要翻译：本公开一般涉及无人飞行器系统（UAS）领域，特别是发射，飞行和陆上无人驾驶飞行器（UAV）。本公开描述了由UAV，便携式发射台，伸缩式地面网和集成RFID系统组成的系统。该系统提供无人机性能和有效载荷能力的独特组合，能够承受极端天气条件（包括偏远地区的大风）的集成射频识别设备（RFID）电子系统。

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