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1. 发明授权

US11472546B2 Fixed-wing short-takeoff-and-landing aircraft and related methods 有权
公开(公告)号：US11472546B2
公开(公告)日：2022-10-18
申请号：US16799393
申请日：2020-02-24
申请人： Aurora Flight Sciences Corporation
发明人： Tony Shuo Tao
IPC分类号： B64C29/00 , B64C1/14 , B64C39/08 , B64C9/00 , B64C11/28 , B64C23/02 , B64D27/20 , B64D27/24
摘要： Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

2. 发明授权

US11472537B2 Artificial buoyancy method and apparatus 有权
公开(公告)号：US11472537B2
公开(公告)日：2022-10-18
申请号：US17395767
申请日：2021-08-06
申请人： Gregory Hubert Piesinger
发明人： Gregory Hubert Piesinger
IPC分类号： B64C23/00 , B64C23/02 , B64D47/06
摘要： Lifting devices are described that provide aeronautical lift by either pushing air sideways off its top surface, or by pulling away from top surface air, without changing upward air pressure on its bottom surface. In a first implementation, a pyramid shaped structure is composed of a stack of thin sections whose dimensions are rapidly extended and retracted using ultrasonic movements. Top surface air is pushed sideways when extended followed by momentary low pressure when retracted, thus providing lift. In a second implementation, a rapidly rotating lifting device is composed of a stack of thin round teethed plates, resembling circular saw blades, in which the diameter of each upper plate is slightly smaller than each lower plate. This device also creates lift as teeth push air sideways and gaps between teeth create momentary low pressure. In a third implementation, a lifting device top surface contains an array of MicroElectroMechanical Systems (MEMS) devices, such as Capacitive Micromachined Ultrasonic Transducers (CMUTs), which momentary produce lift by their upper pointing membranes rapidly pulling away from lifting device top surface air when oscillating at high frequency.

3. 发明授权

US10049511B2 Method and device for detecting oscillatory failures in an automatic position control chain of an aircraft control surface 有权
公开(公告)号：US10049511B2
公开(公告)日：2018-08-14
申请号：US15284989
申请日：2016-10-04
申请人： Airbus Operations SAS
发明人： Philippe Goupil , Rémy Dayre , Simone Urbano
IPC分类号： B64C23/02 , G07C5/08 , B64D45/00 , G05B23/02 , B64C13/50
摘要： A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.

4. 发明申请

US20180093751A1 System for reducing thermal barrier of hypersonic aero vehicle 审中-公开
公开(公告)号：US20180093751A1
公开(公告)日：2018-04-05
申请号：US15831244
申请日：2017-12-04
申请人： Zhongwei Shi
发明人： Zhongwei Shi
IPC分类号： B64C1/00 , B64C23/02
CPC分类号： B64C1/0009 , B64C1/40 , B64C23/02 , B64C30/00 , B64C2230/00 , B64G1/58
摘要： A system for reducing thermal barrier of hypersonic aero vehicle is disclosed, wherein the obelisk shaped hypersonic aero vehicle is covered by combined multiple long and narrow plates. Across the plates, roller bearings are placed and spaced in short distance. The air frictions across the roller bearings of the hypersonic aero vehicle consecutively and the coefficient of friction is 0.002. The heat of the air friction is just normal and does not cause the thermal barrier and melting. The system improves the speed and reduces the energy consumption significantly.The advantages of the system are: 1. reducing the thermal barrier with innovative structure; 2. solving the problem of thermal barrier which is common for conventional hypersonic aero vehicle.

5. 发明申请

US20170267342A1 CROSS FLOW FAN WITH EXIT GUIDE VANES 审中-公开
公开(公告)号：US20170267342A1
公开(公告)日：2017-09-21
申请号：US15072657
申请日：2016-03-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Wesley K. Lord
IPC分类号： B64C39/00 , B64C23/02 , B64C11/00 , B64C21/02
CPC分类号： B64C39/005 , B64C11/006 , B64C21/025 , B64C23/02 , B64C2230/04 , F04D17/04 , Y02T50/166
摘要： A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

6. 发明授权

US08448905B2 Aircraft with aerodynamic lift generating device 有权
标题翻译：具有气动升力产生装置的飞机
公开(公告)号：US08448905B2
公开(公告)日：2013-05-28
申请号：US12225589
申请日：2007-04-02
申请人： Patrick William Peebles
发明人： Patrick William Peebles
IPC分类号： B64C23/02
CPC分类号： B64C23/02 , B64C39/005
摘要： An aircraft (1) comprising: a fuselage (2), opposing wings (3, 4) either side of the fuselage (2), each wing (3, 4) supports at least one tangential flow rotor (5) and has a rotational axis. At least one tail section (3A) is disposed on each wing (3, 4) for forming a wing trailing edge. The tail sections (3A) are moveable about the, or each, rotor axis (X) relative to the fuselage (2) so as to provide, in use of said aircraft (1), variable thrust forces, whereby in use, movement of the or each tail section (3A) controls the flight of the aircraft (1). Lift is generated by way of a shroud (12) which forms an extension to the tail section (3A) curved surface or cowl to jointly cover a proportion of the circumference of the rotor. Ideally the shroud (12) and tail section curved surfaces create a vortex chamber generally within the rotor. An alternative embodiment includes a vertical axis fan (6) is provided on the fuselage (2) to adjust aircraft “pitch”.
摘要翻译：一种飞机（1），包括：机身（2），机身（2）的任一侧的相对翼（3,4），每个翼（3,4）支撑至少一个切向流动转子（5），并且具有旋转轴。至少一个尾部（3A）设置在每个机翼（3,4）上，用于形成机翼后缘。尾部（3A）可相对于机身（2）围绕转子轴线（X）或每个转动轴线（X）移动，从而在使用所述飞行器（1）时提供可变的推力，由此在使用中，或每个尾部（3A）控制飞行器（1）的飞行。提升通过形成对尾部（3A）弯曲表面或整流罩的延伸部分的护罩（12）产生，以共同覆盖转子圆周的一部分。理想地，护罩（12）和尾部弯曲表面通常在转子内产生涡流室。替代实施例包括在机身（2）上设置垂直轴风扇（6）以调节飞机“间距”。

7. 发明授权

US5918835A Wingtip vortex impeller device for reducing drag and vortex cancellation 失效
标题翻译： Wingtip涡流叶轮装置，用于减少阻力和涡流消除
公开(公告)号：US5918835A
公开(公告)日：1999-07-06
申请号：US38813
申请日：1998-03-11
申请人： Heinz Adolf Gerhardt
发明人： Heinz Adolf Gerhardt
IPC分类号： B64C23/06 , B64C23/02
CPC分类号： B64C23/065 , Y02T50/164
摘要： The present invention is a wingtip vortex device installed at the wingtips of an aircraft for induced drag reduction and vortex cancellation. Also, the wingtip vortex device is self-contained and is powered by the wingtip vortex. The wingtip vortex device comprises a shaft coupled between the wing and a spinner. The spinner is a streamlined body of revolution with a number of radial fins. The wingtip vortex of the aircraft induces spinner whirl, which is opposite to that of the wingtip vortex. As a result, the spinner-induced whirl produces an upwash superimposed on the downwash of the vortex. Thus, the total downwash, and hence the induced drag, are reduced.
摘要翻译：本发明是安装在用于诱导减阻和消除涡流的飞机的翼尖处的翼尖涡流装置。此外，翼尖涡流装置是独立的并且由翼尖涡流驱动。翼尖涡流装置包括连接在机翼和旋转器之间的轴。旋转器是具有许多径向翅片的流线型革命体。飞机的翼尖涡流引起旋翼旋转，与翼尖涡流相反。结果，旋转器引起的旋转产生叠加在涡流的下冲洗上的上涌。因此，总的下流，因此诱发的阻力减少。

8. 发明授权

US3483676A Helicopter engine air inlets 失效
标题翻译：直升机发动机空气入口
公开(公告)号：US3483676A
公开(公告)日：1969-12-16
申请号：US3483676D
申请日：1967-09-29
申请人： GEN ELECTRIC
发明人： SARGISSON DONALD F
IPC分类号： F02C7/052 , B64C23/06 , B64C23/02
CPC分类号： B64D33/02 , B64D2033/0246 , F02C7/052 , Y02A50/2355 , Y02T50/672
摘要： 1,192,503. Cyclone separators. GENERAL ELECTRIC CO. 30 Aug., 1968 [29 Sept., 1967], No. 41489/68. Heading B2P. [Also in Division F1] The invention relates to air intake structure for a gas turbine engine which constitutes the power plant of a helicopter. A cowl defining an air intake is provided axially aligned with and forward of the engine intake, the cowl having a plurality of filters extending radially therethrough, the filters serving to remove dust and like particles and passing essentially clean air to the interior of the cowl when there is air flow therethrough. Closure doors are provided which are movable between a first position in which air may flow axially through the cowl to the engine intake, and a second position in which such air flow is prevented. A valve is associated with each filter element, the valve closing when air flows axially through the cowl when the closure doors are open, thus preventing flow of air through the filter elements, and opening when such axial air flow is prevented by closing of said doors. The helicopter shown is provided with two gas turbine engines E, each having a cowl 14 axially aligned with the engine intake. The cowl 14 comprises an outer screen 22, an outer panel 24 and an inner panel 26. A plurality of vortex type filters 28 are associated with the panels 24, 26 each filter comprising a vortex tube 30 and a frusto conical outlet 32. A flap valve 36 is pivotally mounted at 37 adjacent the outlet 32, being shown in the open position in Fig. 6 and in the closed position in Fig. 7. A pair of closure doors 34 is mounted at the forward open end of the cowl. In normal operation the doors 34 are open and air flows axially through the cowl thus acting to close the flap valves 36 so that no air enters through the filters 28. When operating in dust-laden conditions the doors 34 are closed so that no air flows axially into the cowl and the flap valves 36 now open, and air flows 'radially inwardly through the filters 28, dust particles being separated out and clean air passing into the engine intake 16. The dust particles separated out pass between the panels 24, 26 and are discharged through outlet 35, Fig. 2 not shown.

9. 发明授权

US3380689A Stabilizing system for aircraft 失效
标题翻译：飞机稳定系统
公开(公告)号：US3380689A
公开(公告)日：1968-04-30
申请号：US54210366
申请日：1966-04-12
申请人： RUDOLF BUCHER
发明人： RUDOLF BUCHER
IPC分类号： B64C23/02 , B64C29/00
CPC分类号： B64C29/00 , B64C23/02

10. 发明授权

US2106820A Flying machine 失效
标题翻译：飞机
公开(公告)号：US2106820A
公开(公告)日：1938-02-01
申请号：US6718836
申请日：1936-03-05
申请人： HENRI THIBAULT EMILE
发明人： HENRI THIBAULT EMILE
IPC分类号： B64C23/02
CPC分类号： B64C23/02

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