公开(公告)号：US20110180672A1

公开(公告)日：2011-07-28

申请号：US13011680

申请日：2011-01-21

申请人： Nandor Vestroci ,  Fatemeh Hajibagher

发明人： Nandor Vestroci ,  Fatemeh Hajibagher

IPC分类号： B64C3/16 ,  B64C5/02

CPC分类号： B64C3/14 ,  B64C3/10 ,  B64C5/02 ,  B64C39/08 ,  B64C2003/146 ,  Y02T50/12

摘要： General purpose airplane with a swept back wing provided with a sharp leading edge as to cause flow separation and stall of the wing in cases where the limits of the regular flight envelope are exceeded in terms of angle of attack, and as a result to cause the front part of the airplane to move downward, said airplane also having positive lift-producing horizontal stabilizer provided with rounded leading edge, which does not stall at this point, therefore holds the tail in level during the process, all together acting to restore the original flight attitude. The horizontal stabilizer is essentially a straight (or similar) wing with a steeper lift-coefficient curve as that of the swept-back wing, therefore, in case of an un-commanded pitch-up of the airplane the greater increase of lift on the horizontal stabilizer together with its greater moment arm provides the stabilizing force to counter such pitching.

摘要翻译： 具有扫掠后翼的通用飞机具有锋利的前缘，以便在迎角方面超过正常飞行包线的极限的情况下导致翼的流动分离和失速，并且因此导致 飞机的前部向下移动，所述飞机还具有带有圆形前缘的正升力产生水平稳定器，在该点上不停止，因此在该过程中将尾巴保持在水平位置，一起起作用以恢复原始 飞行态度 水平稳定器基本上是直的（或类似的）翼，其具有与扫掠翼的更陡峭的升力系数曲线，因此，在飞机的未命令俯仰的情况下，升高的增加在 水平稳定器及其更大的力矩臂提供了抵抗这种俯仰的稳定力。

公开(公告)号：US20050067525A1

公开(公告)日：2005-03-31

申请号：US10651782

申请日：2003-08-29

申请人： John Morgenstern ,  Alan Arslan

发明人： John Morgenstern ,  Alan Arslan

IPC分类号： B64C3/16 ,  B64C5/04 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/36 ,  B64C13/50 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  B64C27/22

CPC分类号： B64C5/12 ,  B64C3/16 ,  B64C5/04 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/326 ,  B64C9/36 ,  B64C13/503 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： An aircraft thickness/camber control device mounts to the lower surface of a airfoil configuration, for example on a fuselage, and extends along a longitudinal axis. The device, when deployed, generates expansions ahead of compressions generated by off-design conditions, inlet spillage for example, and enables maintenance of a low boom signature. The device, when positioned at appropriate locations, may also be used as a drag reduction device. The thickness/camber control device comprises a structural member capable of coupling to the airfoil at a position forward of the concentrated source of added compression and a control element. The control element is coupled to the structural member and controls the structural member to adjust thickness/camber of the configuration to cancel the far-field effect of the extra compression or concentrated pressure source.

摘要翻译： 飞机厚度/外倾控制装置安装在机翼构造的下表面上，例如在机身上，并沿着纵向轴线延伸。 该设备在部署时，在脱离设计条件产生的压缩之前产生膨胀，例如进气口溢出，并能够维持低吊杆特征。 当位于适当位置时，该装置也可用作减阻装置。 厚度/外倾控制装置包括能够在增加压缩的集中源的前方的位置处与翼型件耦合的结构构件和控制元件。 控制元件联接到结构构件并且控制结构构件以调整构造的厚度/弯度以消除额外压缩或集中压力源的远场效应。

公开(公告)号：US20050045764A1

公开(公告)日：2005-03-03

申请号：US10652128

申请日：2003-08-29

申请人： John Morgenstern ,  Alan Arslan ,  Howard Lee ,  Robert Cuccias

发明人： John Morgenstern ,  Alan Arslan ,  Howard Lee ,  Robert Cuccias

IPC分类号： B64C3/16 ,  B64C5/02 ,  B64C5/04 ,  B64C5/10 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/36 ,  B64C13/42 ,  B64C13/50 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  B64C27/22

CPC分类号： B64C9/323 ,  B64C3/16 ,  B64C5/02 ,  B64C5/04 ,  B64C5/10 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/36 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  Y02T50/12 ,  Y02T50/32

摘要： A supersonic aircraft comprises the fuselage extending forward and aft along a longitudinal axis, a wing coupled to the fuselage, and a canard. The canard is coupled onto the fuselage forward of the wing at an elevated position that enables stretching of the aircraft lifting length and forms an effective area distribution to attain a shaped sonic boom signature.

摘要翻译： 超音速飞机包括沿着纵向轴线向前和向后延伸的机身，与机身相连的机翼和一个卡车。 该机箱在机身前方的机身上被联接到提升位置，能够延长飞机提升长度并形成一个有效的区域分布，以获得一个成形的声波吊臂标志。

公开(公告)号：US06857599B2

公开(公告)日：2005-02-22

申请号：US10746744

申请日：2003-12-23

申请人： Richard R. Tracy ,  James D. Chase ,  Ilan Kroo

发明人： Richard R. Tracy ,  James D. Chase ,  Ilan Kroo

IPC分类号： B64C3/10 ,  B64C3/16 ,  B64C5/04 ,  B64C30/00 ,  B64C39/12 ,  B64C1/00

CPC分类号： B64C30/00 ,  B64C3/10 ,  B64C3/16 ,  B64C5/04 ,  B64C39/12 ,  Y02T50/12

摘要： An aircraft, comprising a fuselage having an elongated, narrow forward portion, a main wing carried by a rear portion of the fuselage, a canard wing carried by said fuselage forward portion and having swept back leading and trailing edges tapering toward a tip or tips, the canard wing having less lifting surface than the main wing.

摘要翻译： 一种飞机，包括具有细长的较窄前部的机身，由机身的后部承载的主翼，由所述机身前部部分承载的鸭翼，并且具有朝向尖端或尖端逐渐变细的后掠的前缘和后缘， 鸭翼比主翼具有较小的提升面。

公开(公告)号：US5836549A

公开(公告)日：1998-11-17

申请号：US781237

申请日：1997-01-10

申请人： Boyd B. Bushman

发明人： Boyd B. Bushman

IPC分类号： B64C3/48 ,  B64C11/18 ,  B64C3/16 ,  B64C3/36

CPC分类号： B64C3/48 ,  B64C11/18 ,  Y02T50/145

摘要： A jet airplane capable of supersonic flight has airfoils with leading edges. Each leading edge has a cavity which extends for substantially the entire length of the airfoil. The leading edge also has a cover which is approximately the same size as the cavity. The cover has an open position and a closed position. When the cover is in the open position, the leading portion has a concave profile. When the cover is in the closed position, the leading portion has a convex profile that gives the airfoil a conventional shape. The cover is rotated to the open position when the airplane reaches supersonic speed. At supersonic speed, a shock wave forms on the leading edge of the airfoil. However, the cavity forms a compression zone between the shock wave and the leading edge, diverting the heat and pressure of the shock wave away from the airfoil. Downstream from the compressed zone, pressure wakes form along the airfoil and cool the airfoil. At subsonic speed, the cover is rotated to the closed position to achieve optimal airfoil efficiency.

摘要翻译： 能够超音速飞行的喷气式飞机具有前缘的翼型。 每个前缘具有延伸到翼型件的基本上整个长度的空腔。 前缘还具有与空腔大致相同的盖。 盖子有打开位置和关闭位置。 当盖处于打开位置时，前导部分具有凹形轮廓。 当盖处于关闭位置时，引导部分具有凸起轮廓，其使翼型件成为常规形状。 当飞机达到超音速时，盖旋转到打开位置。 在超音速下，在翼型的前缘形成冲击波。 然而，空腔在冲击波和前缘之间形成压缩区，将冲击波的热量和压力转移离开翼型。 在压缩区下游，沿翼型形成压力，并冷却翼型。 在亚音速下，盖旋转到关闭位置以获得最佳的翼型效率。

公开(公告)号：US3596852A

公开(公告)日：1971-08-03

申请号：US3596852D

申请日：1968-07-19

申请人： GEORGE H WAKEFIELD

发明人： WAKEFIELD GEORGE H

IPC分类号： B64C30/00 ,  B64C3/16 ,  B64D33/04

CPC分类号： B64C30/00

摘要： A supersonic aircraft having retractable wings and stabilizer controls wherein the leading edge of the airfoil is a continuous air inlet and the fuselage and all remaining portions of the aircraft are situated largely downstream of the air inlet, the aircraft being substantially T-shaped in configuration, a large portion of the shock wave generated by the aircraft being received into the air inlet. At least a portion of the jet exhaust is deflected into the shock wave produced by the aircraft at supersonic speeds for the purpose of disrupting the shock wave. Rapid deceleration of the aircraft from supersonic to sonic speeds obtained by extension of retractable airfoils and stabilizers.

公开(公告)号：US12116139B2

公开(公告)日：2024-10-15

申请号：US17885463

申请日：2022-08-10

申请人： REGENT Craft Inc.

发明人： Michael Klinker ,  Daniel Cottrell ,  William Bryan Baker ,  Andrew Gregg ,  Andrew Levin

IPC分类号： B64C13/16 ,  B63B1/24 ,  B63B79/00 ,  B64C3/16 ,  B64C35/00 ,  B64D27/357

CPC分类号： B64D27/357 ,  B64C3/16 ,  B64C13/16 ,  B63B1/24 ,  B63B79/00 ,  B64C35/007

摘要： A craft includes a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

公开(公告)号：US12006036B2

公开(公告)日：2024-06-11

申请号：US18168257

申请日：2023-02-13

申请人： TEXTRON INNOVATIONS INC.

发明人： Carlos Alexander Fenny ,  Rohn Lee Olson

IPC分类号： B64C29/02 ,  B64C1/06 ,  B64C3/10 ,  B64C3/16 ,  B64C11/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/50 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  B64D27/24 ,  B64D31/00 ,  B64C1/00 ,  B64C39/00 ,  B64D27/02

CPC分类号： B64C29/02 ,  B64C1/068 ,  B64C3/10 ,  B64C3/16 ,  B64C11/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/50 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64D27/24 ,  B64D31/00 ,  B64C2001/0045 ,  B64C39/029 ,  B64D27/026

摘要： The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

公开(公告)号：US20220281593A1

公开(公告)日：2022-09-08

申请号：US17591811

申请日：2022-02-03

申请人： Volocopter GmbH

发明人： Martin STOBBE ,  Krishna Pal RAJPUT ,  Sebastian MORES

IPC分类号： B64C29/00 ,  B64C3/16 ,  B64C3/32 ,  B64D27/24 ,  B64C39/06

摘要： A VTOL aircraft (1) having a fuselage (2) for transporting passengers and/or load, front and rear wings (3, 4) attached to the fuselage, a right connecting beam (5a) and a left connecting beam (5b), which connecting beams structurally connect the front wing and the rear wing, and which connecting beams are spaced apart from the fuselage, and at least two lifting units (M1-M6) on each one of the connecting beams. The lifting units each include at least one propeller (6b) and at least one motor (6a) driving the propeller, preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation. The front wing, at least in portions thereof, has a sweep angle γ between γ=450 and γ=135°, and the rear wing, at least in portions thereof, has a forward sweep with sweep angle β≥30°.

公开(公告)号：US20210371103A1

公开(公告)日：2021-12-02

申请号：US17136585

申请日：2020-12-29

申请人： Textron Innovations Inc.

发明人： Carlos Alexander Fenny ,  Rohn Lee Olson ,  Andrew James Zahasky

IPC分类号： B64C39/06 ,  B64C11/28 ,  B64C27/50 ,  B64C3/16 ,  B64C3/10 ,  B64C27/08 ,  B64C29/00 ,  B64C27/12 ,  B64D27/24 ,  B64D31/00 ,  B64C29/02 ,  B64C1/06 ,  B64C39/02

摘要： An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more motors are disposed within or attached to the spokes. Three or more propellers are proximate to a leading edge of the one or more spokes, distributed along the one or more spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight.