公开(公告)号：US11851172B1

公开(公告)日：2023-12-26

申请号：US17334713

申请日：2021-05-29

申请人： Piasecki Aircraft Corporation

发明人： Luigi U. Ricci Moretti ,  Frederick W. Piasecki ,  Robert H. Lewis ,  Dinesh Barwey

IPC分类号： B64C27/26 ,  B64C13/16 ,  B64C9/30 ,  B64C13/48 ,  B64C9/10 ,  B64C3/38

CPC分类号： B64C27/26 ,  B64C3/385 ,  B64C9/10 ,  B64C9/30 ,  B64C13/16 ,  B64C13/48 ,  B64C2211/00

摘要： A supplemental wing for a rotary wing aircraft rotates about a pitch axis between a forward flight position and a hover position. The supplemental wing generates lift and generates both positive and negative pitching moments that balance and that may passively rotate the supplemental wing to an equilibrium position. The supplemental wing may use power assist to overcome friction to move to the equilibrium position. The lift generated by the supplemental wing reduces at high forward speeds to preserve main rotor control authority. The supplemental wing rotates to avoid aft translation when in the hover position. The supplemental wing may be retrofitted to existing helicopters and flown using existing helicopter controls without pilot re-training.

公开(公告)号：US11760476B2

公开(公告)日：2023-09-19

申请号：US17042508

申请日：2018-03-29

申请人： Yutaka Narahara

发明人： Yutaka Narahara

IPC分类号： B64C33/02 ,  B64C29/00 ,  B64C3/40 ,  B64C3/38 ,  B64U10/40

CPC分类号： B64C33/025 ,  B64C3/385 ,  B64C3/40 ,  B64C29/0033 ,  B64U10/40

摘要： A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

公开(公告)号：US20180178899A1

公开(公告)日：2018-06-28

申请号：US15391700

申请日：2016-12-27

申请人： Korea Advanced Institute of Science and Technology

发明人： Dongsoo HAR ,  Celso MORAES ,  Dongsuk KUM

IPC分类号： B64C3/38 ,  B64C29/02 ,  B64C9/20 ,  B64C13/50 ,  B64C39/02 ,  B64D27/24

CPC分类号： B64D27/24 ,  B64C3/385 ,  B64C5/02 ,  B64C11/001 ,  B64C13/50 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/62

摘要： An aircraft includes: a fuselage having opposing leading and trailing extremities along a vertical axis; a fixed wing airframe having opposed at least two main wings connected to the fuselage and extending on a horizontal axis; at least two electric coplanar main wing motors respectively attached to the main wings; a duct frame attach to the trailing extremity of the fuselage; at least two horizontal stabilizers connected to the duct frame and extending on the horizontal axis; an electric tail motor fitted an inner side of the duct frame; multiple battery packs installed inside the fuselage and suitable for supply power to the main wing motors and the tail motor; and support beams suitable for connecting the duct frame to the fuselage.

公开(公告)号：US09919796B2

公开(公告)日：2018-03-20

申请号：US14908850

申请日：2014-08-07

申请人： UNIT 1SRL

发明人： Pietro Giovenga

IPC分类号： B64C27/22 ,  B64C29/00 ,  B64C3/38 ,  B64C3/54 ,  B64D27/08 ,  B64C39/02

CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/08 ,  Y02T50/14

摘要： A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.

公开(公告)号：US20180057148A1

公开(公告)日：2018-03-01

申请号：US15252560

申请日：2016-08-31

申请人： Bell Helicopter Textron Inc.

发明人： Jeffrey Bosworth

IPC分类号： B64C13/18 ,  B64C3/38 ,  B64C29/00

CPC分类号： B64C13/18 ,  B64C3/385 ,  B64C29/0033

摘要： A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.

公开(公告)号：US20170096221A1

公开(公告)日：2017-04-06

申请号：US15205162

申请日：2016-07-08

申请人： Piasecki Aircraft Corporation

发明人： John W. Piasecki ,  Frederick W. Piasecki ,  Brian Geiger ,  Douglas Johnson ,  David Pitcairn

IPC分类号： B64C37/00 ,  B64D17/80 ,  B64C29/00 ,  B64C25/58 ,  B64C3/56 ,  B64C27/22 ,  B60F5/02 ,  B64D25/00

CPC分类号： B64C37/00 ,  B60F5/02 ,  B64C3/385 ,  B64C3/56 ,  B64C11/001 ,  B64C25/58 ,  B64C27/08 ,  B64C27/20 ,  B64C27/22 ,  B64C27/32 ,  B64C27/52 ,  B64C27/57 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/00 ,  B64C39/02 ,  B64D17/80 ,  B64D25/00 ,  B64D2201/00 ,  G05D1/102

摘要： An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be manned. The air module may have two rotors, which may be ducted fans. The air module may include a parachute, an airbag and landing gear.

公开(公告)号：US20170057630A1

公开(公告)日：2017-03-02

申请号：US15119812

申请日：2015-02-17

申请人： IAT 21 INNOVATIVE AERONAUTICS TECHNOLOGIES GMBH

发明人： Meinhard Schwaiger

IPC分类号： B64C29/00 ,  B64C3/56 ,  B64C27/02 ,  B64C39/02 ,  B64D27/04 ,  B64D27/24 ,  B64C3/38 ,  B64C27/20

CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C3/56 ,  B64C27/026 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026 ,  B64D2211/00

摘要： The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and independently of the propeller units (3).

摘要翻译： 本发明涉及一种飞机，其包括机身（1），可相对于机身（1）枢转的多个螺旋桨单元（3）和能够相对于机身至少部分地枢转的翼（5） 1）并且独立于螺旋桨单元（3）。

公开(公告)号：US09555681B2

公开(公告)日：2017-01-31

申请号：US14241239

申请日：2012-08-22

申请人： {hacek over (S)}tefan Klein

发明人： {hacek over (S)}tefan Klein

IPC分类号： B60F5/02 ,  B64C3/56 ,  B64C37/00 ,  B60F5/00 ,  B64C3/38 ,  B64C3/54 ,  B64C25/04 ,  B64C25/54 ,  B64C25/00

CPC分类号： B60F5/02 ,  B60F5/003 ,  B64C3/385 ,  B64C3/54 ,  B64C3/56 ,  B64C25/04 ,  B64C25/54 ,  B64C37/00 ,  B64C2025/003 ,  Y02T50/14

摘要： Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.

摘要翻译： 地面和空中混合动力运输车辆的变换方法包括以下转换和相互的步骤：倾斜补偿盖（7）。 将整个机翼（1）从围绕两个垂直轴（2）的运输车辆纵向位置扩展到飞行位置。 通过使每个机翼（1）的后部围绕水平轴线（3）倾斜，翼部（1）的后部部分从翼部（1）的顶部前部部分扩展到扩展的飞行位置。 机翼的起飞和着陆倾斜（1）以机翼的角度α= 0到40°开始。 前轮轨道（5）通过将前轮（5）轴向移动朝向机身而减小。 此外，描述了用于地面和空气的相应的混合运输车辆，其包含用于从英镑双轨或四轨车转换成用于起飞和降落在地面或水上的英制飞机的相互转换机制，反之亦然。

公开(公告)号：US20160244158A1

公开(公告)日：2016-08-25

申请号：US14121001

申请日：2014-08-13

申请人： USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINSTRATION

发明人： WILLIAM J. FREDERICKS ,  Mark D. Moore ,  Ronald C. Busan ,  Paul M. Rothhaar ,  David D. North ,  William M. Langford ,  Christopher T. Laws ,  William T. Hodges ,  Zachary R. Johns ,  Sandy R. Webb

IPC分类号： B64C29/00 ,  B64C3/40 ,  B64C9/14 ,  B64C39/02 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64D27/24 ,  B64D27/26

CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

摘要： Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

摘要翻译： 提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。 实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。 一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列 耦合到尾部并且每个被配置为驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电推进系统。

公开(公告)号：US20160121995A1

公开(公告)日：2016-05-05

申请号：US14205424

申请日：2014-03-12

申请人： Bertelsen Design LLC

发明人： William D. Bertelsen

IPC分类号： B64C3/54 ,  B64C3/26 ,  B64C29/00 ,  B64C3/16

CPC分类号： B64C29/0025 ,  B64C3/385 ,  B64C39/066 ,  B64C39/068 ,  Y02T50/14

摘要： In at least some implementations, an aircraft includes a fuselage, a wing spar rotatably carried by the fuselage, a first wing element and a second wing element. The first wing element is carried by the wing spar, rotatable with the wing spar, and slidably moveable relative to the fuselage and wing spar. The second wing element is connected to the first wing element for pivoted movement of the second wing element relative to the first wing element. The second wing element at least partially overlaps the first wing element and the first and second wing elements are moveable to a plurality of positions wherein the amount that the second wing element overlaps the first wing element varies to vary the effective combined wing area of the wing elements.

摘要翻译： 在至少一些实施方案中，飞行器包括机身，由机身可旋转地承载的翼梁，第一翼元件和第二翼元件。 第一翼元件由翼梁承载，可与翼梁一起旋转，并且相对于机身翼翼可滑动地移动。 第二翼元件连接到第一翼元件，用于第二翼元件相对于第一翼元件的枢转运动。 第二翼元件至少部分地与第一翼元件重叠，并且第一和第二翼元件可移动到多个位置，其中第二翼元件与第一翼元件重叠的量变化以改变翼的有效组合翼面积 元素。