公开(公告)号：US20020005454A1

公开(公告)日：2002-01-17

申请号：US09826424

申请日：2001-04-03

Inventor： Paul B. MacCready ,  Bart D. .Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

IPC: B64C001/00 ,  B64B001/20 ,  B64C017/00

CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中的燃料的沸腾率。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

公开(公告)号：US5503350A

公开(公告)日：1996-04-02

申请号：US145204

申请日：1993-10-28

Applicant: Howard A. Foote

Inventor： Howard A. Foote

IPC: B64C39/02 ,  B64D27/24 ,  H01Q1/24

CPC classification number: G05D1/0038 ,  B64C39/024 ,  B64D27/24 ,  H01Q1/248 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/122 ,  B64C2201/165 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S320/33

Abstract: An unmanned, remotely controlled microwave-powered aircraft for use as a stationary communications platform. The aircraft is generally a flying wing with a large, flat inner wing having a rectenna on the underside. Rectennas may also be provided on the underside of the wings, the combined output from the rectenna being used to provide power to two electric motors housed within torpedo-shaped nacelles which drive two rear propellers. The rectenna converts a microwave signal at 35 GHz generated by a ground power station utilizing dual gyrotrons and a 34-meter diameter antenna dish. The aircraft has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna to supply power to the flight controls, propulsion system and payload.

Abstract translation: 一种无人遥控的微波动力飞机，用作固定通信平台。 该飞机通常是具有大的，平坦的内翼的飞翼，其在下侧具有直角天线。 也可以在机翼的下侧设置整流器，来自整流罩的组合输出用于向容纳在用于驱动两个后部螺旋桨的鱼雷型发动机舱内的两个电动机提供动力。 整流天线使用双回旋加速器和直径34米的天线盘转换由地面电站产生的35GHz的微波信号。 该飞机具有优选的翼型横截面，并且由轻质但坚固的材料构成，以便提供几个月的增强的飞行时间。 电力管理和分配系统管理由天线产生的直流电力，为飞行控制，推进系统和有效载荷提供动力。

公开(公告)号：US4601442A

公开(公告)日：1986-07-22

申请号：US545083

申请日：1983-10-25

Applicant: Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

Inventor： Franz Friedel ,  Werner Fruhauf ,  Gunter Harms ,  Georg Heise ,  Heinrich Lukewille

IPC: B64C39/02 ,  F16D7/02 ,  F42B10/64 ,  F42B15/10 ,  F42B15/02

CPC classification number: F42B10/64 ,  B64C39/024 ,  F16D7/021 ,  F42B15/105 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/165 ,  B64C2201/201

Abstract: Unmanned missile with strongly backswept wing unit, in particular delta wings, which is transported in a container and is launched from the container by means of an auxiliary drive after release of a lock, and which during cruise flight is drivable by a propeller engine, lateral force surfaces (25) being deployable for stabilization of the missile during cruise flight, from retraction spaces (26) in the region of the wing root of the delta wings, and further a friction clutch (64, 65) is provided at the missile which, without supply of energy from the outside, couples the standing propeller 6 with the drive motor (7) running in the container, after leaving the container.

Abstract translation: 具有强力后卫的翼单元，特别是三角翼的无人驾驶导弹，其在集装箱中运输并且在释放锁之后通过辅助驱动从容器发射，并且在巡航飞行期间由螺旋桨发动机驱动，横向 力表面（25）可展开用于在巡航飞行期间稳定导弹，来自三角翼机翼根部区域中的缩回空间（26），并且在该导弹处提供摩擦离合器（64,65） 在没有从外部供应能量的情况下，在离开容器之后将立式螺旋桨6与在容器中运行的驱动马达（7）相耦合。

公开(公告)号：US20230271700A1

公开(公告)日：2023-08-31

申请号：US17652705

申请日：2022-02-28

Applicant: Matthew W. TOWNSEND

Inventor： Matthew W. TOWNSEND

IPC: B64C29/02 ,  B64C39/02 ,  B64C17/02 ,  B64C3/40

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C17/02 ,  B64C3/40 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/088 ,  B64C2201/128

Abstract: A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

公开(公告)号：US20230192270A1

公开(公告)日：2023-06-22

申请号：US17553302

申请日：2021-12-16

Applicant: Natilus Inc.

Inventor： Aleksey MATYUSHEV ,  Anatoly Y. STARIKOV

IPC: B64C1/22 ,  B64C39/10 ,  B64C1/14 ,  B64C39/02

CPC classification number: B64C1/22 ,  B64C39/10 ,  B64C1/1415 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/028

Abstract: In one embodiment, an aircraft includes a blended wing body (BWB) and a cargo bay having a polygonal shape. A longitudinal centerline of the aircraft intersects a vertex of the polygonal shape and an interior angle of the vertex.

公开(公告)号：US20180244383A1

公开(公告)日：2018-08-30

申请号：US15755187

申请日：2016-08-30

Applicant: UNIVERSITY OF MARYLAND, COLLEGE PARK

Inventor： EVANDRO GURGEL DO AMARAL VALENTE ,  NORMAN M. WERELEY ,  EDUARDO GURGEL DO AMARAL VALENTE

IPC: B64C37/00 ,  B64C39/10 ,  B64C29/00 ,  B64C29/02 ,  B64C15/12 ,  B64C5/02 ,  B64C11/46 ,  B64C19/00

CPC classification number: B64C37/00 ,  B64C5/02 ,  B64C11/46 ,  B64C15/12 ,  B64C17/02 ,  B64C19/00 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/205 ,  B64C2201/208 ,  B64C2211/00 ,  B64D29/00

Abstract: The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

公开(公告)号：US09926084B2

公开(公告)日：2018-03-27

申请号：US15291878

申请日：2016-10-12

Applicant: Aurora Flight Sciences Corporation

Inventor： James Peverill ,  Adam Woodworth ,  Benjamin Freudberg ,  Dan Cottrell ,  Terrence McKenna

IPC: B64F1/02 ,  B64C39/02 ,  G05D1/10 ,  B60L11/18 ,  B64F1/36 ,  B64C25/68 ,  B64D47/04 ,  B64D47/08 ,  G06K9/00

CPC classification number: B64F1/02 ,  B60L11/1816 ,  B60L11/1838 ,  B60L2200/10 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/066 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/182 ,  B64D47/04 ,  B64D47/08 ,  B64F1/362 ,  G05D1/101 ,  G06K9/0063

Abstract: An aerial vehicle landing station comprising a first post and a second post, wherein the second post is spaced apart from the first post and a cable to capture an aerial vehicle, wherein the cable is stretched between the first post and the second post and configured to support the weight of the aerial vehicle once captured and the cable may provide a charging current to the aerial vehicle once captured. One or more markers may be further positioned on the cable to designate a landing point, wherein the one or more markers are configured to be visually tracked by the aerial vehicle. A cable management device coupled to the cable via one or more pulleys may regulate tension of the cable. A communications transceiver at the aerial vehicle landing station may wirelessly communicate data with the aerial vehicle.

公开(公告)号：US20180057136A1

公开(公告)日：2018-03-01

申请号：US15692524

申请日：2017-08-31

Applicant: HORIZON HOBBY, LLC

Inventor： James Haley ,  Mike McConville ,  Aaron Shell ,  Chris Huhn ,  Dustin Buescher

IPC: B64C1/26 ,  B64C3/56 ,  B64C39/02

CPC classification number: B64C1/26 ,  A63H27/001 ,  B64C3/56 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2211/00

Abstract: Remote control aircraft may benefit from airframes with components that are easy to connect and disconnect. For example, during repair, storage, or transport, it is beneficial to disconnect a wing from a fuselage of a remote controlled aircraft. Systems and methods for connecting and disconnecting airframe components are described herein. For example, a snap-fit mechanism is used in some instances to provide a solid connection during operation or flight, and also to quickly and easily disconnect components at various times, such as during repair, storage, or transport. The snap-fit mechanism allows for a quick disconnect without the use of tools and without causing any loose parts.

公开(公告)号：US20180048828A1

公开(公告)日：2018-02-15

申请号：US15672775

申请日：2017-08-09

Applicant: PARROT DRONES

Inventor： Henri Seydoux ,  Frédéric Pirat ,  Arnaud Chauveur

IPC: H04N5/232 ,  B64D47/08 ,  G01C21/18 ,  B64C39/02

CPC classification number: H04N5/23296 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64D47/08 ,  G01C21/18 ,  G03B15/006 ,  G05D1/0038 ,  G05D1/0094 ,  G05D1/0808 ,  G05D1/101 ,  H04N5/23203 ,  H04N5/23293

Abstract: The invention relates to a method for capturing a video using a camera on board a fixed-wing drone, the camera comprising an image sensor, the fixed-wing drone comprising an inertial unit configured to measure the roll angle, the pitch angle and/or the yaw angle of the fixed-wing drone 57858. This method comprises obtaining one or more images corresponding to a zone of the sensor with reduced dimensions relative to those of the sensor and associated with a shot reference, the position of the zone being determined from the orientation of the shot reference obtained as a function of the roll angle, the pitch angle and/or the yaw angle of the fixed-wing drone.

公开(公告)号：US20180039272A1

公开(公告)日：2018-02-08

申请号：US15672264

申请日：2017-08-08

Applicant: PARROT DRONES

Inventor： Henri SEYDOUX ,  Frédéric PIRAT ,  Arnaud VAN DEN BOSSCHE

IPC: G05D1/00 ,  B64C39/02 ,  B64D47/08

CPC classification number: G05D1/0088 ,  A63H30/04 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/00 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2203/00 ,  B64D47/08 ,  G05D1/0038 ,  G05D1/101

Abstract: A module for a drone that integrates an electronic circuit and one or more sensors for the attitude, altitude, speed, orientation and/or position of the drone in the same one-piece housing. The module also integrates an electronic power circuit that receives set command values prepared by the processor of the electronic circuit on the basis of the data provided by the integrated sensors and provides, as an output, corresponding signals for directly supplying current or voltage to the propulsion means of the drone and to the control surfaces.