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公开(公告)号：US20170247120A1
公开(公告)日：2017-08-31
申请号：US15054368
申请日：2016-02-26
Applicant: Skycatch, Inc.
Inventor： Samuel Giles Miller
CPC classification number: B64F1/36 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/127 , B64C2201/165 , B64F1/007
Abstract: The present disclosure is directed toward a system for autonomously landing an unmanned aerial vehicle (UAV) within an unmanned aerial vehicle ground station (UAVGS) and removing a battery assembly from within the UAV while landed. In particular, systems described herein enable a battery arm to engage a battery assembly and remove the battery assembly from within the UAV. Additionally, the battery arm can include one or more sensors that detect a pattern of sensor contacts arranged on an end of the battery assembly. In particular, the sensors on the battery arm can detect and identify the battery assembly based on the particular pattern of sensor contacts on the end of the battery assembly.
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公开(公告)号：US20170247113A1
公开(公告)日：2017-08-31
申请号：US15441112
申请日：2017-02-23
Applicant: PARROT DRONES
Inventor： Thierry SANLAVILLE , Maxime DUCLOUX , Flavien MORRA
CPC classification number: B64D27/00 , B64C27/08 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/165 , B64D47/08
Abstract: Embodiments disclosed include a rotary-wing drone that includes a drone body and linking arms, such that a propulsion unit is located at the distal ends of the linking arms. The rotary-wing drone may also include a stiff battery pack with at least one fixation means and a guiding profile. The drone body may also include a platform with at least one guiding rail configured to cooperate and receive the complementary guiding profile of the battery pack and at least one fixation means complementary to the fixation means of the battery pack so that the battery pack attaches onto and stiffens the drone body.
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公开(公告)号：US20170247109A1
公开(公告)日：2017-08-31
申请号：US15595556
申请日：2017-05-15
Applicant: Amazon Technologies, Inc.
Inventor： Daniel Buchmueller , Louis LeRoi LeGrand, III , Jack Erdozain, JR. , Scarlett Elizabeth Koller , Eric Alexander Riehl , Trevor Barr Walker
CPC classification number: B64C39/024 , B64C15/14 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/128 , B64C2201/14 , B64C2201/146 , B64D1/08 , B64D1/12 , G05D1/00 , G05D1/0011 , G05D1/0094 , G05D1/0202 , G06Q10/083
Abstract: Stabilized delivery using an Unmanned Aerial Vehicle (UAV) is described. In one embodiment, the UAV includes a flight controller configured to control a flight path of the UAV, a winch mechanism secured to an underside of the UAV, a platform tethered to and extendable from the winch mechanism, and a ballast system configured to stabilize the platform. The winch mechanism may be relied upon to drop an item for delivery without landing the UAV. The winch mechanism can include a first winch mechanism secured to the UAV at a first orientation and a second winch mechanism secured to the UAV at a second orientation. Because the winch mechanism may give rise to certain design and operating considerations, various active and passive flight and/or ballast control systems are described. These systems maintain an orientation of the UAV, the platform, and/or the item during one or more stages of airborne drop delivery.
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公开(公告)号：US20170240291A1
公开(公告)日：2017-08-24
申请号：US15371373
申请日：2016-12-07
Applicant: Hylium Industries, Inc.
Inventor： Seo Young KIM
CPC classification number: B64D37/005 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/066 , B64C2201/108 , B64C2201/165 , B64D33/08 , B64D37/02 , H01M8/04014 , H01M8/04201 , H01M8/2475 , H01M16/006 , H01M2220/20 , H01M2250/20 , H02J7/0052 , H02J7/34 , Y02T50/44 , Y02T90/32
Abstract: A fuel cell power pack used as a power source in a multicopter includes a fuel tank and a fuel cell stack for producing electrical energy using hydrogen supplied from the fuel tank and supplying the electrical energy to a battery, and since the fuel cell stack is disposed at a certain point of an arm extended from the aircraft body in the radius direction (a point affected by a descending air current generated by each rotating blade), the electrical energy can be produced using the descending air current generated by the rotating blade without configuring a separate blowing apparatus.
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95.发明申请公开(公告)号：US20170233073A1
公开(公告)日：2017-08-17
申请号：US15445837
申请日：2017-02-28
Applicant: SZ DJI TECHNOLOGY CO., LTD.
Inventor： Jiyuan Ao , Xumin Wu , Tingting Wang , Zhuang Feng , Sungki Lee
CPC classification number: B64C39/026 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/141 , G01L19/14
Abstract: The invention provides systems and methods for isolating one or more sensors within an unmanned aerial vehicle (UAV). The method may comprise providing a UAV that includes a housing forming a central body of the UAV. The UAV may also include a first compartment of the central body with one or more electrical components (1) disposed therein, and (2) adapted to affect operation of the UAV. Further, the UAV may include a second compartment of the central body that is isolated from the first compartment such that the barometric pressure in the second compartment is independent of the barometric pressure in the first compartment. Additionally, the method may comprise disposing the one or more sensors within the second compartment of the UAV.
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Patent Agency Ranking
公开(公告)号：US20170225574A1
公开(公告)日：2017-08-10
申请号：US15040236
申请日：2016-02-10
Applicant: QUALCOMM Incorporated
Inventor： Christian Oliver Thelen , Michael Mitrani
CPC classification number: B60L11/182 , B60L53/12 , B60L53/30 , B64C27/08 , B64C39/024 , B64C2201/042 , B64C2201/066 , B64D27/24 , B64D2221/00 , H02J7/0042 , H02J7/025 , H02J50/90 , Y02T50/62
Abstract: Some aspects provide for a multicopter that includes a frame and a charging unit receiver configured to receive a portion of a charging unit. In some aspects, a perimeter of a cross-section of the proximal portion of the charging unit receiver may be shorter than a perimeter of a cross-section of the distal portion of the charging unit receiver. In some aspects, a perimeter of a cross-section of the distal portion of the charging unit receiver may be shorter than a perimeter of a cross-section of the proximal portion of the charging unit receiver. Some aspects provide for a charging unit that includes a frame and a multicopter receiver configured to receive a portion of the multicopter. In some aspects, a perimeter of a cross-section of the distal portion of the multicopter receiver may be shorter than a perimeter of a cross-section of the proximal portion of the multicopter receiver.
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公开(公告)号：US20170217600A1
公开(公告)日：2017-08-03
申请号：US15501318
申请日：2015-07-29
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Eyal REGEV
CPC classification number: B64D35/02 , B60L50/15 , B64C15/00 , B64C27/14 , B64C2201/042 , B64C2201/165 , B64D27/24 , H02K7/10 , H02K7/108 , H02K16/00 , H02K21/24 , H02K2213/12 , Y02T50/44 , Y02T50/62
Abstract: A propulsion system assembly is provided including a driveshaft and a plurality of electric motor modules. The driveshaft is rotatably mounted to a casing about a drive axis, the driveshaft including a first shaft end and an opposite facing second shaft end. The plurality of electric motor modules are in axially stacked relationship with one another with respect to the drive axis to define an electric motor module stack, each electric motor module being configured for transmitting a torque to the driveshaft when coupled thereto independently of at least one other electric motor module. Each electric motor module includes a controllable clutch arrangement for selectively coupling and decoupling the respective electric motor module with respect to the driveshaft to respectively enable and disable transmission of torque between the respective electric motor module and the driveshaft.
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公开(公告)号：US20170217585A1
公开(公告)日：2017-08-03
申请号：US15328611
申请日：2015-07-21
Applicant: ATMOS UAV B.V.
Inventor： Sander HULSMAN , Jurjen DE GROOT , Maarten MILIS , Dirk Lucas Eduard DOKTER , Joost Leon BOUMAN , Ruud KNOOPS
CPC classification number: B64C29/02 , B64C39/024 , B64C2201/028 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165
Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,12) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.
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公开(公告)号：US20170217562A1
公开(公告)日：2017-08-03
申请号：US15013644
申请日：2016-02-02
Applicant: James Schalla
Inventor： James Schalla
CPC classification number: B64C1/34 , A63H27/12 , A63H29/18 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/101 , B64C2201/108
Abstract: In one embodiment, an unmanned aircraft comprises a housing, an inflatable fuselage, three motors, and three propellers. The housing may comprise an enclosure configured to house one or more electrical components. The inflatable fuselage may comprise a first, a second and a third spindle each extending from the housing. The first motor may be coupled to a first propeller and mounted to the first spindle. The second motor may be coupled to a second propeller and mounted to the second spindle. The third motor may be coupled to a third propeller and mounted to the third spindle.
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公开(公告)号：US20170210481A1
公开(公告)日：2017-07-27
申请号：US15321699
申请日：2016-07-15
Applicant: HANKUK CARBON CO., LTD.
Inventor： Jeong-Gyu BAK , Jinsoo CHO , Boseong KIM , Senghyun YUN , Sunghong WON , Tae-Chul JEONG , Sooyoung CHO , Geunho LEE , Kyusung PARK , Juhyung HA , Changmo MOON , Sunho BECK , Changjun MEANG , Hanki LEE , Minjun KIM , Dain LEE
CPC classification number: B64D27/24 , B64C29/0025 , B64C29/0033 , B64C2201/042 , B64D27/02 , B64D31/06 , B64D35/02 , B64D2027/026 , B64D2221/00 , Y02T50/44 , Y02T50/64
Abstract: A vertical take-off and landing aircraft using a hybrid electric propulsion system includes an engine, a generator that produces electric power using power supplied by the engine, and a battery that stores the produced electric power. A motor receives the electric power stored in the battery and electric power produced by the generator but not stored in the battery and provides the power to a thrust generating apparatus. A controller selects either silence mode or normal mode, and determines the amount of electric power stored in the battery and the amount of electric power not stored in the battery from the electric power supplied to the motor. In the silence mode, the controller supplies only the electric power stored in the battery and controls a duration by adjusting output power of motor. In the normal mode, the controller supplies electric power not stored in the battery.
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