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41.
公开(公告)号:US20180181116A1
公开(公告)日:2018-06-28
申请号:US15852971
申请日:2017-12-22
Applicant: Samsung Electronics Co., Ltd.
Inventor: Jong Kee LEE , Su Hyun NA , Tae Ho WANG , Choon Kyoung MOON , Eun Kyung YOO , Olivia LEE , Hee Young CHUNG
IPC: G05D1/00 , G06F3/0488 , G06F3/0484
CPC classification number: G05D1/0016 , B64C39/024 , B64C2201/108 , B64C2201/127 , B64C2201/146 , G05D1/0038 , G05D1/101 , G06F3/04847 , G06F3/04883 , G06F2203/04808 , H04N7/185
Abstract: An electronic device is provided that includes a communication circuit configured to transmit and receive wireless data with the unmanned aerial vehicle (UAV), a display configured to display a user interface (UI) for operating the UAV, a memory, and a processor electrically coupled with the communication circuit, the display, and the memory. The processor is configured to receive information about a direction of a first point of the UAV from the UAV, display a direction indication object corresponding to a direction of the first point on the display, in response to receiving a user input associated with movement or rotation of the UAV, generate a control signal for moving or rotating the UAV with respect to the first point in response to a location of the direction indication object and the user input, and transmit the generated control signal to the UAV using the communication circuit.
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42.
公开(公告)号:US20180178899A1
公开(公告)日:2018-06-28
申请号:US15391700
申请日:2016-12-27
Inventor: Dongsoo HAR , Celso MORAES , Dongsuk KUM
CPC classification number: 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
Abstract: 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.
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公开(公告)号:US20180170553A1
公开(公告)日:2018-06-21
申请号:US15385136
申请日:2016-12-20
Applicant: QUALCOMM Incorporated
Inventor: Peng WANG , Don LE , Jon ANDERSON , Chinchuan Andrew CHIU
CPC classification number: B64D13/006 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64D33/08 , F28D15/0275 , F28D15/04 , F28D2021/0021
Abstract: An innovative passive cooling solution with sealed UAV enclosure system allows heat from a semiconductor chip to be dissipated to the ambient environment through evaporation/condensation phase-change cooling and air cooling a heat sink such as a fin without any additional power consumption to operate cooling solution. One example of such a solution may include a pipe with a fin and a fluid. The pipe may include a wick structure along an inner surface of the pipe configured to allow the fluid to travel within the wick structure and to allow a vapor form of the fluid to exit the wick structure towards a center of the pipe.
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公开(公告)号:US09994313B2
公开(公告)日:2018-06-12
申请号:US14554892
申请日:2014-11-26
Applicant: XCraft Enterprises, LLC
Inventor: Jerry Daniel Claridge , Charles Fischer Manning
CPC classification number: B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/027 , B64C2201/042 , B64C2201/104 , B64C2201/108
Abstract: This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.
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公开(公告)号:US20180155032A1
公开(公告)日:2018-06-07
申请号:US15870187
申请日:2018-01-12
Applicant: United Parcel Service of America, Inc.
Inventor: Julio Gil , Jeffrey Cooper
IPC: B64D1/22 , G08G5/02 , E05F15/77 , G08G5/00 , G06Q10/08 , B60P3/11 , B64C39/02 , B64D9/00 , B64D45/04 , B64F1/02 , B64F1/10 , B64F1/22 , B64F1/32 , G01S19/42 , B65G1/06 , B65G1/04
CPC classification number: G06Q10/0832 , B60P3/11 , B64C39/024 , B64C2201/024 , B64C2201/108 , B64C2201/128 , B64C2201/141 , B64C2201/146 , B64C2201/18 , B64C2201/208 , B64C2211/00 , B64D1/00 , B64D1/22 , B64D9/00 , B64D45/04 , B64F1/02 , B64F1/10 , B64F1/22 , B64F1/32 , B65G1/0435 , B65G1/06 , E05F15/77 , G01S19/42 , G06Q10/083 , G06Q10/0833 , G08G5/006 , G08G5/0069 , G08G5/025 , H04L67/26 , H04W4/70
Abstract: Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.
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公开(公告)号:US20180155009A1
公开(公告)日:2018-06-07
申请号:US15833385
申请日:2017-12-06
Applicant: ETH Zurich
Inventor: Mark W. MUELLER , Sergei LUPASHIN , Raffaello D'ANDREA , Markus WAIBEL
CPC classification number: B64C13/24 , B64C27/08 , B64C27/20 , B64C27/32 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/108 , B64C2201/127 , B64C2201/141 , B64C2201/146 , B64C2203/00 , B64D45/00 , G05D1/0072
Abstract: According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure. The method may comprise the step of identifying a failure wherein the failure affects the torque and/or thrust force produced by an effector, and in response to identifying a failure carrying out the following steps, (1) computing an estimate of the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said multicopter rotates when flying, (2) computing an estimate of the angular velocity of said multicopter, (3) controlling one or more of said at least four effectors based on said estimate of the orientation of the primary axis of said body with respect to said predefined reference frame and said estimate of the angular velocity of the multicopter. The step of controlling one or more of said at least four effectors may be performed such that (a) said one or more effectors collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein (i) the torque along said primary axis causes said multicopter to rotate about said primary axis, and (ii) the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and (b) such that said one or more effectors individually produce a thrust force along said primary axis.
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公开(公告)号:US09988147B2
公开(公告)日:2018-06-05
申请号:US15638970
申请日:2017-06-30
Applicant: AEROVIRONMENT, INC.
Inventor: Dana J. Taylor , Phillip T. Tokumaru , Bart Dean Hibbs , William Martin Parks , David Wayne Ganzer , Joseph Frederick King
IPC: B64C29/00 , G05D1/08 , B64C27/26 , B64C39/02 , B64C11/32 , B64C29/02 , B64C27/605 , B64D27/24 , B64C27/54
CPC classification number: B64C29/0025 , B64C11/32 , B64C27/26 , B64C27/54 , B64C27/605 , B64C29/00 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/24 , G05D1/0858
Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.
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公开(公告)号:US20180149479A1
公开(公告)日:2018-05-31
申请号:US15577303
申请日:2016-06-29
Applicant: Yuneec Technology Co., Limited
Inventor: YU TIAN , Wenyan JIANG
CPC classification number: G01C21/005 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64D47/08 , G01S7/481 , G01S17/023 , G01S17/933 , G03B15/006 , G03B17/12 , G05D1/0038 , G05D1/0094 , G05D1/0202 , G05D1/101 , G06K9/0063 , G06K9/209 , G06K9/46 , G06K9/4604 , G06K9/6202 , G06K2209/21 , G06T7/60 , G06T2207/10032 , G08G5/045 , H04N5/23238 , H04N5/2328 , H04N5/23296 , H04N5/247
Abstract: Provided are a geo-location or navigation camera, and an aircraft and a navigation method therefor. The geo-location or navigation camera comprises an image capturing apparatus (15), an image capturing direction of the image capturing apparatus (15) being vertically downward. The camera further comprises a gimbal stability-enhancement system comprising a gimbal body and a gimbal control system connected to the gimbal body. The image capturing apparatus (15) is arranged on the gimbal body. By means of the balance control and shock absorption effects of the gimbal stability-enhancement system, the stability of the image capturing apparatus (15) is better, and the image capturing direction of the image capturing apparatus (15) is maintained to be always vertically downward. The aircraft can still be navigated without a GPS. The method has advantages of being highly accurate and widely applicable.
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公开(公告)号:US20180141660A1
公开(公告)日:2018-05-24
申请号:US15873429
申请日:2018-01-17
Applicant: TEAL DRONES, INC.
Inventor: George Michael Matus
IPC: B64C39/02
CPC classification number: B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/141 , B64C2201/145 , B64C2211/00
Abstract: A rotor-based remote flying vehicle platform includes a vehicle body. The vehicle body includes a processing unit that receives positional sensor data and provides flight controls based upon the received positional sensor data. The vehicle body also includes a first frame connection interface that is configured to interface with a plurality of different arm types. The first frame connection interface comprises a physical connection and an electronic connection. Additionally, the rotor-based remote flying vehicle platform includes a first arm, of a rotor-based remote flying vehicle platform, that is selectively connectable to the vehicle body through the first frame connection interface. The first arm comprises a first arm connection interface that is selectively connectable to the first frame connection interface. Additionally, the first arm comprises a first motor mounted to the first arm.
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公开(公告)号:US09975442B2
公开(公告)日:2018-05-22
申请号:US15455199
申请日:2017-03-10
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor: Sang-Cherl Lee , Hae-Dong Kim , Hyeon-Cheol Gong , Gi-Hyuk Choi , In-Hee Hwang , Byong-Suk Suk
CPC classification number: B60L11/1824 , B60L2200/10 , B60L2230/10 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/066 , B64C2201/108 , B64C2201/182 , B64C2201/201 , B64D45/08 , B64F1/00 , B64F1/005 , B64F1/12 , B64F1/222 , F21S8/086 , F21V33/00 , F21W2131/103 , F21Y2115/10
Abstract: An apparatus and method for containing and charging an unmanned VTOL aircraft are disclosed. The apparatus for containing and charging an unmanned VTOL aircraft includes a post, an extended member, a cover, a fastening unit, and a charging unit. The post is placed on a ground. The extended member is connected to the post. The cover is provided on the extended member, and is configured to be opened or closed in order to contain and protect the unmanned VTOL aircraft. The fastening unit is provided in the cover, and is configured to fasten the unmanned VTOL aircraft. The charging unit is provided in the fastening unit, and is configured to charge the unmanned VTOL aircraft.
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