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公开(公告)号：US09663244B2
公开(公告)日：2017-05-30
申请号：US14356577
申请日：2014-03-19
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Tao Zhao , Xi feng Zhao , Yong Wang , Li Zhou , Tao Wang
CPC classification number: B64D47/08 , B64C39/024 , B64C2201/127 , B64C2201/128 , F16M11/10 , F16M11/18 , F16M11/2028 , F16M11/42 , G03B15/006 , G03B17/561
Abstract: Systems, devices, and methods are provided relating to improved mounting platforms for supporting a payload on a movable object. In one aspect, an apparatus for supporting a payload comprises: a first support member coupled to the payload and configured to rotate the payload; a second support member coupled to the first support member and configured to rotate the first support member relative to the second support member; and a flexible member electrically coupling the first and second support members, wherein a length of the flexible member winds around a portion of the first support member or second support member, such that the length winds up around the portion when the first support member is rotated in a first direction and unwinds from the portion when the first support member is rotated in a second direction.
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公开(公告)号：US20160349280A1
公开(公告)日：2016-12-01
申请号：US15231674
申请日：2016-08-08
Applicant: SZ DJI TECHNOLOGY CO., LTD
IPC: G01P1/00 , G01P15/08 , G01C19/5783
CPC classification number: G01P1/003 , B64C2201/14 , B64D45/00 , F16F7/104 , F16F15/00 , G01C19/16 , G01C19/56 , G01C19/5628 , G01C19/5663 , G01C19/5769 , G01C19/5783 , G01C21/16 , G01C25/00 , G01P1/023 , G01P15/08 , G01P15/0802
Abstract: The present disclosure relates to an inertia measurement module for an unmanned aircraft, which comprises a housing assembly, a sensing assembly and a vibration damper. The vibration damper comprises a first vibration-attenuation cushion; and the sensing assembly comprises a first circuit board, a second circuit board and a flexible signal line for connecting the first circuit board and the second circuit board. An inertia sensor is fixed on the second circuit board, and the first circuit board is fixed on the housing assembly. The inertia measurement module further comprises a weight block, and the second circuit board, the weight block, the first vibration-attenuation cushion and the first circuit board are bonded together. The present disclosure greatly reduces the influence of the operational vibration frequency of the unmanned aircraft on the inertia sensor and improves the measurement stability of the inertia sensor.
Abstract translation: 本公开涉及一种用于无人驾驶飞机的惯性测量模块，其包括壳体组件，感测组件和减振器。 振动阻尼器包括第一减振垫; 并且感测组件包括用于连接第一电路板和第二电路板的第一电路板，第二电路板和柔性信号线。 惯性传感器固定在第二电路板上，第一电路板固定在壳体组件上。 惯性测量模块还包括重量块，并且第二电路板，配重块，第一减振垫和第一电路板结合在一起。 本发明大大降低了无人驾驶飞行器的操作振动频率对惯性传感器的影响，提高了惯性传感器的测量稳定性。
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公开(公告)号：US09493225B2
公开(公告)日：2016-11-15
申请号：US15012068
申请日：2016-02-01
Applicant: SZ DJI TECHNOLOGY Co., LTD
Inventor： Tao Wang , Tao Zhao , Hao Du , Mingxi Wang
CPC classification number: B64C1/063 , A63H27/12 , B64C1/00 , B64C1/061 , B64C25/32 , B64C27/08 , B64C39/024 , B64C39/028 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/127 , B64C2201/14 , B64C2201/146 , B64C2201/165 , B64D47/00 , B64D47/08 , G05D1/042
Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
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公开(公告)号：US09483950B2
公开(公告)日：2016-11-01
申请号：US14857120
申请日：2015-09-17
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Mingyu Wang , Tao Wang , Jianyu Song
CPC classification number: G08G5/006 , B64C39/024 , B64C2201/024 , B64C2201/127 , B64C2201/141 , B64C2201/146 , B64D47/08 , G05D1/0214 , G05D1/101 , G08G5/0004 , G08G5/0013 , G08G5/0021 , G08G5/0026 , G08G5/0052 , G08G5/0069 , G08G5/0082
Abstract: Systems, methods, and devices are provided for providing flight response to flight-restricted regions. The location of an unmanned aerial vehicle (UAV) may be compared with a location of a flight-restricted region. If needed a flight-response measure may be taken by the UAV to prevent the UAV from flying in a no-fly zone. Different flight-response measures may be taken based on the distance between the UAV and the flight-restricted region and the rules of a jurisdiction within which the UAV falls.
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公开(公告)号：US20160200418A1
公开(公告)日：2016-07-14
申请号：US15012152
申请日：2016-02-01
Applicant: SZ DJI TECHNOLOGY Co., LTD
Inventor： Tao Wang , Tao Zhao , Zhi Gang Ou
CPC classification number: B64C27/32 , A63H27/001 , A63H27/02 , B64C11/02 , B64C11/04 , B64C27/08 , B64C27/14 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/108 , F01D5/025
Abstract: Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.
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Patent Agency Ranking
公开(公告)号：US09342987B2
公开(公告)日：2016-05-17
申请号：US14857120
申请日：2015-09-17
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Mingyu Wang , Tao Wang , Jianyu Song
Abstract: Systems, methods, and devices are provided for providing flight response to flight-restricted regions. The location of an unmanned aerial vehicle (UAV) may be compared with a location of a flight-restricted region. If needed a flight-response measure may be taken by the UAV to prevent the UAV from flying in a no-fly zone. Different flight-response measures may be taken based on the distance between the UAV and the flight-restricted region and the rules of a jurisdiction within which the UAV falls.
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公开(公告)号：US20160097793A1
公开(公告)日：2016-04-07
申请号：US14940721
申请日：2015-11-13
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Tao Wang
CPC classification number: G01P15/14 , F16F15/022 , F16F15/04 , F16F15/085 , G01C21/16 , G01P1/02 , G01P15/18
Abstract: A micro inertial measurement system includes a housing, a sensing module, and a damper. The sensing module includes a rigid sensing support, a measuring and controlling circuit board mounted on the rigid sensing support and an inertial sensor set on the measuring and controlling circuit board. The inertial sensor includes a gyroscope and an accelerometer. The sensing module is mounted in the housing. The damper is mounted in the housing and set in the gap between the sensing module and the inside wall of the housing. By use of the above-mentioned structure, the noise immunity of the inertial measuring system can be greatly improved, and the volume and weight of the inertial measuring system can be greatly reduced.
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公开(公告)号：US20160075431A1
公开(公告)日：2016-03-17
申请号：US14947923
申请日：2015-11-20
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Tao Wang , Tao Zhao , Shaojie Chen , Zhigang Ou
CPC classification number: B64C27/08 , A63H27/12 , B64C1/30 , B64C25/06 , B64C25/32 , B64C27/00 , B64C27/54 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2201/128 , B64C2201/14 , B64C2201/141 , B64C2201/20 , B64D31/14 , B64D43/00 , G01R33/0047 , G01V3/16 , G05D1/00 , Y10T29/49117
Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
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公开(公告)号：US20160031558A1
公开(公告)日：2016-02-04
申请号：US14836344
申请日：2015-08-26
Applicant: SZ DJI TECHNOLOGY CO., LTD
Inventor： Tao Wang , Tao Zhao , Shaojie Chen , Zhigang Ou
CPC classification number: B64C27/08 , A63H27/12 , B64C1/30 , B64C25/06 , B64C25/32 , B64C27/00 , B64C27/54 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2201/128 , B64C2201/14 , B64C2201/141 , B64C2201/20 , B64D31/14 , B64D43/00 , G01R33/0047 , G01V3/16 , G05D1/00 , Y10T29/49117
Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.
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公开(公告)号：US20160023744A1
公开(公告)日：2016-01-28
申请号：US14639550
申请日：2015-03-05
Applicant: SZ DJI TECHNOLOGY CO., Ltd
Inventor： Tao Wang , Tao Zhao , Hao Du , Mingxi Wang
CPC classification number: B64C1/063 , A63H27/12 , B64C1/00 , B64C1/061 , B64C25/32 , B64C27/08 , B64C39/024 , B64C39/028 , B64C2025/325 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64C2201/127 , B64C2201/14 , B64C2201/146 , B64C2201/165 , B64D47/00 , B64D47/08 , G05D1/042
Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.
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