公开(公告)号：US20190248464A1

公开(公告)日：2019-08-15

申请号：US16394966

申请日：2019-04-25

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： Fangming YE ,  Zhao YANG ,  Di OU ,  Hongshan LI

IPC: B64C1/06 ,  B64C39/02

CPC classification number: B64C1/063 ,  B64C1/061 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/126

Abstract: An unmanned aerial vehicle includes a fuselage and an arm coupled to the fuselage. The arm includes a first segment, a second segment, and a connecting assembly coupling and locking the first segment and the second segment to each other. The connecting assembly includes a first connecting member and a second connecting member. The first connecting member is rotatably coupled to one of the first segment or the second segment. The second connecting member is coupled to another one of the first segment or the second segment. The first connecting member is rotatable relative to the arm and engages with the second connecting member to lock the first segment and the second segment.

公开(公告)号：US20180320767A1

公开(公告)日：2018-11-08

申请号：US15587945

申请日：2017-05-05

Applicant: Sierra Nevada Corporation

Inventor： Jake Crine ,  Benjamin Paul Cunningham ,  Alec B. Devereaux ,  Sonny J. Lewis ,  Jonathan Peritt

IPC: F16H19/02 ,  F16H57/08

CPC classification number: F16H19/02 ,  B64C3/56 ,  B64C2201/102 ,  F16H25/2252 ,  F16H57/082

Abstract: An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

公开(公告)号：US20180273170A1

公开(公告)日：2018-09-27

申请号：US15927847

申请日：2018-03-21

Applicant: Regents of the University of Minnesota

Inventor： Ruben Raphael D'Sa ,  Nikolaos Papanikolopoulos ,  Devon Jenson ,  Travis Henderson ,  John Kilian

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/56 ,  B64C3/32 ,  B64D27/24 ,  B64C11/30 ,  B64C13/18

CPC classification number: B64C29/02 ,  B64C3/32 ,  B64C3/56 ,  B64C11/30 ,  B64C13/18 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/102 ,  B64C2201/162 ,  B64C2201/165 ,  B64D27/24 ,  B64D2211/00

Abstract: An unmanned aerial vehicle (UAV) including wing sections and hinge assemblies. Each wing section includes an airfoil and a propulsion unit. The wing sections are arranged side-by-side, pivotably connected by the hinge assemblies to define an airframe module. The airframe module is transitionable between a fixed-wing state and a rotor state. In the fixed-wing state, the airframe module has an elongated shape extending between opposing, first and second ends. In the rotor state, the first end is immediately proximate the second end. With this construction, the UAV provides two distinct modes of flight (fixed-wing for low power flight, and rotor for high maneuverability flight (including hover)). The wing sections can carry solar cells and a battery. A maximum power point tracker (MPPT) can be provided for optimizing the match between the solar array and the battery. The propulsion unit can include a variable pitch propeller.

公开(公告)号：US20180273166A1

公开(公告)日：2018-09-27

申请号：US15995419

申请日：2018-06-01

Applicant: Paul E. ARLTON ,  David J. ARLTON

Inventor： Paul E. ARLTON ,  David J. ARLTON

IPC: B64C27/605 ,  B64C27/10 ,  B64C27/14 ,  B64C39/02 ,  B64C7/00 ,  B64C27/82

CPC classification number: B64C27/605 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2027/8281 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：US20180244402A1

公开(公告)日：2018-08-30

申请号：US15755699

申请日：2016-08-25

Applicant: UVISION AIR LTD

Inventor： MOSHE KAHLON ,  SHLOMO HAKIM

IPC: B64F1/04 ,  B64C39/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/201

Abstract: A launcher for unmanned aerial vehicles (UAV), the launcher having a foldable UAV stowed within said launcher, the launcher includes, a launch tube configured as a UAV launcher and a UAV carrying case. The launcher further includes a pneumatic booster connected to said UAV for accelerating said UAV during launching phase. The launcher further includes a separation mechanism operated to permits separation of the booster from the UAV when the UAV leaves the launcher tube and to transfer the kinetic energy that is created from the pneumatic booster to the UAV in the launching phase. The UAV is propelled off of the launch tube by the booster that transmits thrust in the launch tube to the space below said booster. The UAV which is connected to the booster by the separation mechanism is pushed out of the launcher tube body and leaves the launch tube, the booster is separated from the UAV by the separation mechanism and the UAV is automatically deployed. The UAV propellers are activated to propel the UAV and driven the UAV.

公开(公告)号：US20180134369A1

公开(公告)日：2018-05-17

申请号：US15854773

申请日：2017-12-27

Applicant: Haoxiang Electric Energy (Kunshan)Co., Ltd.

Inventor： Yu Tian ,  Wenyan Jiang

IPC: B64C1/30 ,  B64C39/02

CPC classification number: B64C1/30 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108

Abstract: An arm linkage foldable device for a UAV (unmanned aerial vehicle) includes a linkage module and two connection modules. The linkage module includes a guided structure and a slider. The slider slides along the guided structure. Two aircraft arms located at two sides of the fuselage are respectively connected with two sides of a slider through the two connection modules, a joint of every connection module and the slider is rotatable. A protruding portion is located on every connection module, a slide groove is provided on the fuselage corresponding to the protruding portion, the protruding portion is inserted into the slide groove and slides along the slide groove. The slider moves along the guided structure to drive one connection module to move, the connection module drives one aircraft arm to move with the slider and rotate relatively to the slider, so that the aircraft is unfolded or folded.

公开(公告)号：US20180086454A1

公开(公告)日：2018-03-29

申请号：US15567586

申请日：2016-04-20

Applicant: George Michael Cook ,  Jonathan Edward Cook ,  Michael Kevin Cook

Inventor： George Michael Cook ,  Jonathan Edward Cook ,  Michael Kevin Cook

IPC: B64C39/02 ,  B64C13/30

CPC classification number: B64C13/30 ,  B64C1/061 ,  B64C3/56 ,  B64C13/28 ,  B64C31/02 ,  B64C39/024 ,  B64C2001/0054 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2211/00

Abstract: An aerial delivery assembly for autonomously delivering a load to a target location, the assembly comprising an airframe which comprises a main body, at least one deployable lift providing structure, the lift providing structure being moveable between a stowed position and a deployed position; and at least one deployable and adjustable control structure for controlling the flight of the assembly and moveable between a stowed position and a deployed position. The main body comprises a compartment for receiving a load to be delivered. The assembly further comprises a control unit comprising an actuation module for use in adjusting the control structure, wherein the control unit is releaseably connected to the airframe such that it is reusable in an aerial delivery assembly having a different airframe.

公开(公告)号：US09902488B2

公开(公告)日：2018-02-27

申请号：US15388396

申请日：2016-12-22

Applicant: Area- I Inc.

Inventor： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC: B64C3/54 ,  B64C39/02 ,  B64C13/30 ,  B64C3/56

CPC classification number: B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：US20170369150A1

公开(公告)日：2017-12-28

申请号：US15608758

申请日：2017-05-30

Applicant: SIERRA NEVADA CORPORATION

Inventor： Ken FINKLEA ,  Carlos MIRALLES

IPC: B64C3/56 ,  B64D17/80 ,  B64C39/02

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206 ,  B64C2201/208 ,  B64D17/80

Abstract: In one embodiment, a wing for an unmanned aerial vehicle is described. The unmanned aerial vehicle includes a first body of the wing with a first end proximate a body of the vehicle. A second end is opposite the first end. A first joint is on the first end of the first main body of the wing. The joint rotatably couples the wing to the vehicle. A second joint is on the second end of the vehicle. A second body of the wing is rotatably coupled to the first body via the second joint.

公开(公告)号：US20170291686A1

公开(公告)日：2017-10-12

申请号：US15388433

申请日：2016-12-22

Applicant: Area- I Inc.

Inventor： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC: B64C5/12 ,  B64C3/56 ,  B64C3/54 ,  B64C39/02 ,  B64C5/02

CPC classification number: B64C3/40 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2211/00

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.