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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
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.
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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
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.
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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
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.
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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
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.
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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
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.
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Patent Agency Ranking
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
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.
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公开(公告)号：US09776715B2
公开(公告)日：2017-10-03
申请号：US15350458
申请日：2016-11-14
Applicant: Andrew H B Zhou , Dylan T X Zhou , Tiger T G Zhou
Inventor： Andrew H B Zhou , Dylan T X Zhou , Tiger T G Zhou
IPC: B64C35/00 , B60F5/02 , B64C29/00 , B64C39/02 , G05D1/04 , B64C37/00 , G05D1/08 , G08G5/04 , B60R11/04 , B60K16/00
CPC classification number: B64C35/008 , B60F5/02 , B60K16/00 , B60K2016/003 , B60R11/04 , B64C29/0033 , B64C29/0066 , B64C29/0075 , B64C37/00 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/141 , B64C2201/162 , G05D1/0816 , G05D1/0858 , G08G5/04
Abstract: An amphibious vertical takeoff and landing (VTOL) unmanned device is provided. The amphibious VTOL unmanned device includes a modular and expandable waterproof body, an outer body shell, a gimbaled swivel propulsion system comprising a plurality of VTOL jet engines and VTOL ducted fans, a processor, electronic speed controllers, a two-way telemetry device, a video transmitter, a radio control receiver, a power distribution board, an electrical machine, an onboard electricity generator comprising a plurality of solar cells, a light detection and ranging device, an ultrasonic radar sensor, a plurality of sensors, a tail configured to stabilize the amphibious VTOL unmanned device, a head VTOL ducted fan adapted for VTOL, a plurality of wheels, a plurality of foldable wings configured to create a pressure difference and creating a lift, a plurality of parachutes configured to safely land the amphibious VTOL unmanned device in an emergency.
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公开(公告)号：US20170260973A1
公开(公告)日：2017-09-14
申请号：US15065185
申请日：2016-03-09
Applicant: Northrop Grumman Systems Corporation
Inventor： Gregory L. Larson , Peter A. Barnett
CPC classification number: F03G7/065 , B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/082 , B64C2201/102 , B64D5/00 , B64D7/00
Abstract: An exemplary rotational assembly includes a base having a circular collar and first and second arms that rotate about the circular collar in opposite angular directions. In a stored state the arms have substantially the same angle relative to the circular collar; in a deployed state the arms have rotated into opposing positions. Each end of a Nitinol wire is coupled to the first and second arms and contracts when heated by the flow of electrical current. This contraction causes the simultaneously application of a rotational force to the first and second arms causing the first and second arms to rotate about the circular collar in opposite angular directions. The simultaneous counter rotating angular forces during rotation of the arms causes no substantial change in angular inertia at the base.
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公开(公告)号：US20170240276A1
公开(公告)日：2017-08-24
申请号：US15503470
申请日：2015-08-11
Applicant: ALMOG RESCUE SYSTEMS LTD.
Inventor： Ariel Zilberstein
CPC classification number: B64C31/02 , A62C3/0242 , A62C3/025 , B64C39/024 , B64C2201/102 , B64C2201/128 , B64C2201/201 , B64C2201/206 , B64D1/10 , B64D1/16 , B64D5/00
Abstract: A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.
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公开(公告)号：US09682774B2
公开(公告)日：2017-06-20
申请号：US14507313
申请日：2014-10-06
Applicant: Aurora Flight Sciences Corporation
Inventor： James Donald Paduano , Paul Nils Dahlstrand , John Brooke Wissler , Adam Woodworth
IPC: B64C13/16 , B64C27/52 , B64C29/04 , B64C29/02 , B64C39/02 , B64C29/00 , B64C3/42 , B64C5/02 , B64C9/00 , B64C25/10 , B64D27/02 , B64D43/00
CPC classification number: B64C27/52 , B64C3/42 , B64C5/02 , B64C9/00 , B64C13/16 , B64C25/10 , B64C29/00 , B64C29/0033 , B64C29/0091 , B64C29/02 , B64C29/04 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/102 , B64C2201/108 , B64C2201/162 , B64C2201/187 , B64D27/02 , B64D43/00
Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.
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