公开(公告)号：US10059436B1

公开(公告)日：2018-08-28

申请号：US15783898

申请日：2017-10-13

申请人： Kitty Hawk Corporation

发明人： Cameron Robertson ,  Todd Reichert

IPC分类号： B64C25/54 ,  B64C27/08 ,  B64D17/80 ,  B64D27/24 ,  B64C25/36 ,  B64C31/028 ,  B64C25/32

CPC分类号： B64C25/54 ,  B64C25/36 ,  B64C27/001 ,  B64C27/08 ,  B64C31/028 ,  B64C35/00 ,  B64C35/008 ,  B64C2025/325 ,  B64D17/80 ,  B64D27/24

摘要： A float has a front-to-back length, a width, and a height where the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float. At least a bottom portion of the float is watertight. The float includes an access panel to access the inside of the float. A battery is inside the float and is accessible via the access panel.

公开(公告)号：US20180162552A1

公开(公告)日：2018-06-14

申请号：US15879166

申请日：2018-01-24

申请人： Kitty Hawk Corporation

发明人： Zachais Vawter ,  Todd Reichert

IPC分类号： B64D45/04 ,  G05D1/10 ,  B64D17/72 ,  B64D1/10 ,  B64D1/12 ,  B64D25/08 ,  B64D17/80 ,  B64C39/02 ,  B64D45/00

CPC分类号： B64D45/04 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/185 ,  B64D1/10 ,  B64D1/12 ,  B64D17/725 ,  B64D17/80 ,  B64D25/08 ,  B64D2045/008 ,  G05D1/101

摘要： A ballistic parachute associated with an aircraft is deployed where the aircraft includes a first part and a second part, the two parts are detachably coupled to each other when the ballistic parachute is deployed, and the ballistic parachute is coupled to the first part of the aircraft. A landing zone associated with the second part of the aircraft is determined and it is decided whether to decouple the two parts, including by deciding whether the landing zone associated with the second part of the aircraft is inhabited. If it is decided to decouple the two parts from each other, they are decoupled from each other.

公开(公告)号：US20180155038A1

公开(公告)日：2018-06-07

申请号：US15368108

申请日：2016-12-02

申请人： Joseph Miller ,  Caroline Jackson

发明人： Joseph Miller ,  Caroline Jackson

IPC分类号： B64D17/80 ,  B64C25/56

CPC分类号： B64D17/80 ,  B64C25/56

摘要： An aircraft parachute system includes an aircraft that has a fuselage, a pair of wings, a tail section and a plurality of engines. A plurality of parachute units is provided and each of the parachute units is coupled to the aircraft. Each of the parachute units is selectively deployed when the aircraft experiences an in-flight emergency such that the plurality of parachute units inhibits the aircraft from crashing. A plurality of balloon units is provided and each of the balloon units is coupled to the aircraft. Each of the balloon units is selectively deployed when the aircraft experiences the in-flight emergency. In this way each of the balloon units floats the aircraft in water when the aircraft lands in water.

公开(公告)号：US09981749B1

公开(公告)日：2018-05-29

申请号：US15783909

申请日：2017-10-13

申请人： Kitty Hawk Corporation

发明人： Peter A. Swan ,  Craig Western ,  Damon Vander Lind ,  Amy Qian

IPC分类号： B64D17/72 ,  B64D17/80

CPC分类号： B64D17/725 ,  B64D17/80

摘要： A parachute system includes a parachute which is coupled to a rocket via a first load path, which includes a tow line, one or more upper parachute lines, and one or more lower parachute lines, and a second load path, which includes a release line. The rocket is configured to tow the parachute via the tow line. There is a lower parachute line restrainer which when released permits the lower parachute lines to extend to full length. There is also a release which is configured to open in the event a load switches from the first load path to the second load path; when the release is open, the parachute and the rocket are permitted to separate.

公开(公告)号：US09944389B2

公开(公告)日：2018-04-17

申请号：US15476612

申请日：2017-03-31

申请人： Piasecki Aircraft Corporation

发明人： John W. Piasecki ,  Frederick W. Piasecki ,  Brian Geiger ,  Douglas Johnson ,  David Pitcairn

IPC分类号： B64C37/00 ,  B64C29/00 ,  B60F5/02 ,  B64C11/00 ,  B64C27/08 ,  B64C27/20 ,  B64C27/22 ,  B64C27/57 ,  B64D17/80 ,  B64C39/02 ,  B64C3/56 ,  G05D1/10

CPC分类号： B64C37/00 ,  B60F5/02 ,  B64C3/385 ,  B64C3/56 ,  B64C11/001 ,  B64C25/58 ,  B64C27/08 ,  B64C27/20 ,  B64C27/22 ,  B64C27/32 ,  B64C27/52 ,  B64C27/57 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/00 ,  B64C39/02 ,  B64D17/80 ,  B64D25/00 ,  B64D2201/00 ,  G05D1/102

摘要： An air module may be attached to a ground module. The air module may be equipped with a center of gravity effector to change the relative locations and hence the center of gravity of the air and ground modules when the modules are attached. The center of gravity effector may be active or passive or a combination of active and passive. The center of gravity effector may be combined with a center of lift effector to change the relative locations of the center of gravity and center of lift.

公开(公告)号：US20170371332A1

公开(公告)日：2017-12-28

申请号：US15698303

申请日：2017-09-07

申请人： SkyCat Oy

发明人： Henri Hiisilä ,  Janne Laurinen

IPC分类号： G05D1/00 ,  B64C19/00 ,  B64C39/02 ,  G08C17/02 ,  A63H30/04 ,  A63H33/20 ,  B64D17/80

CPC分类号： G05D1/0022 ,  A63H30/04 ,  A63H33/20 ,  B64C19/00 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80 ,  G05D1/0055 ,  G08C17/02

摘要： The present invention relates to a method for replacing a signal controlling an actuator in a remote-controlled flying device with another signal. A flight controller supplies control signals to a safety device, and the signal to be replaced may be a signal to be transmitted by the safety device to a speed controller of at least one motor, or to a servo unit controlling the same, or the signal to be replaced may be a signal to be transmitted from the safety device to a servo unit controlling legs, a camera rack, a camera, a stabilizing system or an electric motor of the flying device. A replacement signal is a signal stored in a memory of the safety device. The replacement signal may be capable of controlling the speed controller directly or via the servo unit, in such a way that power transmission to said motor/motors is stopped or reduced, and this motor is/these motors are switched off or its/their rotation is decelerated, or the replacement signal may be capable of controlling said servo unit in such a way that said actuator is moved to a second position. The replacement signal may be a signal to be transmitted from a receiver past a flight controller, capable of controlling the speed controller or servo unit of the motor in such a way that power transmission to the motor is stopped or reduced, or to control said actuator in such a way that this actuator is moved to another position.

公开(公告)号：US20170267348A1

公开(公告)日：2017-09-21

申请号：US15612989

申请日：2017-06-02

申请人： Flirtey Holdings, Inc.

发明人： Matthew Sweeny ,  John Elverum ,  John Foggia

IPC分类号： B64D1/22 ,  B65D25/22 ,  B65D5/50 ,  B65D81/38 ,  B65D5/10 ,  A47J47/14 ,  B64C39/02 ,  B65D25/34

CPC分类号： B65D5/5007 ,  A47J47/14 ,  B64C25/58 ,  B64C39/024 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/70 ,  B64D17/80 ,  B65D5/10 ,  B65D25/22 ,  B65D25/34 ,  B65D81/3813

摘要： Certain aspects of the technology disclosed involve a container for delivery by drone (e.g., an unmanned aerial vehicle). The container can include a coupling mechanism to lock and unlock a package attached to the drone based on a tension applied to the coupling mechanism. The package can include sidewalls affixed to a top wall. The sidewalls can include securing mechanisms to be secured to a bottom wall of the container. A rigid extremity can be a contiguous extension of any of the sidewalls and extend below a lower surface of the sidewalls. The rigid extremity can include a malleable contour proximate to a corner of the container. The malleable contour can extend from a base of the rigid extremity through the sidewall. An aperture in the top wall can be configured for a inserting member of a coupling mechanism.

公开(公告)号：US20170235018A1

公开(公告)日：2017-08-17

申请号：US15401999

申请日：2017-01-09

申请人： Pictometry International Corp.

发明人： Mark A. Foster ,  Frank Giuffrida ,  Antony Parchment

IPC分类号： G01V99/00 ,  B64D47/08 ,  G06F17/30 ,  B64C39/02

CPC分类号： G01V99/005 ,  B64C39/024 ,  B64C2201/123 ,  B64C2201/127 ,  B64D17/80 ,  B64D45/00 ,  B64D47/08 ,  B64D2201/00 ,  G05D1/0094 ,  G05D1/101 ,  G06F3/04817 ,  G06F16/5866 ,  G06T7/70 ,  G06T2207/10032

摘要： A method comprising receiving aerial images captured by one or more unmanned aerial vehicle; receiving metadata associated with the aerial images captured by the one or more unmanned aerial vehicle; geo-referencing the aerial images based on a geographic location of a surface to determine geographic coordinates of pixels of the aerial images; receiving a geographic location from a user; retrieving one or more of the aerial images associated with the geographic location based on the determined geographic coordinates; and displaying to the user one or more overview image depicting the geographic location and overlaid with one or more icons indicative of and associated with the retrieved aerial images associated with the geographic location.

公开(公告)号：US20170158327A1

公开(公告)日：2017-06-08

申请号：US15370592

申请日：2016-12-06

申请人： AAI Corporation

发明人： Neal H. Willford

IPC分类号： B64C39/02 ,  B64C29/02 ,  B64C25/34 ,  B64D17/80 ,  G05D1/08 ,  G05D1/00

CPC分类号： B64C39/024 ,  B64C25/34 ,  B64C27/50 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D17/80 ,  G05D1/0055 ,  G05D1/0816 ,  G05D1/0858

摘要： A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing-plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path that is perpendicular to the horizontal flight path.

公开(公告)号：US09637238B2

公开(公告)日：2017-05-02

申请号：US14656648

申请日：2015-03-12

申请人： Aaron Wypyszynski

发明人： Aaron Wypyszynski

IPC分类号： B65D3/00 ,  B65D47/00 ,  B64D17/80 ,  B64D3/00 ,  B64C39/02 ,  B64C31/028

CPC分类号： B64D17/80 ,  B64C31/028 ,  B64C39/026 ,  B64D3/00

摘要： A system for airboarding and performing stunts behind an aircraft includes a lifting board, a handle, and a tow rope connected to the board and handle. The lifting board may include landing gear, a binding for securing an operator to the board, tail sections for stabilizing the board during flight, and ailerons for facilitating turns and rolls. The system may include a control system integrated into the handle and board that improves the operator's ability to control the board.