公开(公告)号：US11433093B2

公开(公告)日：2022-09-06

申请号：US16528672

申请日：2019-08-01

申请人： John Stevens George

发明人： John Stevens George

IPC分类号： B64C27/02 ,  B64C27/24 ,  B64D27/00 ,  A61K31/728 ,  C12N7/00 ,  A61K31/7105 ,  C12N15/86 ,  A61K9/14 ,  A61K48/00 ,  B64D27/24 ,  B82Y5/00 ,  B64D27/02

摘要： A gyroplane employing torque compensated main rotor and hybrid power train is disclosed. The invention incorporates a torque-compensated main rotor system with a common Collective pitch control, which can be driven transiently during flight to allow Vertical Take-Off, Landing and Hovering (VTOLH) flight operations. Torque compensation is via a coaxial counter-rotating (CACR) rotor system, or alternatively using a single rotor in conjunction with one or more electronically-controlled, fixed-pitch, thruster motors. The use of electric motors for lift and torque compensation facilitates electronic and potentially autonomous control of all phases of vertical flight.

公开(公告)号：US11353889B1

公开(公告)日：2022-06-07

申请号：US17348869

申请日：2021-06-16

申请人： BETA AIR, LLC

发明人： Collin Freiheit

IPC分类号： G01D1/00 ,  B64C39/02 ,  G07C5/00 ,  B64D27/00 ,  G05D1/10 ,  G07C5/08 ,  G06N20/00 ,  G05D1/00

摘要： A system for electric aircraft navigation includes a sensor configured to detect a navigation signal, a flight controller, wherein the flight controller is configured to receive the navigation signal, identify a navigation status as a function of the navigation signal, and determine an aircraft adjustment as a function of the navigation status, and a pilot display, wherein the pilot display is configured to display the aircraft adjustment to a user, and present an autonomous function configured to enact the aircraft adjustment automatically.

公开(公告)号：US11220170B2

公开(公告)日：2022-01-11

申请号：US16919046

申请日：2020-07-01

申请人： AeroVironment, Inc.

发明人： Christopher E. Fisher ,  Phillip T. Tokumaru ,  Marc L. Schmalzel ,  John Peter Zwaan ,  Jeremy D. Tyler ,  Justin B. McAllister ,  Gabriel E. Torres ,  Pavel Belik

IPC分类号： B64C39/00 ,  B60K1/04 ,  B60K1/00 ,  B64D27/00 ,  B63H21/17 ,  B63G8/08 ,  B60K7/00 ,  B60K17/356 ,  A63H27/00 ,  B64C27/00 ,  B64C39/02 ,  B64D27/24 ,  B63B35/00 ,  B63G8/00

摘要： A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

公开(公告)号：US11117004B2

公开(公告)日：2021-09-14

申请号：US15860791

申请日：2018-01-03

申请人： The Boeing Company

发明人： Scott M. Livingston ,  Jack W. Mauldin ,  Robert P. Lotter ,  Paul B. Philipp ,  Khalid S. Alshobber ,  John N. Harris

IPC分类号： A62C3/08 ,  B64D27/00 ,  B64D45/00 ,  F16J15/02 ,  F16J15/06 ,  B64C1/10 ,  B64C1/16 ,  A62C2/06 ,  A62C99/00 ,  F02K1/78 ,  F16L55/10

摘要： A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

公开(公告)号：US11046424B2

公开(公告)日：2021-06-29

申请号：US15506937

申请日：2015-08-28

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Clement Marcel Maurice Dejeu ,  Jonathan Evert Vlastuin ,  Mathieu Simon Paul Gruber

IPC分类号： B64C11/06 ,  B64C11/48 ,  B64C11/30 ,  F02K3/072 ,  F01D1/26 ,  F01D7/00 ,  B64D27/00 ,  F04D29/36

摘要： A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

公开(公告)号：US20210188451A1

公开(公告)日：2021-06-24

申请号：US17173110

申请日：2021-02-10

申请人： SZ DJI TECHNOLOGY CO., LTD.

发明人： Tong WANG ,  Tao LIN

IPC分类号： B64D27/00 ,  H02J7/00 ,  G06F1/26 ,  B64C39/02

摘要： A power supply method includes when detecting that a host apparatus is connected to an external apparatus via a connector, determining a maximum voltage value supported by the external apparatus, and selecting a first power supply circuit or a second power supply circuit to supply power to the external apparatus according to the maximum voltage value. A first power supply voltage value of the first power supply circuit is greater than a second power supply voltage value of the second power supply circuit.

公开(公告)号：US10907544B2

公开(公告)日：2021-02-02

申请号：US14665081

申请日：2015-03-23

申请人： United Technologies Corporation

发明人： Dmytro Mykolayovych Voytovych ,  Om P. Sharma

IPC分类号： F02C7/04 ,  B64D27/00 ,  F01D5/02 ,  B64D33/02 ,  B64D27/14 ,  B64C39/10

摘要： A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.

公开(公告)号：US20210001700A1

公开(公告)日：2021-01-07

申请号：US16919046

申请日：2020-07-01

申请人： AeroVironment, Inc.

发明人： Christopher E. Fisher ,  Phillip T. Tokumaru ,  Marc L. Schmalzel ,  John Peter Zwaan ,  Jeremy D. Tyler ,  Justin B. McAllister ,  Gabriel E. Torres ,  Pavel Belik

IPC分类号： B60K1/04 ,  B60K1/00 ,  B64D27/00 ,  B63H21/17 ,  B63G8/08 ,  B60K7/00 ,  B60K17/356 ,  A63H27/00 ,  B64C27/00 ,  B64C39/02 ,  B64D27/24

摘要： A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

公开(公告)号：US10737796B2

公开(公告)日：2020-08-11

申请号：US15182860

申请日：2016-06-15

申请人： SNECMA

发明人： Mathieu Simon Paul Gruber ,  Timothy Delteil McWilliams

IPC分类号： B64D27/20 ,  B64D29/06 ,  B64C21/04 ,  B64D27/26 ,  F02C6/20 ,  F02C7/045 ,  B64D29/04 ,  B64D27/00

摘要： A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented.

公开(公告)号：US10710734B2

公开(公告)日：2020-07-14

申请号：US15689992

申请日：2017-08-29

申请人： The Boeing Company

发明人： Mithra M. K. V. Sankrithi

IPC分类号： B64D27/00 ,  B64D27/24 ,  B64D41/00 ,  F02K3/06 ,  F01D15/10 ,  H02K7/18 ,  B64C11/30 ,  B64D27/16 ,  F02K5/00 ,  F02K3/072 ,  B64D27/02 ,  F02K1/66

摘要： Hybrid aircraft propulsors having electrically-driven augmentor fans are disclosed. An example apparatus includes a turbofan having a core engine and a ducted fan to be rotated via the core engine. The ducted fan includes a plurality of ducted fan blades arranged circumferentially around the core engine and circumscribed by a nacelle. The example apparatus further includes an augmentor fan having an augmentor hub ring and a plurality of augmentor fan blades. The augmentor fan blades are arranged circumferentially around the augmentor hub ring and project outwardly relative to an outer surface of the nacelle. The augmentor fan is to rotate separately from the ducted fan. The example apparatus further includes an electrical drive to rotate the augmentor hub ring in response to a supply of electrical energy provided to the electrical drive.