公开(公告)号：US20180244377A1

公开(公告)日：2018-08-30

申请号：US15757282

申请日：2016-09-01

Applicant: Joy Yin Chan

Inventor： Joy Yin Chan

IPC: B64C27/08 ,  B64C27/605 ,  B64D35/04 ,  B64C27/12 ,  B64C39/02

CPC classification number: B64C27/08 ,  B64C27/12 ,  B64C27/14 ,  B64C27/605 ,  B64C27/68 ,  B64C27/80 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/108 ,  B64D35/04 ,  B64D35/06

Abstract: A multi-rotor flying machine includes a body on or in which a motor is mounted; and a respective head rotor mounted for rotation on a respective mast at each of at least three locations disposed around and spaced laterally outwardly from the motor. The motor is drivingly connected to each mast, for rotating each head rotor, by a respective driveline. Adjacent to at least one mast, the machine further includes a pitch rudder system that includes a pitch driver or rotor, or translational rotor. The arrangement is such that the head rotors are operable to provide thrust, while the pitch rudder system enables yaw to be achieved independently of operation of the head rotors.

公开(公告)号：US09969486B1

公开(公告)日：2018-05-15

申请号：US15188922

申请日：2016-06-21

Applicant: Amazon Technologies, Inc.

Inventor： Barry James O'Brien ,  Scott Michael Wilcox ,  Joshua John Watson

IPC: B64C13/20 ,  G01J5/52 ,  G05D1/06 ,  B64C39/02 ,  B64D47/08 ,  G01C25/00 ,  G01K15/00 ,  G01K13/00 ,  G06K9/62

CPC classification number: B64C13/20 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/145 ,  B64D47/08 ,  G01C25/00 ,  G01J5/522 ,  G01K13/00 ,  G01K15/00 ,  G05D1/0653 ,  G06K9/6202 ,  G06T2207/10024 ,  G06T2207/10032

Abstract: This disclosure describes systems, methods, and apparatus for automating the verification of aerial vehicle sensors as part of a pre-flight, flight departure, in-transit flight, and/or delivery destination calibration verification process. At different stages, aerial vehicle sensors may obtain sensor measurements about objects within an environment, the obtained measurements may be processed to determine information about the object, as presented in the measurements, and the processed information may be compared with the actual information about the object to determine a variation or difference between the information. If the variation is within a tolerance range, the sensor may be auto adjusted and operation of the aerial vehicle may continue. If the variation exceeds a correction range, flight of the aerial vehicle may be aborted and the aerial vehicle routed for a full sensor calibration.

公开(公告)号：US20180115265A1

公开(公告)日：2018-04-26

申请号：US15787911

申请日：2017-10-19

Applicant: Top Flight Technologies, Inc.

Inventor： Samir Nayfeh ,  Julian Lemus ,  Soojae Jung ,  Matthew Sweetland ,  Long N. Phan

IPC: H02P6/34 ,  H02P9/04 ,  H02K11/24 ,  B64C39/02 ,  B64D27/24 ,  B64F5/60 ,  B60K6/26 ,  B60K6/24 ,  B60K6/40 ,  B60W20/10

CPC classification number: H02P6/34 ,  B60K6/24 ,  B60K6/26 ,  B60K6/40 ,  B60W20/10 ,  B60W2050/0026 ,  B60Y2200/50 ,  B60Y2200/92 ,  B60Y2300/60 ,  B60Y2400/604 ,  B60Y2400/61 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D27/24 ,  B64D2027/026 ,  B64F5/60 ,  F16C1/02 ,  G01L5/13 ,  G01M15/04 ,  G01M15/05 ,  H02K11/24 ,  H02P9/04 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/905 ,  Y10S903/906 ,  Y10S903/951

Abstract: A system includes a torque sensor; and a hybrid power system. The hybrid power sensor includes a frame; an engine mounted on the frame; and a generator, the generator including: a generator rotor mechanically coupled to a shaft of the engine; and a generator stator coupled to the frame by the torque sensor. The torque sensor is configured to measure a torque on the generator stator.

公开(公告)号：US09902493B2

公开(公告)日：2018-02-27

申请号：US15550392

申请日：2016-02-08

Applicant: HUTCHINSON

Inventor： Jean-Michel Simon ,  Christophe Dominiak ,  Sebastien Andre

IPC: B64C27/08 ,  B64C29/00 ,  B64D35/06 ,  B64C39/02

CPC classification number: B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64D35/06 ,  B64D35/08

Abstract: Disclosed is an aerodyne including a supporting structure, to which are connected: at least one supporting axial blower, attached to the supporting structure; at least one main engine driving the supporting blower; at least three attitude blowers controlling roll and pitch, each attitude blower having an electrical motor and being attached, respectively, to one of the elongate arms that are distributed in a laterally, outwardly projecting manner around the supporting structure, to which each arm is connected by an inner end portion, the axis of rotation of each attitude blower being attached relative to the supporting structure, and all the attitude blowers being located outside the space centrally occupied by the supporting blower; at least one battery for supplying power to the electrical motors of the attitude blowers; a landing gear attached under the supporting structure; and a nacelle for holding the battery and a payload.

公开(公告)号：US09896200B2

公开(公告)日：2018-02-20

申请号：US15332391

申请日：2016-10-24

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： William J. Fredericks ,  Mark D. Moore ,  Ronald C. Busan ,  Paul M. Rothhaar ,  David D. North ,  William M. Langford ,  Christopher T. Laws ,  William T. Hodges ,  Zachary R. Johns ,  Sandy R. Webb

IPC: B64C29/00 ,  B64C39/00 ,  B64C11/28 ,  B64C25/52 ,  B64D27/24 ,  B64C3/40 ,  B64C9/14 ,  B64D27/26 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64C39/02 ,  B64C5/02 ,  B64D27/02

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

公开(公告)号：US09878786B2

公开(公告)日：2018-01-30

申请号：US14630114

申请日：2015-02-24

Applicant: Elwha LLC

Inventor： Alistair K. Chan ,  Jesse R. Cheatham, III ,  Hon Wah Chin ,  William David Duncan ,  Roderick A. Hyde ,  Muriel Y. Ishikawa ,  Jordin T. Kare ,  TOny S. Pan ,  Robert C. Petroski ,  Clarence T. Tegreene ,  David B. Tuckerman ,  Thomas Allan Weaver ,  Lowell L. Wood, Jr.

IPC: B64C27/00 ,  B64C39/02 ,  B64C27/08 ,  B64C27/52 ,  B64D27/26 ,  B64D47/08

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/52 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/128 ,  B64D27/26 ,  B64D47/08

Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission.

公开(公告)号：US20180022452A1

公开(公告)日：2018-01-25

申请号：US15693859

申请日：2017-09-01

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64C39/02 ,  B64C27/08 ,  B64D1/08 ,  G05D1/10 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64F3/02 ,  B64C27/00 ,  B64D1/22

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

公开(公告)号：US20170300066A1

公开(公告)日：2017-10-19

申请号：US15131914

申请日：2016-04-18

Applicant: LATITUDE ENGINEERING, LLC

Inventor： Jason Michael K. Douglas ,  Justin Armer ,  Carlos Murphy

IPC: G05D1/08 ,  B64C29/00 ,  B64C39/02

CPC classification number: G05D1/0816 ,  B64C29/0008 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G05D1/0833 ,  G05D1/0858

Abstract: An unmanned aircraft includes a forward propulsion system comprising one or more forward thrust engines and one or more corresponding rotors coupled to the forward thrust engines; a vertical propulsion system comprising one or more vertical thrust engines and one or more corresponding rotors coupled to the vertical thrust engines; a plurality of sensors; and a yaw control system, that includes a processor configured to monitor one or more aircraft parameters received from at least one of the plurality of sensors and to enter a free yaw control mode based on the received aircraft parameters.

公开(公告)号：US20170297733A1

公开(公告)日：2017-10-19

申请号：US15278309

申请日：2016-09-28

Applicant: Ewatt Technology Co., Ltd.

Inventor： Guocheng ZHAO ,  Wei LUO ,  Pengcheng QI

IPC: B64D33/02 ,  B64C39/02 ,  F02K1/34 ,  B64D33/08 ,  B64D27/08 ,  B64C27/82

CPC classification number: B64D33/02 ,  B64C27/82 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/141 ,  B64C2201/146 ,  B64D27/08 ,  B64D33/06 ,  B64D33/08 ,  B64D2033/0246 ,  B64D2033/028

Abstract: The present invention discloses an unmanned helicopter, and belongs to the technical field of unmanned aerial vehicles. The unmanned helicopter includes an air inlet system, an exhaust system, a cooling system and a dynamic balance system. The air inlet system is fixed on a second side; the exhaust system is fixed on a third side; and the cooling system is fixed on a first side, and the dynamic balance system is fixed on a tail. The airflow at the outside of the unmanned helicopter flows into the air inlet system smoothly, quickly and efficiently under the action of its own flow velocity relative to the unmanned helicopter, therefore the technical problem in the prior art that the air entering the fuselage with a unit volume is burnt insufficiently, which generates adverse effects on the normal flight of the unmanned helicopter, is solved.

公开(公告)号：US20170138281A1

公开(公告)日：2017-05-18

申请号：US15319948

申请日：2015-06-23

Applicant: ORBITAL AUSTRALIA PTY LTD

Inventor： Tyron Dean UTLEY ,  Nicolass Harry BUTERS ,  Jayesh NARAYAN

IPC: F02D41/00 ,  B64C39/02 ,  H02K11/21 ,  F02D41/22

CPC classification number: F02D41/009 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/044 ,  F02D41/222 ,  F02D2200/101 ,  F02D2400/08 ,  H02K11/21 ,  Y02T10/40

Abstract: Redundancy in engine timing position sensing maintains a UAV operational in the event of failure of a primary engine timing position sub-system. The redundancy avoids duplication of the primary crankshaft timing position sensing components, and avoids adding weight, cost and component complexity. Conditioned (square) waveform(s) (102) is/are created from respective sinusoidal waveform(s). Each consecutive leading edge (103a) and trailing edge (103b) of the pulses of the square waveform (102) is derived from the crossing of the zero voltage value by consecutive sinusoidal waveforms A,B,C (e.g. Voltage (V) vs Time (t) or angular degrees). The square pulse waveform (102) is output (104) to a microcontroller (106) to create and output a pseudo crankshaft timing position signal (108) to be used by an ECU to determine ignition and fuel injection events in the event that the primary timing signal from the crankshaft position sensor (CPS) has failed. The signal (108) output to the ECU can have a missing pulse (116) (i.e. indicative of a TDC position of the engine crankshaft) as well as multiple square pulses (114) corresponding to the pulses of the initial square pulse waveform (102). The waveform signal (108) is therefore derived from the alternator waveform signal(s) and provides a pseudo crankshaft timing position signal in the event of failure of the primary or initial CPS signal.