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公开(公告)号：US20180244386A1
公开(公告)日：2018-08-30
申请号：US15893992
申请日：2018-02-12
Applicant: Top Flight Technologies, Inc.
Inventor： Long N. Phan
CPC classification number: B64C39/024 , B64C27/12 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/108 , B64C2201/125 , B64C2201/127 , B64C2201/141 , B64C2201/162 , B64C2201/165 , B64C2201/208 , B64D2027/026 , G01W1/02 , G01W1/08 , G08G5/0069 , G08G5/0091
Abstract: An unmanned aerial vehicle includes an atmospheric sensor configured to measure an atmospheric condition. The unmanned aerial vehicle includes a rotor motor configured to drive rotation of a propeller of the unmanned aerial vehicle. The unmanned aerial vehicle includes a hybrid energy generation system including a rechargeable battery configured to provide electrical energy to the rotor motor; an engine configured to generate mechanical energy; and a generator coupled to the engine and configured to generate electrical energy from the mechanical energy generated by the engine, the electrical energy generated by the generator being provided to at least one of the rechargeable battery and the rotor motor.
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公开(公告)号：US10035596B2
公开(公告)日：2018-07-31
申请号：US15693789
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: B64C27/08 , B64C39/02 , B64C27/00 , B64D1/08 , B64D1/22 , B64D27/02 , B64D27/24 , B64D33/08 , B64F3/02 , G05D1/10
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.
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33.发明申请公开(公告)号：US20180118361A1
公开(公告)日：2018-05-03
申请号：US15542418
申请日：2016-01-11
Applicant: KOREAN AIR LINES CO., LTD.
Inventor： Seung Kie CHOI , Shin Je CHO , Sang Hun LEE
CPC classification number: B64D31/06 , B64C39/024 , B64C2201/044 , B64D33/08 , F02D9/02 , F02D41/0002 , F02D41/14 , F02D41/1401 , F02D41/26 , F02D2200/021 , F02D2400/06 , Y02T10/42
Abstract: The present invention relates to a system for maintaining a constant temperature of an engine in an unmanned aerial system with an autothrottle limiting device, the system comprising: an autopilot 100 for issuing a throttle command; an autothrottle limiting device 200 for automatically limiting an upper limit of the throttle command issued by the autopilot 100; and a rotary engine 300 for feeding an internal temperature of the engine of the autopilot 100 back to the autothrottle limiting device 200. Thus, the system is applicable to all the kinds of unmanned aerial systems employing an air-cooling rotary engine (i.e. reciprocating engine), uses the existing autopilot of the unmanned aerial system without modification, improves the reliability and life of the engine, and safely takes the aerial vehicle back without accidents in the engine even though communication with a terrestrial system is interrupted.
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公开(公告)号：US09957035B2
公开(公告)日：2018-05-01
申请号：US14172035
申请日：2014-02-04
Applicant: Texas A&M University System
Inventor： John Valasek , James Franklin May , Andrew Beckett , Cecil C. Rhodes, Jr.
CPC classification number: B64C1/26 , B64C1/22 , B64C39/024 , B64C39/04 , B64C2201/021 , B64C2201/044 , B64C2201/128 , B64C2211/00
Abstract: The present invention relates to an aircraft. The aircraft includes a fuselage module for receiving a payload. The fuselage module includes a plurality of internal connections. The aircraft includes a wing module adjustably coupled to the fuselage module and a tail module coupled to the wing module. The wing module may be adjusted relative to the fuselage module to adjust a location of an aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft. A main landing gear may be adjusted relative to the fuselage module to adjust the location of the aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.
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公开(公告)号：US09919797B2
公开(公告)日：2018-03-20
申请号：US14560765
申请日：2014-12-04
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.
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.
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Patent Agency Ranking
公开(公告)号：US20180030887A1
公开(公告)日：2018-02-01
申请号：US15661600
申请日：2017-07-27
Applicant: Ewatt Technology Co., Ltd.
Inventor： Guocheng ZHAO , Wei LUO , Pengcheng QI
IPC: F02B61/04 , B64C27/14 , F02B73/00 , F16H7/02 , F02B75/16 , F16H37/06 , F16H1/22 , B64C39/02 , F02B67/06
CPC classification number: F02B61/04 , B64C27/08 , B64C27/12 , B64C27/14 , B64C27/59 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64D35/04 , F02B67/06 , F02B73/00 , F02B75/16 , F16H1/222 , F16H7/02 , F16H37/065
Abstract: The present invention discloses a multi-shaft power source unmanned flight equipment, and belongs to the technical field of unmanned aerial vehicles. The multi-shaft power source unmanned flight equipment comprises a frame (1), a plurality of rotor sets (2) and a power device (3). The plurality of rotor sets (2) are rotatably fixed on the frame (1), and the power device (3) is correspondingly movably connected with each rotor set (2) respectively. Power is provided for flight of the unmanned flight equipment by the power device (3) with oil drive characteristics, mechanical kinetic energy is generated by burning a combustion material pre-injected in the power device (3), and rotors (21) in each rotor set (2) correspondingly connected with the power device are driven to rotate, thereby replacing the traditional electric multi-rotor unmanned aerial vehicle structure adopting electric modes such as batteries, electronic speed controllers and the like to supply power and provide power for the rotation of the rotors (21); and the unmanned flight equipment has the characteristics of long duration and strong loading capacity.
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公开(公告)号：US09771162B1
公开(公告)日：2017-09-26
申请号：US15163977
申请日：2016-05-25
Applicant: Amazon Technologies, Inc.
Inventor： Nicholas Kristofer Gentry
CPC classification number: B64D35/08 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/066 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/128 , B64C2201/145 , B64D27/24 , B64D2027/026 , G05D1/042 , G08G5/006 , Y10S903/93
Abstract: An unmanned aerial vehicle (“UAV”) is configured with a redundant power generation system on-board the UAV. A redundant power system on-board the UAV can selectively utilize an auxiliary power source during operation and/or flight of the UAV. The power system on-board the UAV may include a battery and at least one auxiliary power source comprising a combustion engine. The combustion engine on-board the UAV may be selectively operated to charge the battery when a charge level of the battery is below a full charge level, and/or to power one or more propeller motors of the UAV.
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公开(公告)号：US09637232B2
公开(公告)日：2017-05-02
申请号：US13169337
申请日：2011-06-27
Applicant: Mark D. Horn
Inventor： Mark D. Horn
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/044 , B64C2201/162 , B64D33/04 , F01D25/30 , Y10T137/85938
Abstract: An exhaust system includes a multiple of distribution risers which extend transverse to a plenum, each of the multiple of distribution risers includes at least one downstream directed aperture.
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公开(公告)号：US20170008627A1
公开(公告)日：2017-01-12
申请号：US15207436
申请日：2016-07-11
Applicant: Joaquin de Soto , Jorge F. Miranda
Inventor： Joaquin de Soto , Jorge F. Miranda
CPC classification number: B64C39/024 , B64C27/08 , B64C27/20 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/044 , B64C2201/108 , B64C2201/141 , B64C2201/146 , B64C2211/00 , B64D27/04 , B64D27/24 , B64D2027/026 , G07C5/008 , H02J7/1423 , H02K7/1815 , Y02T50/64
Abstract: Embodiments are directed towards hybrid power supply that provides electric power to a multirotor rotorcraft to extend range or flying time. In one embodiment, an internal combustion engine and fuel tank are provided that interoperate with a battery provided by a commercial multirotor rotorcraft to substantially extend flying time or flying distance.
Abstract translation: 实施例涉及向多转子旋翼飞机提供电力以延长范围或飞行时间的混合动力电源。 在一个实施例中，提供内燃机和燃料箱，其与由商用多转子旋翼飞机提供的电池相互作用以大大延长飞行时间或飞行距离。
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公开(公告)号：US09429076B2
公开(公告)日：2016-08-30
申请号：US13979120
申请日：2012-01-06
Applicant: Stephen John Richard Smith , Kieran James Watt , Andrew Charles White
Inventor： Stephen John Richard Smith , Kieran James Watt , Andrew Charles White
CPC classification number: F02C7/24 , B64C39/024 , B64C2201/044 , B64D13/08 , B64D15/02 , B64D15/04 , B64D27/10 , B64D33/08 , B64D2013/0607 , B64D2013/0614 , B64D2013/0648 , B64D2013/0674 , F28D2020/0013 , F28D2020/0017 , F28F13/003 , Y02T50/56
Abstract: A turboprop-powered medium altitude long endurance aircraft, having a gas turbine engine; a heat scavenging device to scavenge heat from the gas turbine engine; and a heating device to use the scavenged heat to provide heating to the aircraft. The heat scavenging device may be placed on an engine casing and/or on or in an engine exhaust duct. The heating device may include a circulation path routed directly to a location in the aircraft where heating is to be performed, for example a leading edge of an engine support pylon or a leading edge of an engine-carrying wing. The heating device can include a heat exchanger.
Abstract translation: 具有燃气涡轮发动机的涡轮螺旋桨发动机中型高空耐久型飞机; 用于清除来自燃气涡轮发动机的热的除热装置; 以及使用清扫热量来向飞机提供加热的加热装置。 除热装置可以放置在发动机壳体上和/或在发动机排气管道上或发动机排气管道中。 加热装置可以包括直接路由到飞行器中要进行加热的位置的循环路径，例如发动机支撑塔的前缘或发动机承载翼的前缘。 加热装置可以包括热交换器。
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