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公开(公告)号：US20180009529A1
公开(公告)日：2018-01-11
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: B64C39/02 , B64C27/08 , B64D1/08 , G05D1/10 , B64D27/02 , B64D27/24 , B64D33/08 , B64F3/02 , B64D1/22 , B64C27/00
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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公开(公告)号：US09815684B2
公开(公告)日：2017-11-14
申请号：US13998443
申请日：2013-11-01
Applicant: Brian Kamradt , Dart A. Fox
Inventor： Brian Kamradt , Dart A. Fox
CPC classification number: B67D7/845 , B64C39/024 , B64C2201/024 , B64C2201/063 , B64C2201/128 , B64C2201/141 , B64C2201/182 , B67D7/02 , B67D7/0401 , B67D7/78 , B67D2210/00089
Abstract: An unmanned self-sustained fuel dispensing station for fuels of all sorts (gasoline, pesticides, water, fertilizers etc.) a tank, docking, and coupling system for unmanned aerial vehicles (UAV) of the vertical takeoff types. The station can be independent of public power and communication utilities and can operate by remote control without an on-site attendant. The preferred system has a central command center with a control computer in communication with a station control computer located at one or more satellite stations through a communications link. The station control computer can be controlled remotely by the command center. The station control computer programming has control over the activities of the station through an electrical generation subsystem with a solar array, battery bank, battery charger and standby generator; a fuel dispensing subsystem; a security subsystem with video cameras; a communications link and a status sensor subsystem.
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公开(公告)号：US09751625B2
公开(公告)日：2017-09-05
申请号：US15202771
申请日：2016-07-06
Applicant: Top Flight Technologies, Inc.
Inventor： Long N. Phan , Sanjay Emani Sarma , Cody Miles Wojcik , Eli M. Davis , Benjamin Arthur Sena , Julian Lemus
IPC: B64D41/00 , B64C39/02 , B64D27/02 , B64C27/00 , B64C27/08 , B64D33/08 , B64D27/24 , B64D1/08 , B64D1/22 , 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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公开(公告)号：US09505484B1
公开(公告)日：2016-11-29
申请号：US15096216
申请日：2016-04-11
Applicant: Nasser M. Al-Sabah
Inventor： Nasser M. Al-Sabah
IPC: B64C3/38 , B64C13/00 , B64C9/00 , B64C13/20 , B64C9/32 , B64D27/02 , B64C3/34 , B64D47/08 , B64D15/00 , B64C39/02 , B64D37/00 , B64D27/14 , B64D27/20
CPC classification number: B64C3/38 , B64C1/26 , B64C3/34 , B64C5/06 , B64C9/00 , B64C9/326 , B64C13/00 , B64C13/20 , B64C39/024 , B64C2201/021 , B64C2201/048 , B64C2201/063 , B64C2201/104 , B64C2201/126 , B64C2201/141 , B64C2201/146 , B64C2201/16 , B64C2201/165 , B64C2211/00 , B64D15/00 , B64D27/02 , B64D27/14 , B64D27/20 , B64D37/00 , B64D39/00 , B64D47/08 , Y02T50/32
Abstract: The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.
Abstract translation: 模块化飞机系统包括具有永久安装的尾翼和多组翼模块和发动机模块的单个机身，每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身和每个模块配置为快速拆卸和安装模块，以最大限度地减少飞机的停机时间。 在具有较高耐久性和/或重量承载能力的情况下，为相对高速飞行提供具有相对较低纵横比的短翼。 为长距离和耐力航班提供高长宽比的长翼，速度并不是绝对重要的。 还提供了中跨翼模块。 提供涡轮螺旋桨发动机，单涡轮喷气发动机和双涡轮喷气发动机模块用于安装，具体取决于任何给定航班的任务要求。 该飞机主要适用于自主操作或远程操作的无人驾驶飞行器。
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公开(公告)号：US20160311544A1
公开(公告)日：2016-10-27
申请号：US15202771
申请日：2016-07-06
Applicant: Top Flight Technologies, Inc.
Inventor： Long N. Phan , Sanjay Emani Sarma , Cody Miles Wojcik , Eli M. Davis , Benjamin Arthur Sena , Julian Lemus
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.
Abstract translation: 一种包括至少一个转子电动机的无人驾驶飞行器。 转子电机由微型混合发电系统供电。 微型混合发电机系统包括被配置为向至少一个转子电动机提供电力的可再充电电池，被配置为产生机械功率的小型发动机，耦合到小型发动机的发电机电动机，并且被配置为使用由 小型发动机，桥式整流器，被配置为将由发电电动机产生的交流电力转换为直流电力，并将DC电力提供给可再充电电池和至少一个转子电动机中的一个或两者;以及电子控制单元， 所述小型发动机的节气门至少部分地基于至少一个负载的功率需求，所述至少一个负载包括所述至少一个转子电动机。
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Patent Agency Ranking
公开(公告)号：US20160176523A1
公开(公告)日：2016-06-23
申请号：US14645194
申请日：2015-03-11
Applicant: Elwha LLC
Inventor： William D. Duncan , Roderick A. Hyde , Jordin T. Kare , Stephen L. Malaska , Nathan P. Myhrvold , Robert C. Petroski , Thomas Allan Weaver , Lowell L. Wood, JR.
CPC classification number: B64C39/024 , B64C39/022 , B64C2201/021 , B64C2201/042 , B64C2201/046 , B64C2201/063 , B64C2201/066 , B64C2201/12 , B64C2201/127 , B64C2201/145 , B64C2201/146 , B64C2201/208 , B64F1/00 , G05D1/0094
Abstract: A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.
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公开(公告)号：US20190241264A1
公开(公告)日：2019-08-08
申请号：US16387057
申请日：2019-04-17
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 , B64D33/08 , B64D27/24 , B64D1/22 , B64D1/08 , B64F3/02 , G05D1/10 , B64D27/02 , B64C27/00 , B64C27/08
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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公开(公告)号：US20180281945A1
公开(公告)日：2018-10-04
申请号：US15476558
申请日：2017-03-31
Applicant: Intel Corporation
Inventor： Bradford H. Needham , Douglas Paul Bogia
CPC classification number: B64C39/024 , B64C2201/063 , B64C2201/066 , B64C2201/141 , B64C2201/145 , G06T7/70 , G06T2207/10048 , H01L35/28 , H02J7/025 , H02J7/32 , H02J50/10 , H02N2/186
Abstract: Various systems and methods for providing and deploying a power harvesting drone are described herein. A power harvesting drone includes a motor assembly; an energy replenishment coupler; a processor communicatively coupled to the energy replenishment coupler; and a memory storing instructions, which when executed by the processor cause the processor to: operate the power harvesting drone to navigate a predetermined path; determine that a power supply used to operate the power harvesting drone is below a threshold of remaining power; identify an opportunistic energy source; and deviate from the predetermined path to replenish at least a portion of the power supply from the opportunistic energy source using the energy replenishment coupler onboard the power harvesting drone.
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公开(公告)号：US20180162545A1
公开(公告)日：2018-06-14
申请号：US15681336
申请日：2017-08-18
Applicant: Marinus Ben Bosma
Inventor： Marinus Ben Bosma
CPC classification number: B64D39/06 , B64C39/024 , B64C2201/021 , B64C2201/063 , B64C2201/12 , B64D39/04
Abstract: An apparatus and method for refueling an aircraft comprising a hose guide. The hose guide includes a framework having wings and remotely-adjustable control surfaces interacting with air through which the hose guide moves. An attachment interface, attaching the hose guide to a fuel hose extended from a tanker aircraft, at a distal end away from the tanker aircraft, and a control system adjusting the adjustable control surfaces. Wherein the hose guide is towed as a glider by the tanker aircraft, and adjustment of the control surfaces adjusts three-dimensional position of the end of the fuel hose at the hose guide relative to position of the tanker aircraft.
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公开(公告)号：US20170241576A1
公开(公告)日：2017-08-24
申请号：US15278071
申请日：2016-09-28
Applicant: Icon Polymer Group Limited
Inventor： Timothy Denzil Pryce , Calvin Tan
CPC classification number: F16L11/22 , B60L3/0046 , B60L3/0069 , B60L3/04 , B60L11/1818 , B60L2200/10 , B60L2230/12 , B60L2240/36 , B60L2240/662 , B64C39/024 , B64C2201/063 , B64C2201/066 , B64D39/00 , B64D39/06 , F16L11/127 , H01R12/77 , H01R13/005 , H01R13/6683 , H01R2201/26 , Y02T10/7005 , Y02T10/7088 , Y02T10/7291 , Y02T90/121 , Y02T90/14 , Y02T90/16
Abstract: A hose is disclosed for conveying fluids. The hose has a wall defining a fluid carrying tube and a power and/or data transmission cable is integrated into said wall. Also disclosed is a user definable module that is removably attachable to the distal end of a fluid conveying hose. The hose being releasably connectable to a fluid receiving entity to provide fluid to said entity. The fluid conveying hose has a wall defining a fluid carrying tube and a power and/or data transmission cable integrated into that wall. The user definable module is connectable to the cable and has components to measure at least one measurable parameter at the end of the hose and/or provide electrical connection between the cable and said fluid receiving entity for the transmission of data and/or power along the hose via said user definable interface. Also disclosed is a method of configuring a hose for fluid transfer. The method includes the step of selecting a user definable module and attaching the selected module to a distal end of the hose prior to connecting said hose to a fluid receiving entity.
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