| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 一种无人空中加油装置及加油方法 | CN201710355372.X | 2017-05-19 | CN107140218A | 2017-09-08 | 江雄; 邱名; 郝颜; 陈逖; 蒋筑宇; 王子维 |
| 本发明涉及空中加油技术领域，公开了一种无人空中加油装置，包括副油箱和箭体，所述副油箱安装在箭体上，所述箭体包括前端两侧的翼面、后端的舵面以及发动机，所述副油箱上设置有加油连接装置；同时公开了一种利用上述加油装置进行的无人空中加油方法，将副油箱通过箭体发射到空中，控制中心同时获取飞机和加油装置的飞行参数，进而控制加油装置飞临飞机后，保持加油装置与飞机具备相同的飞行状态，再通过飞机上的加油机构与副油箱的连接装置安全对接，实现空中加油。本发明的加油装置可全天候发射，能适应复杂环境下的加油需求；无跑道需求，可在舰船和岛礁上发射；飞行时间短，加油响应速度快；无人驾驶，无安全担忧。 | ||||||
| 2 | 無人航空機を位置決定するためのシステムおよび方法 | JP2017052024 | 2017-03-17 | JP2017197172A | 2017-11-02 | マイケル・スティーブン・フェルドマン; マイケル・ジョセフ・デラーンノ; マウリシオ・カスティロ−エフェン; ジェームズ・ジェラルド・ロペス; フランク・サッジオ,サード; ウィリアム・ジェイ・ベレンゼン |
| 【課題】無人航空機を位置決定するためのシステムおよび方法を提供すること。 【解決手段】送信信号を変調して電磁放射送信機に対する座標系に関連付けられた場所情報を符号化するように構成された電磁放射送信機を備える位置基準システムを含む、無人航空機を位置決定するためのシステムを提供する。システムは、無人航空機の位置を制御するように構成された少なくとも1つの制御装置と、送信信号を受信するように構成された電磁放射受信機とを含む、無人航空機をさらに含む。無人航空機は、電磁放射受信機によって受信された場所情報に少なくとも部分的に基づいて少なくとも1つの制御装置を制御するように構成された、制御システムをさらに含む。 【選択図】図1 |
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| 3 | SYSTEMS AND METHODS FOR LONG ENDURANCE AIRSHIP OPERATIONS | EP12712014.5 | 2012-03-13 | EP2686238A1 | 2014-01-22 | Heppe, Stephen |
| In one example, a long endurance airship system includes a payload airship and a first logistics airship mechanically joined to the payload airship to form a first combined airship, the payload airship and the logistics airship having design capabilities differing by at least a factor of two with regard to at least one of: power generation capability, propulsion capability, endurance capability, and lift capability, in which the first combined airship is free flying, lighter-than-air, and configured to maintain stationkeeping for greater than 30 days. Illustrative methods for long endurance airship operations are also provided. | ||||||
| 4 | Tail sitter vehicle with aerial and ground refueling system | US15070599 | 2016-03-15 | US10106274B2 | 2018-10-23 | Mark R. Alber; Charles Gayagoy; Jeffrey Parkhurst; Glenn D. Tiongson |
| An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations. | ||||||
| 5 | Non-GPS Methods and Devices For Refueling Remotely Piloted Aircraft | US15912528 | 2018-03-05 | US20180251229A1 | 2018-09-06 | Jahangir S. Rastegar |
| A method for remotely guiding a refueling boom of a tanker to engage with a fueling receptacle of an aircraft while the tanker and the aircraft are in flight. The method comprising: transmitting a polarized RF scanning pattern from one of the refueling boom and refueling receptacle; detecting the polarized RF scanning pattern at one or more cavity sensors disposed on the other of the refueling boom and the refueling receptacle; and controlling a position of the refueling boom relative to a position of the refueling receptacle based on the detected polarized RF scanning pattern at the one or more cavity sensors. | ||||||
| 6 | System and method for positioning an unmanned aerial vehicle | US15087015 | 2016-03-31 | US10053218B2 | 2018-08-21 | Michael Steven Feldmann; Michael Joseph Dell'Anno; Mauricio Castillo-Effen; James Gerard Lopez; Frank Saggio, III; William J. Berendsen |
| A system for positioning an unmanned aerial vehicle is provided including a position reference system including an electromagnetic radiation transmitter configured to modulate a transmission signal to encode location information associated with a coordinate system relative to the electromagnetic radiation transmitter. The system further includes an unmanned aerial vehicle including at least one control device configured to control a position of the unmanned aerial vehicle and an electromagnetic radiation receiver configured to receive the transmission signal. The unmanned aerial vehicle further includes a control system configured to control the at least one control device based at least in part on the location information received by the electromagnetic radiation receiver. | ||||||
| 7 | Micro hybrid generator system drone | US15693789 | 2017-09-01 | US10035596B2 | 2018-07-31 | Long N. Phan; Sanjay Emani Sarma; Cody Miles Wojcik; Eli M. Davis; Benjamin Arthur Sena; Julian Lemus |
| 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. | ||||||
| 8 | Motor vehicle with captive aircraft | US14645194 | 2015-03-11 | US09969490B2 | 2018-05-15 | 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. |
| 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. | ||||||
| 9 | Hose for Conveying Fluid | US15278071 | 2016-09-28 | US20170241576A1 | 2017-08-24 | Timothy Denzil Pryce; Calvin Tan |
| 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. | ||||||
| 10 | MOTOR VEHICLE WITH CAPTIVE AIRCRAFT | US14645194 | 2015-03-11 | US20160176523A1 | 2016-06-23 | 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. |
| 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. | ||||||
| 11 | Systems and methods for wireless data transfer during in-flight refueling of an aircraft | US13908303 | 2013-06-03 | US09085370B2 | 2015-07-21 | James Gerard Lopez; Michael Joseph Dell'Anno |
| A refueling drogue assembly includes a drogue body coupled to a tanker aircraft, and at least one data transmission device coupled to the drogue body. The at least one data transmission device is configured to receive a transmission signal from a partner transmission device coupled to an airborne target aircraft. The transmission signal includes data to be stored. The drogue assembly further includes a data storage device coupled to the tanker aircraft. The data storage device is communicatively coupled to the at least one data transmission device. The data storage device is configured to receive the transmission signal and store the data. | ||||||
| 12 | MOTOR VEHICLE WITH CAPTIVE AIRCRAFT | US14054613 | 2013-10-15 | US20150102154A1 | 2015-04-16 | 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. |
| 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. | ||||||
| 13 | System and method of automatic piloting for in-flight refuelling of aircraft, and aircraft comprising said system | US12968692 | 2010-12-15 | US08712608B2 | 2014-04-29 | Geremia Pepicelli; Gaetano Portaro; Renzo Bava |
| An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information. | ||||||
| 14 | MICRO HYBRID GENERATOR SYSTEM DRONE | US16387057 | 2019-04-17 | US20190241264A1 | 2019-08-08 | Long N. Phan; Sanjay Emani Sarma; Cody Miles Wojcik; Eli M. Davis; Benjamin Arthur Sena; Julian Lemus |
| 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. | ||||||
| 15 | Motor vehicle with captive aircraft | US14054613 | 2013-10-15 | US10112710B2 | 2018-10-30 | 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. |
| 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. | ||||||
| 16 | Replaceable power modules on aerial vehicles | US15181254 | 2016-06-13 | US10017265B1 | 2018-07-10 | Glen C. Larsen |
| An aerial vehicle may receive electrical power from power modules that may be installed into or removed from the aerial vehicle during flight operations. Such power modules may be inserted into a chamber from below the aerial vehicle and may come into contact with one or more terminals or leads for powering propulsion motors or other electrical loads. Such power modules may also be removed from above the aerial vehicle, thereby uncoupling the power modules from the electrical loads. Power modules may be installed into or removed from a chamber using tension members that are guided into the chamber from lateral slots extending between a perimeter of the aerial vehicle and the chamber. The tension members may be used to not only engage and remove a power module within the chamber but also to install a power module into the chamber. | ||||||
| 17 | MICRO HYBRID GENERATOR SYSTEM DRONE | US15693859 | 2017-09-01 | US20180022452A1 | 2018-01-25 | Long N. Phan; Sanjay Emani Sarma; Cody Miles Wojcik; Eli M. Davis; Benjamin Arthur Sena; Julian Lemus |
| 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. | ||||||
| 18 | SYSTEM AND METHOD FOR POSITIONING AN UNMANNED AERIAL VEHICLE | US15087015 | 2016-03-31 | US20170285627A1 | 2017-10-05 | Michael Steven Feldmann; Michael Joseph Dell'Anno; Mauricio Castillo-Effen; James Gerard Lopez; Frank Saggio, III; William J. Berendsen |
| A system for positioning an unmanned aerial vehicle is provided including a position reference system including an electromagnetic radiation transmitter configured to modulate a transmission signal to encode location information associated with a coordinate system relative to the electromagnetic radiation transmitter. The system further includes an unmanned aerial vehicle including at least one control device configured to control a position of the unmanned aerial vehicle and an electromagnetic radiation receiver configured to receive the transmission signal. The unmanned aerial vehicle further includes a control system configured to control the at least one control device based at least in part on the location information received by the electromagnetic radiation receiver. | ||||||
| 19 | Micro hybrid generator system drone | US15262177 | 2016-09-12 | US09751626B2 | 2017-09-05 | Long N. Phan; Sanjay Emani Sarma; Cody Miles Wojcik; Eli M. Davis; Benjamin Arthur Sena; Julian Lemus |
| 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. | ||||||
| 20 | Modular aircraft system | US15096216 | 2016-04-11 | US09505484B1 | 2016-11-29 | Nasser M. Al-Sabah |
| 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. | ||||||
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