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1.发明申请公开(公告)号：US20190168887A1
公开(公告)日：2019-06-06
申请号：US16135998
申请日：2018-09-19
CPC分类号： B64D39/00 , B64D5/00 , B64D27/023 , B64G1/005 , B64G1/14
摘要： A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.
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公开(公告)号：US20180251229A1
公开(公告)日：2018-09-06
申请号：US15912528
申请日：2018-03-05
申请人： Jahangir S. Rastegar
发明人： Jahangir S. Rastegar
CPC分类号： B64D39/00 , B64C39/024 , B64C2201/063 , B64C2201/14
摘要： 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.
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公开(公告)号：US10035606B2
公开(公告)日：2018-07-31
申请号：US14712031
申请日：2015-05-14
申请人： The Boeing Company
CPC分类号： B64D39/06 , B64D39/00 , B67D7/04 , B67D7/14 , B67D7/3245
摘要： A system for effecting automatic identifying of a receiving aircraft receiving fuel from a fuel delivery apparatus in a delivering aircraft during an airborne fueling operation includes: (a) a first unit coupled with the receiving aircraft; (b) a second unit coupled with the delivering aircraft; and (c) a processing unit coupled with at least one of the first unit and the second unit. The first and second units cooperate to effect communicative coupling for conveying identifying information between the receiving aircraft and the delivering aircraft. The processing unit cooperates with at least one of the first unit and the second unit for employing the identifying information to effect the identifying.
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公开(公告)号：US20180044033A1
公开(公告)日：2018-02-15
申请号：US15723571
申请日：2017-10-03
摘要： The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.
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公开(公告)号：US20170283047A1
公开(公告)日：2017-10-05
申请号：US15508346
申请日：2015-09-29
发明人： Steven D. Weiner , William J. Eadie
CPC分类号： F16F15/02 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C27/82 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe. A flight control computer is configured to control a main rotor rotational speed of the upper and the lower rotor assemblies of the main rotor assembly as a function of airspeed of the aircraft. A method of operating an aircraft includes retrieving a threshold main rotor rotational speed of the dual coaxial main rotor assembly and calculating an actual main rotor rotational speed according to an environment of the aircraft. The actual main rotor rotational speed is maintained to remain at or below the threshold main rotor speed according to an airspeed of the aircraft.
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公开(公告)号：US09663219B2
公开(公告)日：2017-05-30
申请号：US14807014
申请日：2015-07-23
发明人： Mathieu Carton , Pierre Debusschere , David Chabe
CPC分类号： B64C13/00 , B64D39/00 , G05D1/0607 , G05D1/0808
摘要： The system comprises at least one lift generator element that is able to modify directly the lift of the aircraft and means for defining a deflection instruction upon actuation by a pilot of the aircraft of a control column of the aircraft generating a vertical load factor control value and applying it to an elevator and simultaneously defining a command instruction and applying it to the lift generator element to generate a direct lift.
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公开(公告)号：US20170136903A1
公开(公告)日：2017-05-18
申请号：US15010701
申请日：2016-01-29
申请人： NextEv USA, Inc.
发明人： Christopher P. Ricci
IPC分类号： B60L11/18
CPC分类号： B60L11/1827 , B60L11/1816 , B60L11/182 , B60L11/1838 , B60L11/1844 , B60L11/1861 , B60L2230/10 , B64C39/024 , B64C2201/12 , B64D39/00 , Y02E60/721 , Y02T10/7005 , Y02T10/7044 , Y02T10/705 , Y02T10/7088 , Y02T90/121 , Y02T90/122 , Y02T90/125 , Y02T90/128 , Y02T90/14 , Y02T90/16 , Y02T90/163 , Y04S10/126
摘要： Techniques for electric vehicle systems, and in particular to an electric vehicle emergency charging system and method of use. In one embodiment, a system for charging a moving electric vehicle is disclosed, the system comprising: an electrical storage unit disposed on the electric vehicle; a charging panel in electrical communication with the electrical storage unit; a vehicle controller that determines if the electrical storage unit requires charging and configured to determine if an emergency external power source is available to charge the electrical storage unit; wherein the charging panel receives the charge from the emergency external power source and charges the electrical storage unit.
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公开(公告)号：US20160258750A1
公开(公告)日：2016-09-08
申请号：US14640878
申请日：2015-03-06
申请人： THE BOEING COMPANY
发明人： RICHARD GOLOB , JUSTIN CLEVE HATCHER , JUNG SOON JANG , KIMBERLY ANN HINSON , JEFFREY L. MUSGRAVE
CPC分类号： G01C9/005 , B64D39/00 , G01C9/02 , G01C25/005
摘要： An aerial refueling boom elevation estimation (“ARBEE”) system for estimating an elevation angle of an aerial refueling boom on an aerial refueling aircraft is described. The ARBEE system may include a data collector, storage unit, optimizer, and comparator.
摘要翻译： 描述了用于估计空中加油飞机上的空中加油站的仰角的空中加油站高程估计（“ARBEE”）系统。 ARBEE系统可以包括数据收集器，存储单元，优化器和比较器。
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公开(公告)号：US09334062B2
公开(公告)日：2016-05-10
申请号：US12792440
申请日：2010-06-02
摘要： An assisted in-flight refueling system having a tanker aircraft equipped with a drogue; a fuel take-on aircraft equipped with a probe; and a drogue-probe coupling assist system designed to determine a first distance between the drogue and the take-on aircraft/probe, a second distance between the tanker aircraft and the drogue, and a third distance between the tanker aircraft and the take-on aircraft. The drogue-probe coupling assist system is also designed to determine information relative to the necessary movement of the drogue and/or the necessary movement of the take-on aircraft to couple the drogue to the probe, as a function of the first, second, and third distance.
摘要翻译： 一个辅助的机上加油系统，具有配备有冷水的油轮飞机; 装有探头的燃油喷射飞机; 以及锥形探针联接辅助系统，其被设计用于确定锥套和接管飞行器/探针之间的第一距离，油罐飞机与锥套之间的第二距离，以及油轮飞机与接收器之间的第三距离 飞机。 锥形探针耦合辅助系统还被设计成根据第一，第二，第二，第二，第二，第二，第二，第二，第二和第二， 和第三距离。
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公开(公告)号：US20160023749A1
公开(公告)日：2016-01-28
申请号：US14807014
申请日：2015-07-23
发明人： Mathieu CARTON , Pierre DEBUSSCHERE , David CHABE
CPC分类号： B64C13/00 , B64D39/00 , G05D1/0607 , G05D1/0808
摘要： The system comprises at least one lift generator element that is able to modify directly the lift of the aircraft and means for defining a deflection instruction upon actuation by a pilot of the aircraft of a control column of the aircraft generating a vertical load factor control value and applying it to an elevator and simultaneously defining a command instruction and applying it to the lift generator element to generate a direct lift.
摘要翻译： 该系统包括至少一个提升发电机元件，该升降机发电机元件能够直接修改飞行器的升降机，以及用于在飞行器的飞行员致动之后定义偏转指令的装置，该飞行器的飞行器产生垂直载荷系数控制值， 将其施加到电梯并同时定义命令指令并将其施加到电梯发电机元件以产生直接电梯。
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