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公开(公告)号：US20240253781A1
公开(公告)日：2024-08-01
申请号：US18101836
申请日：2023-01-26
申请人： JETZERO, INC.
发明人： Blaine Rawdon
CPC分类号： B64C39/10 , B64D39/00 , B64C2039/105
摘要： Aspects relate to blended wing body aircraft having a passenger compartment. Blended wing body aircraft may include a freighter aircraft, a tanker aircraft, a passenger aircraft, or the like. Blended wing body aircraft may include an upper seating area, such as a passenger compartment, configured to accommodate passengers or personnel of aircraft without sacrificing space of a main region of a fuselage of the aircraft.
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公开(公告)号：US11834192B2
公开(公告)日：2023-12-05
申请号：US17497514
申请日：2021-10-08
发明人： Ohad Rix , Joshua Gur , Michael Litvak , Elie Koskas
摘要： A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.
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公开(公告)号：US20230257134A1
公开(公告)日：2023-08-17
申请号：US17672829
申请日：2022-02-16
CPC分类号： B64D37/30 , B64D39/00 , B64D37/06 , B64D27/24 , B64C2039/105
摘要： Aspects relate to blended wing body tankers and methods of use. An exemplary blended wing body tanker includes a blended wing body, a first fuel store located within the blended wing body and configured to store a first fuel, a fuel offloading system operatively connected to the first fuel store and configured to offload the first fuel to another aircraft in flight, a second fuel store located within the blended wing body and configured to store a second fuel different from the first fuel, and a propulsion system powered by the second fuel and configured to propel the blended wing body.
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公开(公告)号：US11718412B2
公开(公告)日：2023-08-08
申请号：US17279467
申请日：2019-09-26
申请人： Brulic Ltd.
发明人： James Pitman
CPC分类号： B64D39/02 , B64D39/00 , B64D39/06 , H02J7/00032 , H02J7/0045 , H02J50/10
摘要： A propellant-handling module for installation in a host aircraft comprises: a motorised drum unit comprising a line and drogue for engagement with a propellant supply line of a propellant supply aircraft and for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft; a propellant inlet configured for connection with the propellant supply line; a propellant outlet in communication with the propellant inlet and configured for connection with a propellant system of the host aircraft; an electrical power unit for powering the propellant-handling module; and a communication and control system for receiving a deploy command signal and a return command signal from the supply aircraft and configured to: receive said deploy command signal and in response control the motorised drum unit to deploy the line and drogue for said engagement with the propellant supply line; and receive said return command signal and in response control the motorised drum unit to return the line and drogue to the host aircraft in said engagement with the propellant supply line for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft.
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5.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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