| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Fluid transfer device | JP2000588029 | 1999-11-29 | JP2002532343A | 2002-10-02 | カール チェウン テュン コン |
| (57)【要約】 特に、航空機燃料供給装置の燃料のような、揮発性流体又は有害流体を貯蔵又は移送するために、可変容積貯蔵タンク（１０）又はリザーバー及び関連流体（１２）移送装置を提供する。 各流体貯蔵タンク（１０）は、流体（１２）を受け入れて、貯蔵するための可変容積内部チャンバー（１４）を構成する、可動ベース壁（２２）と共同するタンク本体（１８）を有する。 | ||||||
| 22 | Auxiliary fuel transfer system for aircraft | JP4709590 | 1990-02-27 | JPH02267327A | 1990-11-01 | RORENSU ENU SECHIARORI; REIMONDO SHII KURESHISUKI JIYU; TOOMASU PII UIRUSON |
| PURPOSE: To accurately and easily perform detection of abnormalities by judging abnormal fuel transfer when pressure of transfer fuel does not reach the specified pressure within the specified time from the start of transfer when fuel is transferred from an auxiliary fuel tank to a main fuel tank. CONSTITUTION: Fuel in a main fuel tank 10 divided into two sections 12, 14 is supplied to engines 28, 30 through engine supply lines 36, 38 interposedly mounted with valves 32, 34. An inner main tank pipe 16 provided on the section 12 is connected to an auxiliary tank pipe 50 connected to a plurality of auxiliary tanks 52, 60 and 66 through a switch valve 48. In this case, pressure of a line 46 is detected by a pressure sensor 106 during fuel transfer from the auxiliary tank to the main fuel tank. If fuel pressure does not reach the specified pressure within the specified time from the start of transfer or if the fuel change rate of a main fuel tank level is less than a specified value, it is judged that fuel transfer is abnormal. COPYRIGHT: (C)1990,JPO | ||||||
| 23 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751133.1 | 2014-02-10 | EP2956356A1 | 2015-12-23 | FREUND, Donald |
| A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist. | ||||||
| 24 | Aircraft aerial refuelling system | EP12165221.8 | 2012-04-23 | EP2517957A3 | 2015-12-16 | Tichborne, Franklin; Lawson, Mark; Freeman, Hugh; Epifanie, Arnaud; Edwards, Adrian |
An aircraft aerial refuelling system including at least one pressure controlled fuel pump (20) having a control system (33) adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback (42). Also, methods of operating an aircraft aerial refuelling system.
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| 25 | AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS FOR INCREASING AN AIRCRAFT'S ON-BOARD FUEL CAPACITY | EP07845468.3 | 2007-12-12 | EP2114766B1 | 2015-10-07 | WEBER DE BRITO, Barbosa; HASMANN, Paulo Henrique; ASSAO, Regis |
| 26 | AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS FOR INCREASING AN AIRCRAFT'S ON-BOARD FUEL CAPACITY | EP07845468.3 | 2007-12-12 | EP2114766A2 | 2009-11-11 | WEBER DE BRITO BARBOSA; HASMANN, Paulo Henrique; ASSAO, Regis |
| Aircraft fuel tanks, systems and methods increase an aircraft's fuel capacity. The fuel tanks have a tank body defining an interior space for holding aircraft fuel, and a relief manifold assembly operatively associated to the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The relief manifold assembly preferably includes a buffer vessel defining a buffer chamber in fluid communication with the interior space defined by the fuel tank body. The buffer vessel may advantageously be fixed to the tank body within the interior space thereof. At least one of a fuel vent manifold assembly for venting the interior space of the fuel tank and a fuel refill/transfer manifold assembly for supplying fuel to and withdrawing fuel from the interior space of the fuel tank. | ||||||
| 27 | Improvements in and relating to aircraft wings and fuel tanks | EP06254424.2 | 2006-08-23 | EP1762487A2 | 2007-03-14 | Ward, Michael David |
On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of an aircraft. There exists a zone that is at risk of such damage. The layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with this invention includes port and starboard inner fuel tanks (11C, 21C) that are positioned adjacent to a central fuel tank (3) in the central wing section, but outside of the at-risk zone. Each of the port and starboard inner fuel tanks (11C, 21C) is defined in part by a respective inner boundary member (5RP, 5RS) that when viewed in plan extends, at least in part, in a direction at an angle of less than 20° to the adjacent vertical plane (A-A) defining the at-risk zone. Thus the amount of fuel stored in fuel tanks (11C, 21C) in the wing assembly that cover a region outside of the at-risk zone and that do not extend into the at-risk zone may be increased.
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| 28 | FLUID TRANSFER SYSTEM | EP99961848.1 | 1999-11-29 | EP1159192B1 | 2006-03-22 | Kong, Carl Cheung Tung |
| A variable volume storage tank (10) or reservoir and related fluid (12) transfer system are provided for storing and transferring volatile or hazardous fluid, particularly such as fuel in an aircraft fuel supply system. Each fluid storage tank (10) comprises a tank body (18) in combination with a movable base wall (22) defining a variable volume internal chamber (14) for receiving and storing fluid (12). | ||||||
| 29 | AIRCRAFT STRUCTURE FATIGUE ALLEVIATION | EP00931421.2 | 2000-05-25 | EP1183181B1 | 2004-11-17 | TIGHE, David John; WILLIAMS, Andrew David |
| A fuel transfer apparatus for an aircraft comprises: two or more fuel tanks (2, 3, 4, 5, 6) arranged in an inboard to outboard alignment, at least one being situated in the wing (1) of the aircraft, means for transferring fuel between the tanks (8, 9), and a fuel management system (10) for controlling and monitoring the transfer of fuel between tanks; the fuel management system comprises: means for receiving a first input signal that the aircraft has left the ground, means for receiving a second input signal that the aircraft is approaching its destination, means for initiating the transfer of the fuel from a relatively inboard tank location to a relatively outboard tank location in response to the first input signal, and means for initiating the transfer of the fuel from a relatively outboard tank location to a relatively inboard tank location in response to the second input signal. | ||||||
| 30 | Fuel intelligent crossfeed valve for detecting leakage in aircraft fuel tanks | US14531599 | 2014-11-03 | US09592905B2 | 2017-03-14 | Lubomir A. Ribarov; Leo J. Veilleux, Jr. |
| A fuel management system may include a first fuel tank and a second fuel tank. The fuel management system may also include an intelligent crossfeed valve positioned between the first fuel tank and the second fuel tank and configured to allow fuel to flow between the first fuel tank and the second fuel tank. The fuel management system may also include a sensor configured to detect an amount to which the intelligent crossfeed valve is open. The fuel management system may also include an engine controller connected to the sensor and configured to cause the intelligent crossfeed valve to close in response to the intelligent crossfeed valve being open a third predetermined amount. | ||||||
| 31 | AIRCRAFT AERIAL REFUELLING SYSTEM | US15176809 | 2016-06-08 | US20160355274A1 | 2016-12-08 | Franklin TICHBORNE; Mark LAWSON; Hugh FREEMAN; Arnaud EPIFANIE; Adrian EDWARDS |
| An aircraft aerial refuelling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refuelling system. | ||||||
| 32 | Aircraft aerial refuelling system | US13454157 | 2012-04-24 | US09409651B2 | 2016-08-09 | Franklin Tichborne; Mark Lawson; Hugh Freeman; Arnaud Epifanie; Adrian Edwards |
| An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system. | ||||||
| 33 | FUEL SUPPLY APPARATUS FOR AIRCRAFT ENGINE | US15050800 | 2016-02-23 | US20160169112A1 | 2016-06-16 | Noriko MORIOKA; Hitoshi OYORI |
| Two systems of a first pump unit and a third pump unit that supply fuel of a fuselage fuel tank, and a second pump unit and a fourth pump unit that supply fuel of fuel tanks in both right and left wings are provided corresponding to a left-wing engine and a right-wing engine, respectively. A supply source of the fuel to be supplied to the left-wing engine or the right-wing engine is switched by switching of the pump unit to be turned on. | ||||||
| 34 | FUEL INTELLIGENT CROSSFEED VALVE FOR DETECTING LEAKAGE IN AIRCRAFT FUEL TANKS | US14531599 | 2014-11-03 | US20160122004A1 | 2016-05-05 | Lubomir A. Ribarov; Leo J. Veilleux, JR. |
| A fuel management system may include a first fuel tank and a second fuel tank. The fuel management system may also include an intelligent crossfeed valve positioned between the first fuel tank and the second fuel tank and configured to allow fuel to flow between the first fuel tank and the second fuel tank. The fuel management system may also include a sensor configured to detect an amount to which the intelligent crossfeed valve is open. The fuel management system may also include an engine controller connected to the sensor and configured to cause the intelligent crossfeed valve to close in response to the intelligent crossfeed valve being open a third predetermined amount. | ||||||
| 35 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176843 | 2014-02-10 | US20140224925A1 | 2014-08-14 | Donald Freund |
| Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation. | ||||||
| 36 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176821 | 2014-02-10 | US20140224924A1 | 2014-08-14 | Donald Freund |
| A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist. | ||||||
| 37 | ROTORCRAFT, DYNAMIC, CG MANAGEMENT APPARATUS AND METHOD | US13623778 | 2012-09-20 | US20130037652A1 | 2013-02-14 | Jacob J. van der Westhuizen |
| An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearward from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. Systems and methods redistribute fuel among laterally, vertically, and longitudinally opposed fuel tanks to maintain a center of gravity in a dynamically stable position. | ||||||
| 38 | Method and device for correcting the lateral dissymmetry of an aircraft | US12431662 | 2009-04-28 | US08231082B2 | 2012-07-31 | Martin Delporte; Malika Essadouni |
| Disclosed is an aircraft that comprises a fuselage, a left wing and a right wing opposite one another with respect to said fuselage and each enclosing at least one fuel tank. The aircraft further includes a control device that controls transfer of fuel from a tank on one wing to a tank on another wing, and an automatic pilot that detects a roll-wise inclination of the aircraft as a result of lateral dissymmetry. The automatic pilot is linked to the control device such that the automatic pilot controls the control device to transfer the fuel only at a condition of rectilinear and uniform cruising flight of the aircraft. | ||||||
| 39 | Continuous fuel management system for automatic control of aircraft center of gravity | US12197737 | 2008-08-25 | US08226040B2 | 2012-07-24 | Rubens Domecildes Neto |
| Fuel transference between aircraft fuel tanks, disposed in different locations, is used to maintain the aircraft Center of Gravity close to the aft limit of the certified Center of Gravity versus weight envelope. Continuous fuel transfer decreases the control band thus enhancing aircraft performance. | ||||||
| 40 | METHOD OF OPERATING AN AIRCRAFT FUEL MANAGEMENT SYSTEM | US13130901 | 2008-11-25 | US20110231056A1 | 2011-09-22 | Petter Sjungargard; Ian Case; Antoine Burckhart; Michael Spottiswoode |
| A method of operating an aircraft fuel management system for an aircraft having at least one fuel tank, each fuel tank having an associated fuel quantity indicator arranged to provide an indication of the amount of fuel in the associated fuel tank, the method comprising calculating a value for the amount of fuel on board (FOB_FailedFQI) the aircraft to be utilised by the fuel management system in the event of a failure of at least one of the fuel quantity indicators, the amount of fuel on board being calculated as a value for the initial amount of fuel on board (FOBinit) minus the amount of fuel used. Additionally or alternatively a value for the gross weight centre of gravity of the aircraft is calculated using an assigned value of fuel for each of the fuel tanks having an associated failed fuel quantity indicator. | ||||||
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