| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Fuel balancing system | US11251659 | 2005-10-17 | US07337795B2 | 2008-03-04 | Thomas R. Duranti |
| A fuel system for a mobile platform is provided. The system includes a crossfeed fuel transmission assembly having a single crossfeed valve that controls fuel consumption from a first fuel tank and a second fuel tank. The system additionally includes a balancing fuel transfer assembly fluidly connected to the crossfeed fuel transmission assembly. The balancing fuel transfer assembly includes a plurality of fuel balancing valves for controlling a transfer of fuel to the first and second fuel tanks. The fuel system further includes a fuel balancing controller for automatically controlling the fuel balancing valves to automatically control the transfer of fuel to the first and second fuel tanks. | ||||||
| 102 | Fuel balancing system | US11251659 | 2005-10-17 | US20070084511A1 | 2007-04-19 | Richard Johnson; Michael Penty; Michael Striefel; Thomas Duranti; Diane Duranti |
| A fuel system for a mobile platform is provided. The system includes a crossfeed fuel transmission assembly having a single crossfeed valve that controls fuel consumption from a first fuel tank and a second fuel tank. The system additionally includes a balancing fuel transfer assembly fluidly connected to the crossfeed fuel transmission assembly. The balancing fuel transfer assembly includes a plurality of fuel balancing valves for controlling a transfer of fuel to the first and second fuel tanks. The fuel system further includes a fuel balancing controller for automatically controlling the fuel balancing valves to automatically control the transfer of fuel to the first and second fuel tanks. | ||||||
| 103 | Fluid transfer system | US09779310 | 2001-02-08 | US06527007B2 | 2003-03-04 | Carl Cheung Tung Kong; John Kong |
| A closed fluid transfer system is provided including a fluid source in fluid communication with an inlet of a hollow body. The hollow body includes a flexible and expandable wall, typically composed of elastomeric material, at one end thereof. An outlet is formed distal from the flexible and expandable wall. Fluid is transported from the fluid source to the hollow body through a tube by a pump or the like. The hollow body may constitute a fluid conditioning chamber. Alternatively, the hollow body serves as a fluid source for an energy production device. The hollow body may also be fluidly connected to a vehicle for use as a fuel tank. | ||||||
| 104 | Fuel tank | US48539865 | 1965-09-07 | US3295799A | 1967-01-03 | STOPPE WILLY G |
| 105 | Capacitive | US2899151D | US2899151A | 1959-08-11 | ||
| 106 | Liquid proportionating system | US34673653 | 1953-04-03 | US2879782A | 1959-03-31 | LEVINE ROBERT J |
| 107 | Control apparatus | US61463756 | 1956-10-08 | US2873757A | 1959-02-17 | LINDEMANN ARTHUR W |
| 108 | Aircraft fuel load equalizing system | US57457256 | 1956-03-28 | US2853259A | 1958-09-23 | UNDERWOOD JR JOHN L |
| 109 | Control apparatus | US56649656 | 1956-02-20 | US2841163A | 1958-07-01 | WILLIAMSON REGINALD M |
| 110 | FLUID TRANSFER SYSTEM | PCT/US0151645 | 2001-12-13 | WO02103203A3 | 2003-04-17 | KONG CARL CHEUNG TUNG; KONG JOHN |
| A closed fluid transfer system is provided including a fluid source (12) in fluid communication with an inlet of hollow body.(14) The hollow body includes a flexible and expandable wall (26), typically composed of elastomeric material, at one end thereof. An outlet (32) is formed distal from the flexible and expandable wall. Fluid is transported from the fluid source to the hollow body through a tube by a pump or the like. | ||||||
| 111 | AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS FOR INCREASING AN AIRCRAFT'S ON-BOARD FUEL CAPACITY | PCT/BR2007000342 | 2007-12-12 | WO2008070946A3 | 2009-04-02 | 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. | ||||||
| 112 | Aircraft aerial refuelling system | EP12165221.8 | 2012-04-23 | EP2517957B1 | 2018-06-20 | 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. | ||||||
| 113 | CONTINUOUS FUEL TANK LEVEL CONTROL | EP16176290.1 | 2016-06-24 | EP3109165B1 | 2018-02-28 | RIBAROV, LubomirA.; CARPENTER, Richard J.; ROURKE, Russell P.; RUSSO, Charles J; LUKER, WILLIAM |
| A method of aircraft fuel distribution includes selecting a longitudinal center of gravity and predicting a rate of change of the center of gravity during flight. Fuel is located in a tail fm tank of a vertical tail fin of the aircraft, and is transferred from the tail fin tank forward at a predetermined transfer rate to counteract the predicted rate of change thereby maintaining the selected center of gravity. An aircraft fuel distribution system includes a center main fuel tank, a tail fin tank and a tail fin fuel pump to pump fuel between the tail fin tank and the center main fuel tank. An electronic controller operates the tail fin fuel pump such that fuel is flowed between the tail fin tank and the center main fuel tank at a predetermined transfer rate to maintain automatically an optimal position of a longitudinal center of gravity of the aircraft. | ||||||
| 114 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751133 | 2014-02-10 | EP2956356A4 | 2016-11-30 | 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. | ||||||
| 115 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751877 | 2014-02-10 | EP2956355A4 | 2016-11-02 | FREUND DONALD |
| A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 116 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751884.9 | 2014-02-10 | EP2956358A1 | 2015-12-23 | FREUND, Donald |
| A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 117 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | EP14751160.4 | 2014-02-10 | EP2956357A1 | 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. | ||||||
| 118 | AN AEROSPACE PLANE SYSTEM | EP13883346.2 | 2013-04-04 | EP2834152A1 | 2015-02-11 | ALEXANDER, Nic |
| An aerospace plane (1) having an elongate body (2) supports a pair of wings (3). The wings are adapted to extend away from said body in opposing directions. A landing gear assembly is operatively associated with said body to be moveable from a retracted position where said assembly is substantially locatable within said body and an extended position were said assembly extends at least partially away from said body. At least one engine (10) is adapted to generate thrust. At least one stabilizer is adapted to assist with movement of said aerospace plane. The at least one engine is locatable at least partially within an intake housing (14) to direct air into said at least one engine. The intake housing having at least one door portion to open or close the intake housing to moderate the amount of air flowing into said intake housing and thereby said engine. | ||||||
| 119 | AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS FOR INCREASING AN AIRCRAFT'S ON-BOARD FUEL CAPACITY | EP07845468 | 2007-12-12 | EP2114766A4 | 2014-04-02 | WEBER DE BRITO BARBOSA; HASMANN PAULO HENRIQUE; ASSAO REGIS |
| 120 | FUEL TRANSFER MONITORING SYSTEM AND METHOD | EP08875683.8 | 2008-11-19 | EP2356023A1 | 2011-08-17 | SJUNGARGÅRD, Petter |
| A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks (2, 4, 6, 10, 12), the fuel monitoring system comprises a fuel quantity sensor (14) arranged to measure the quantity of fuel in a first fuel tank (10) and a data processor (16) arranged to receive a fuel quantity measurement from the sensor, wherein in response to receiving a command to transfer fuel from the first fuel tank to one or more further fuel tanks (12) the data processor is arranged to determine the rate of change of fuel quantity in the first tank from the received fuel quantity measurement and if the rate of change of fuel quantity is less than a threshold value and the received fuel quantity measurement is greater than an expected value then the data processor is further arranged to provide an output indicating that the commanded fuel transfer has failed. | ||||||
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