| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | FLUID TRANSFER CHAMBER FOR AIRCRAFT FLUID TRANSMISSION LINES | US14267160 | 2014-05-01 | US20150314858A1 | 2015-11-05 | Joseph Leachman |
| One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft. | ||||||
| 62 | Method of controlling the centre of gravity of an aircraft | US13131209 | 2008-11-25 | US08814096B2 | 2014-08-26 | Michael Spottiswoode; Antoine Burckhart; Petter Sjungargard |
| A method of controlling the center of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft. | ||||||
| 63 | Method and system for maneuvering an aircraft by shifting its center of gravity | US12194088 | 2008-08-19 | US08548721B2 | 2013-10-01 | Pierre Paillard; David Larcher |
| A method to maneuver an aircraft in flight, in which the center of gravity of the aircraft is shifted by transferring fuel from at least one first fuel tank to at least one second fuel tank of the aircraft. A system implementing this method, the system including: at least one first fuel tank and at least one second fuel tank, a flight control unit capable of sending out a maneuver command upon being handled. A computer capable, as a function of this command, of determining a quantity of fuel to be transferred from the first tank to the second tank, at least one means of transfer connecting the first and second tanks and being controlled by the computer, to transfer the fuel from the first tank to the second tank. | ||||||
| 64 | AIRCRAFT AERIAL REFUELLING SYSTEM | US13454157 | 2012-04-24 | US20120273619A1 | 2012-11-01 | 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. | ||||||
| 65 | Aircraft wings and fuel tanks | US11469071 | 2006-08-31 | US07600717B2 | 2009-10-13 | Michael David Ward |
| On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of a conventional aircraft. There exists a zone that is at risk of such damage. Thus, the layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with embodiments 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. | ||||||
| 66 | Fuel balancing system | US11965792 | 2007-12-28 | US07591277B2 | 2009-09-22 | Richard A. Johnson; Michael J. Penty; Michael A. Striefel; 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. | ||||||
| 67 | AIRCRAFT WINGS AND FUEL TANKS | US11469071 | 2006-08-31 | US20090212162A1 | 2009-08-27 | Michael David Ward |
| On failure, a burst rotor of a wing-mounted engine (13, 23) can penetrate fuel tank walls in the wing of a conventional aircraft. There exists a zone that is at risk of such damage. Thus, the layout of fuel tanks (3, 11C, 21C) in the wing of an aircraft in accordance with embodiments 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. | ||||||
| 68 | METHOD AND SYSTEM FOR MANEUVERING AN AIRCRAFT BY SHIFTING ITS CENTER OF GRAVITY | US12194088 | 2008-08-19 | US20090088911A1 | 2009-04-02 | Pierre Paillard; David Larcher |
| A method to maneuver an aircraft in flight, in which the center of gravity of the aircraft is shifted by transferring fuel from at least one first fuel tank to at least one second fuel tank of the aircraft. A system implementing this method, the system including: at least one first fuel tank and at least one second fuel tank, a flight control unit capable of sending out a maneuver command upon being handled. A computer capable, as a function of this command, of determining a quantity of fuel to be transferred from the first tank to the second tank, at least one means of transfer connecting the first and second tanks and being controlled by the computer, to transfer the fuel from the first tank to the second tank | ||||||
| 69 | Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity | US11637922 | 2006-12-13 | US20090050743A1 | 2009-02-26 | Weber de Brito Barbosa; Paulo Henrique Hasmann; Regis Assao |
| 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. At least one control box (e.g., containing valves, pumps and/or sensors) external of the fuel tank may be provided so as to fluid-connect the at least one fluid manifold assembly to the main fuel system of the aircraft. A plurality of aircraft fuel tanks may therefore be positioned adjacent to one another, preferably within the fuselage (e.g., a cargo compartment) of the aircraft so as to be disposed generally along a longitudinal axis of the aircraft. | ||||||
| 70 | FUEL BALANCING SYSTEM | US11965792 | 2007-12-28 | US20080099079A1 | 2008-05-01 | 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. | ||||||
| 71 | Dynamic system for controlling mobile apparatuses | US10557097 | 2004-04-23 | US20070029445A1 | 2007-02-08 | Gabriel Avello |
| The invention relates to a dynamic system for controlling any type of mobile apparatus that is moving in any type of liquid or gas fluid or in space, whereby said mobile apparatus has an aerodynamic profile and can move in a stable manner. The control system has a built-in dynamic device with angular momentum along a main axis of the inertia ellipsoid thereof, which is used in the generation of a spatial variation in the angular momentum to modify and control the trajectory of the mobile apparatus as desired. | ||||||
| 72 | Method and arrangement for aircraft fuel dispersion | US10708818 | 2004-03-26 | US06997415B2 | 2006-02-14 | Gregg Wozniak; David Lamb; Dung Le |
| Method and arrangement for dispersing fuel 62 within a fuel containment system 60 of an aircraft 30 including utilizing a fuel containment system on an aircraft that is located at least partially within a wing 34 of the aircraft and defines a reservoir portion 42 and a remote portion 44. Fuel is pumped during at least aircraft flight operation from the reservoir portion to the remote portion at a pumped rate 80, while simultaneously fuel that is contained in the remote portion of the fuel containment system is permitted to drain to the reservoir portion at a drainage rate 82. The drainage rate is less than the pumped rate. A fuel mass 64 is accumulated in the remote portion of the fuel containment system because of a difference between the pumped rate and the drainage rate and as a result, a counteractive moment 49 is induced in the aircraft that is opposingly directed to a lift moment 46 caused by wing-lift 45 during aircraft flight. | ||||||
| 73 | METHOD AND ARRANGEMENT FOR AIRCRAFT FUEL DISPERSION | US10708818 | 2004-03-26 | US20050139727A1 | 2005-06-30 | Gregg Wozniak; David Lamb; Dung Le |
| Method and arrangement for dispersing fuel 62 within a fuel containment system 60 of an aircraft 30 including utilizing a fuel containment system on an aircraft that is located at least partially within a wing 34 of the aircraft and defines a reservoir portion 42 and a remote portion 44. Fuel is pumped during at least aircraft flight operation from the reservoir portion to the remote portion at a pumped rate 80, while simultaneously fuel that is contained in the remote portion of the fuel containment system is permitted to drain to the reservoir portion at a drainage rate 82. The drainage rate is less than the pumped rate. A fuel mass 64 is accumulated in the remote portion of the fuel containment system because of a difference between the pumped rate and the drainage rate and as a result, a counteractive moment 49 is induced in the aircraft that is opposingly directed to a lift moment 46 caused by wing-lift 45 during aircraft flight. | ||||||
| 74 | Fluid transfer system | US212767 | 1998-12-16 | US6125882A | 2000-10-03 | Carl Cheung Tung Kong |
| A variable volume fluid storage tank or reservoir and related fluid transfer system are provided for storing and transferring volatile or hazardous fluids, particularly such as fuel in an aircraft fuel supply system. Each fluid storage tank comprises a tank body in combination with a movable base wall defining a variable volume internal chamber for receiving and storing fluid. Each storage tank further includes a dispense port for dispensing the fluid, e.g., to a manifold or the like for supply to one or more aircraft engines, with the base wall moving relative to the tank body during fluid dispensing to substantially preclude any residual air or vapor space within the storage tank. A fluid level sensor unit mounted outside the tank chamber tracks displacement of the base wall to provide an indication of the fluid volume remaining within the storage tank. Multiple storage tanks may be ganged together and the fluid contained therein transferred quickly and safely between the tanks in a variety of fluid handling and fluid transfer applications. In one form, multiple storage tanks may be configured for nesting together in a progressively reduced profile as fluid is dispensed therefrom. | ||||||
| 75 | Apparatus for controlling fuel transfers in a distributed fuel tank system | US20023 | 1993-02-18 | US5321945A | 1994-06-21 | Douglas A. Bell |
| The present invention relates to a distributed fuel system, wherein a plurality of fuel tanks used for storing fuel are distributed in different locations.The fuel tanks are connected to each other via a manifold which permits fuel to flow therein. The distributed fuel system includes a plurality of control components interposed at predetermined points of the manifold to permit or restrict the flow of the fuel contained in the manifold in response to control signals. A method for distributing the fuel between the fuel tanks to achieve predetermined levels in each of the fuel tanks comprises the steps of determining the status and condition of the fuel system. The functions to be performed are then selected. Based on the system status and the functions to be performed, the configuration of the control elements is selected to perform the functions to be performed. The control signals are outputted to the control components to obtain the desired configuration of the control components for causing the fuel flow within the distributed fuel system to accomplish the desired functions, thereby yielding the desired fuel distribution. | ||||||
| 76 | Fuel transfer system for aircraft | US316264 | 1989-02-27 | US4932609A | 1990-06-12 | Lawrence N. Secchiaroli; Raymond C. Cresiski, Jr.; Thomas P. Wilson |
| Parallel transfer pumps (92, 94) operate to transfer fuel from auxiliary tanks (52, 60, 66) to the main tank (10). A pressure sensor (106) in the pump discharge line in combination with tank level rate mechanisms (86, 88, 90) sequences pumps (92, 92) and transfer valves (100, 102) if required, and confirms successful transfer or alarms when unsuccessful. | ||||||
| 77 | Liquid measuring and control system | US43996054 | 1954-06-29 | US2884948A | 1959-05-05 | WEISS LEO A |
| 78 | Fuel system head control unit | US56570056 | 1956-02-15 | US2860654A | 1958-11-18 | JOHN MORLEY; JOHN KARANIK; MOORE ALEXANDER P |
| 79 | Center of gravity responsive apparatus | US49873055 | 1955-04-01 | US2838928A | 1958-06-17 | BERGESON RAYMOND L |
| 80 | Aircraft fuel load equalizing system | US46466054 | 1954-10-25 | US2755046A | 1956-07-17 | UNDERWOOD JR JOHN L |
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