| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | CONTINUAL TRANSFERENCE OF FUEL BETWEEN FUEL TANKS AT A RATE COMMENSURATE WITH FUEL BURN DURING CRUISE FLIGHT OPERATION TO MAINTAIN THE AIRCRAFT CENTER OF GRAVITY WITHIN A PRE-SELECTED AFT CENTER OF GRAVITY ENVELOPE | US12197737 | 2008-08-25 | US20100044515A1 | 2010-02-25 | 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. | ||||||
| 42 | METHOD AND DEVICE FOR CORRECTING THE LATERAL DISSYMMETRY OF AN AIRCRAFT | US12431662 | 2009-04-28 | US20090272851A1 | 2009-11-05 | Martin DELPORTE; Malika Essadouni |
| Method and device for correcting the lateral dissymmetry of an aircraft.According to the invention, when the aircraft is in rectilnear and uniform cruising flight, fuel is transferred from one of the wings (3G, 3D) to the other under the control of the automatic pilot. | ||||||
| 43 | Aircraft structure fatigue alleviation | US09582760 | 2000-05-25 | US07073751B1 | 2006-07-11 | David J Tighe; Andrew D Williams |
| 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. | ||||||
| 44 | Fluid transfer system | US09779310 | 2001-02-08 | US20010023710A1 | 2001-09-27 | 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. | ||||||
| 45 | Fluid transfer system | US09611919 | 2000-07-07 | US06231009B1 | 2001-05-15 | 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. | ||||||
| 46 | Emergency flight control system using one engine and fuel transfer | US112067 | 1998-07-08 | US6126111A | 2000-10-03 | Frank W. Burcham, Jr.; John J. Burken; Jeanette Le |
| A system for emergency aircraft control uses at least one engine and lateral fuel transfer that allows a pilot to regain control over an aircraft under emergency conditions. Where aircraft propulsion is available only through engines on one side of the aircraft, lateral fuel transfer provides means by which the center of gravity of the aircraft can be moved over to the wing associated with the operating engine, thus inducing a moment that balances the moment from the remaining engine, allowing the pilot to regain control over the aircraft. By implementing the present invention in flight control programming associated with a flight control computer (FCC), control of the aircraft under emergency conditions can be linked to the yoke or autopilot knob of the aircraft. Additionally, the center of gravity of the aircraft can be shifted in order to effect maneuvers and turns by spacing such center of gravity either closer to or farther away from the propelling engine or engines. In an alternative embodiment, aircraft having a third engine associated with the tail section or otherwise are accommodated and implemented by the present invention by appropriately shifting the center of gravity of the aircraft. Alternatively, where a four-engine aircraft has suffered loss of engine control on one side of the plane, the lateral fuel transfer may deliver the center of gravity closer to the two remaining engines. Differential thrust between the two can then control the pitch and roll of the aircraft in conjunction with lateral fuel transfer. | ||||||
| 47 | Multiplexed junction probe for fuel gaging system and system containing same | US685396 | 1984-12-20 | US4918619A | 1990-04-17 | Eugene F. Orloff; Martin Horowitz; Charles H. Ritter |
| A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location. | ||||||
| 48 | Multiplexed junction probe for fuel gaging system and system containing same | US184271 | 1988-04-21 | US4872120A | 1989-10-03 | Eugene F. Orloff; Martin Horowitz; Charles H. Rittner |
| A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location. | ||||||
| 49 | Automatic/manual fuel tank supply balance system | US662337 | 1984-10-18 | US4591115A | 1986-05-27 | Joseph D. DeCarlo |
| A multi-engine helicopter fuel supply balance system effects automatic trfer of fuel from a larger tank to a smaller tank in response to low fuel level in the smaller tank when in automatic mode, and effects a transfer of a predetermined quantity of fuel between selected tanks by timed operation of a constant delivery pump when in manual mode. | ||||||
| 50 | Center of gravity control apparatus | US60940156 | 1956-09-12 | US3042060A | 1962-07-03 | LINDEMANN ARTHUR W |
| 51 | Center of gravity controller | US62001056 | 1956-11-02 | US3017141A | 1962-01-16 | MORRIS OLLODORT |
| 52 | Control apparatus | US47231454 | 1954-12-01 | US2960294A | 1960-11-15 | JOHNSTON DONALD C; WILSON WILLIAM R |
| 53 | Control apparatus | US56656356 | 1956-02-20 | US2841164A | 1958-07-01 | WILLIAMSON REGINALD M |
| 54 | Aircraft fuel load center of gravity control means | US49342655 | 1955-03-10 | US2823880A | 1958-02-18 | BERGESON RAYMOND L |
| 55 | Fuel distribution control for aircraft | US17110150 | 1950-06-29 | US2684217A | 1954-07-20 | EDWARDS LAWRENCE K |
| 56 | AUTOMATIC ADJUSTMENT OF CENTER OF MASS OF A VEHICLE | US15616762 | 2017-06-07 | US20180354610A1 | 2018-12-13 | Nils KNEUPER; Ralf Rene Shu-Zhong CABOS |
| A method, vehicle, and system for calculating the location of a center of mass of the vehicle and transferring fuel to move the location of the center of mass are provided. The location of the center of mass of the vehicle is determined by measuring or calculating forces acting on the vehicle that counteract the gravitational forces on the vehicle. The location of the center of mass is calculated by determining on a moment arm of the gravitational force that counteracts the moment arms of the other forces acting on the vehicle. Fuel can be transferred among differently-located fuel tanks in the vehicle to move the location of the center of mass to a position in which at least some of the other forces acting on the vehicle are reduced, which may increase the speed and/or efficiency of the vehicle. | ||||||
| 57 | Systems and methods for controlling a magnitude of a sonic boom | US14176821 | 2014-02-10 | US10093410B2 | 2018-10-09 | 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. | ||||||
| 58 | System and method for controlling and monitoring aircraft equipment | US15385966 | 2016-12-21 | US20170183085A1 | 2017-06-29 | Arnaud BRANTHOMME; Guy SCHALLER; Lorianne BOUTZEN |
| A system for controlling and monitoring pieces of equipment of an aircraft, each piece of equipment being able to be switched between two logic activation state values, comprising a man-machine interface, a module for configuration of a functional activation state of a function able to be performed on at least pieces of equipment of a system of the aircraft, the functional activation state being configurable between an active state and an inactive state, the configuration module being adapted for detecting an action of selection of a functional activation state of the function by an operator, and a control and monitoring module configured for determining a logic activation state of each of the pieces of equipment of the system, so that, when each of the pieces of equipment is in the determined logic activation state, the function is in the selected functional activation state. | ||||||
| 59 | CONTINUOUS FUEL TANK LEVEL CONTROL | US15184201 | 2016-06-16 | US20160375985A1 | 2016-12-29 | Lubomir A. Ribarov; Richard J. Carpenter; Russell P. Rourke, JR.; Charles J. Russo; William Luker |
| 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 fin 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. | ||||||
| 60 | Fluid transfer chamber for aircraft fluid transmission lines | US14267160 | 2014-05-01 | US09340279B2 | 2016-05-17 | 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. | ||||||
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