| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Device for changing the loading of aircraft wings | US75842047 | 1947-07-01 | US2585480A | 1952-02-12 | JEAN MAKHONINE |
| 82 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US15921826 | 2018-03-15 | US20180201363A1 | 2018-07-19 | 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. | ||||||
| 83 | ACTUATOR WITH BRUSHLESS DC MOTOR | US15801721 | 2017-11-02 | US20180135772A1 | 2018-05-17 | Till GUNDLACH; Kayvon BARAD; Osama AL-TAYAWE; Geoff WARD; Andrew STEWART; Christopher LEWIS |
| An actuator includes a brushless DC motor, an output device, a reduction system coupled between the brushless DC motor and the output device, and a contactless position sensor configured to sense a position of the output device. | ||||||
| 84 | Aircraft aerial refuelling system | US15176809 | 2016-06-08 | US09845160B2 | 2017-12-19 | 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. | ||||||
| 85 | Systems and methods for controlling a magnitude of a sonic boom | US14176879 | 2014-02-10 | US09580169B2 | 2017-02-28 | Donald Freund |
| 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. | ||||||
| 86 | Systems and methods for controlling a magnitude of a sonic boom | US14176865 | 2014-02-10 | US09561847B2 | 2017-02-07 | Donald Freund |
| A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 87 | Method of operating an aircraft fuel management system | US13130901 | 2008-11-25 | US09517836B2 | 2016-12-13 | 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 utilized 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 center 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. | ||||||
| 88 | Systems and methods for controlling a magnitude of a sonic boom | US14176843 | 2014-02-10 | US09446839B2 | 2016-09-20 | 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. | ||||||
| 89 | Rotorcraft, dynamic, CG management apparatus and method | US13623778 | 2012-09-20 | US09205913B2 | 2015-12-08 | 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. | ||||||
| 90 | AEROSPACE PLANE SYSTEM | US14390470 | 2013-04-04 | US20150232204A1 | 2015-08-20 | Nick Alexander |
| 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. | ||||||
| 91 | Fluid-based orientation control system | US14058486 | 2013-10-21 | US08965674B1 | 2015-02-24 | Stephen D. Russell |
| A system includes a fluid reservoir containing a first fluid, a pair of fluidic channels in fluidic connection with the fluid reservoir, a counter-fluid reservoir having a second fluid that is non-miscible with the first fluid, and a pump connected to the fluid reservoir. The pump is configured to pump the first fluid from the fluid reservoir into the pair of fluidic channels. When contained in a vehicle, the system allows for control of the vehicle's orientation. The system may use sensor input to determine when to actuate the pump. Each fluidic channel may have a cross-section that varies along its length. The fluidic channels may be geometrically symmetric about the fluid reservoir. The system may be incorporated into a vehicle to control the vehicle's orientation. | ||||||
| 92 | Systems and methods to provide compliance with structural load requirements for aircraft with additional fuel tankage | US13095615 | 2011-04-27 | US08851424B2 | 2014-10-07 | Weber Brito Barbosa; Paulo Henrique Hasmann; Luciano Magno Fragola Barbosa |
| Methods and systems are provided to comply with structural load requirements applicable to aircraft additional fuel tank systems. A plurality of aircraft fuel tanks may 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. The tank body defining an interior space for holding aircraft fuel, an intercommunication conduit assembly between the fuel tank modules configured to refuel and transfer fuel from the tank modules by a cascade mode and an intentional air-filled ullage space are operatively associated with the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The intentional air-filled ullage is obtained through the predetermined positioning of the terminal open end of the intercommunication tube inside the respective fuel tank module. The intentional air-filled ullage can be configured in all or in only some of the fuel tank modules according to the design of the auxiliary fuel tanks or aircraft structural loads requirements. | ||||||
| 93 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176879 | 2014-02-10 | US20140224927A1 | 2014-08-14 | Donald Freund |
| 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. | ||||||
| 94 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176865 | 2014-02-10 | US20140224926A1 | 2014-08-14 | Donald Freund |
| A system for controlling a magnitude of a sonic boom includes a first sensor configured to detect a first condition of the supersonic aircraft. The system further includes a pair of wings configured to move fore and aft. The system further includes a processor communicatively coupled with the sensor and operatively coupled with the pair of wings. The processor is configured to (1) receive a first information from the first sensor indicative of the first condition, (2) calculate a lift distribution of the supersonic aircraft based on the first information, (3) determine an existence of a deviation of the lift distribution from a desired lift distribution based on the flight condition, and (4) control the pair of wings to move to redistribute the lift in a manner that more closely conforms to the desired lift distribution. The magnitude of the sonic boom is reduced when the deviation is reduced. | ||||||
| 95 | Fuel transfer monitoring system and method | US13129885 | 2008-11-19 | US08645045B2 | 2014-02-04 | Petter Sjungargard |
| A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks, the fuel monitoring system comprises a fuel quantity sensor arranged to measure the quantity of fuel in a first fuel tank and a data processor 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 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. | ||||||
| 96 | AIRCRAFT WITH A REFUELING DEVICE AND METHOD FOR CONTROLLING THE FLIGHT PATH OF AN AIRCRAFT DURING ITS REFUELING | US13478433 | 2012-05-23 | US20120318929A1 | 2012-12-20 | Burkhard Gölling |
| An aircraft with a refueling device for receiving fuel from a tanker aircraft in-flight is described, including an arrangement of flow influencing devices, an arrangement of flow condition sensor devices measuring flow conditions on respective surface segments, a flight data transmission device receiving flight data of a tanker aircraft, a flight path specification module that determines a nominal flight path or a nominal flight path corridor from the flight data of the flight data transmission device, and a flight control device configured to generate nominal commands for the flow influencing devices based on the measured flow condition and the nominal flight path or the nominal flight path corridor. These nominal commands control or maintain the movement of the aircraft along the nominal flight path or in the nominal flight path corridor. A method for controlling the flight path of an aircraft during the refueling thereof is also provided. | ||||||
| 97 | SYSTEMS AND METHODS TO PROVIDE COMPLIANCE WITH STRUCTURAL LOAD REQUIREMENTS FOR AIRCRAFT WITH ADDITIONAL FUEL TANKAGE | US13095615 | 2011-04-27 | US20110272526A1 | 2011-11-10 | Weber Brito BARBOSA; Paulo Henrique HASMANN; Luciano Magno Fragola BARBOSA |
| Methods and systems are provided to comply with structural load requirements applicable to aircraft additional fuel tank systems. A plurality of aircraft fuel tanks may 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. The tank body defining an interior space for holding aircraft fuel, an intercommunication conduit assembly between the fuel tank modules configured to refuel and transfer fuel from the tank modules by a cascade mode and an intentional air-filled ullage space are operatively associated with the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The intentional air-filled ullage is obtained through the predetermined positioning of the terminal open end of the intercommunication tube inside the respective fuel tank module. The intentional air-filled ullage can be configured in all or in only some of the fuel tank modules according to the design of the auxiliary fuel tanks or aircraft structural loads requirements. | ||||||
| 98 | METHOD OF CONTROLLING THE CENTRE OF GRAVITY OF AN AIRCRAFT | US13131209 | 2008-11-25 | US20110226906A1 | 2011-09-22 | Michael Spottiswoode; Antoine Burckhart; Petter Sjungargard |
| A method of controlling the centre 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. | ||||||
| 99 | FUEL TRANSFER MONITORING SYSTEM AND METHOD | US13129885 | 2008-11-19 | US20110224871A1 | 2011-09-15 | Petter Sjungargard |
| A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks, the fuel monitoring system comprises a fuel quantity sensor arranged to measure the quantity of fuel in a first fuel tank and a data processor 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 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. | ||||||
| 100 | Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity | US11637922 | 2006-12-13 | US07648103B2 | 2010-01-19 | 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. | ||||||
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