A powered clutch actuator assembly for integration with a clutch assembly is provided. The actuator and clutch assemblies, sized to fit within constraints of an aircraft landing gear wheel-mounted taxi drive system, are engineered to occupy a default neutral disengaged position that prevents torque transfer when torque to move the aircraft should not be transferred to the taxi drive system. Multiple solenoids and diodes power rotational motion of the actuator assembly to move a bi-directional clutch component in a desired rotational direction during torque transfer. A locking solenoid automatically locks and maintains the actuator assembly in a neutral disengaged condition when none of the solenoids are powered and disengages the actuator assembly when one solenoid is powered to cause rotation of the actuator assembly. Solenoid supports structured to operate as integral heat sinks may direct heat to an on-aircraft heat sink, prolonging the working life of the actuator assembly.
A lubrication distribution system is provided for mechanical systems, including gearboxes, to evenly and precisely apply lubricant to system structures during operation. The system includes a rotating lubrication distribution component that functions both to pump and to precisely direct lubricant. Machined locator elements enable accurate positioning of the rotating lubrication distribution component within the system. A plurality of lateral ports and surface features in the rotating lubrication distribution component receive and distribute lubricant transferred during rotation from one or more lubricant collection components with profiled lubricant transfer elements that enables collection of lubricant from eddies produced by profiles of the lubricant transfer elements during rotation of the rotating lubrication distribution component. Collected lubricant is directed into the rotating lubrication distribution component ports and distributed evenly and precisely to mechanical system or gearbox structures requiring lubrication. An existing gearbox thrust bearing may be modified to receive and precisely distribute lubricant.
A method for increasing airport airside parking locations without adding infrastructure to the airport is provided. Aircraft equipped with pilot-controllable landing gear wheel-mounted electric taxi drive systems for ground travel are maneuvered forward into remote tarmac stands or non-standard parking locations with the electric taxi drive systems, turned 180 degrees through tight turns, and parked in a nose-out orientation that enables the aircraft to efficiently unload and load passengers. The electric taxi drive systems drive the departing aircraft forward out of the parking locations. Remote tarmac parking locations may be located in areas that do not interfere with arrival and departure of aircraft parking at existing terminal stands. The present method may increase aircraft parking capacity at an airport, provide better utilization of existing tarmac space at the airport, reduce requirements for ground personnel on a per-flight basis, and improve airport ground operations efficiency.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A method is provided that reduces time to dock an electric taxi drive system-driven aircraft parking in a parallel orientation at an airport terminal. Passenger loading bridges are pre-positioned to substantially align with forward and rear doors of the aircraft. Pre-positioned passenger loading bridges extend from the terminal to locations that align with terminal-facing forward and rear doors when electric taxi systems maneuver the aircraft into the parallel parking orientation. The passenger loading bridge connected to a rear door may be pre-positioned at a height above the ramp surface above or below the height of the aircraft's horizontal stabilizer or below the height of the wing to enhance safety and further reduce connection and passenger transfer time. Connection of the pre-positioned passenger loading bridges with the aircraft doors should require only minimal adjustment before passenger transfer between the aircraft and terminal may begin.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64F 1/305 - Passerelles reliant l'aérogare et un aéronef, p. ex. télescopiques, réglables en hauteur
5.
Aircraft engine health monitoring system and method
A system and method are provided that monitors ground level ambient air in an airport ground environment while aircraft equipped with electric taxi drive systems and ground level visual monitoring assemblies are driven with the electric taxi drive systems during ground travel. Monitoring assemblies with detection elements having configurations similar to pitot tubes modified with a sensor array are provided to generate data about components in the ground level ambient air identified to adversely affect aircraft engine health. The detection elements may be cooperatively mounted with the ground level visual monitoring assemblies. Ambient air flow is directed into the detection elements to contact the sensor array during electric taxi drive system-powered ground travel. Real time data related to the identified components generated by the sensor array is processed and analyzed, engine health is monitored, and a predictive scheduled of engine maintenance may be developed from the analyzed real time data.
G01N 1/22 - Dispositifs pour prélever des échantillons à l'état gazeux
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
B64D 45/04 - Aides à l'atterrissageDispositifs de sécurité pour éviter la prise de sol brutale
6.
Aircraft electric taxi system design and operation
A method for designing and operating aircraft nose landing gear wheel-mounted electric taxi systems to move aircraft during ground travel. Electric taxi system components are engineered and sized to produce optimal ground travel torque to move aircraft during the majority of aircraft ground travel and are operated in conjunction with the aircraft steering to turn the nose wheels to an effective angle that moves the aircraft during pushback and in breakaway situations. The nose landing gear wheels are turned to an effective angle and the electric taxi systems are operated simultaneously to get the aircraft moving. After breaking away, the aircraft is driven with electric taxi systems at the optimal ground travel torque in a forward or reverse direction with the nose wheels parallel or in a desired ground travel direction with the nose wheels steered in the desired direction of ground travel.
The present invention provides a method for maneuvering and aligning aircraft equipped and driven during ramp ground travel with landing gear wheel-mounted electric taxi drive systems that have deviated from taxi line travel paths and for maneuvering the electric taxi drive system-driven aircraft to park accurately to align with locations of parking stops when the aircraft nose landing gear wheels stop beyond or short of a parking stop. The aircraft pilot can, without waiting for a tug or starting aircraft engines, precisely maneuver the aircraft with the electric taxi drive systems while viewing the taxi line and parking stop location in real time with an optional camera and sensor system while maneuvering the aircraft in forward or reverse and lateral directions to align the aircraft nose wheels with the taxi line path and to accurately position the nose landing gear wheels at the parking stop.
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A system and a method are provided for safely and efficiently transferring cargo and freight packed in ULD containers directly between an airport freight terminal and freight aircraft. An enclosed freightway is designed to provide a direct connection between the freight terminal and aircraft cargo doors. The enclosed freightway is structured and sized to move ULD containers automatically or manually between freight aircraft and freight terminals. Different freightway configurations enable direct connection between the freight terminal and freight aircraft main cargo door when freight aircraft are driven by electric taxi drive systems or aircraft engines and parked in nose-in orientations and when freight aircraft are driven by electric taxi drive systems and parked in parallel orientations at the freight terminal. An alternative embodiment provides direct connections between freight aircraft cargo doors and interior loading docks for aircraft driven with electric taxi drive systems.
An integrated pushback guidance system and method is provided for guiding pushback travel of electric taxi system-driven aircraft. The pushback guidance system may be integrated with existing ramp monitoring systems to monitor reverse pushback travel of pilot-controlled electric taxi system-driven aircraft along an optimum pushback path from a stand to a pushback end location. Visual signals relating to pushback travel safety as the pilot drives the aircraft along the pushback path are generated in real time by the system and transmitted to a range of display devices viewable by the aircraft pilot and airport personnel responsible for guiding aircraft pushback. The pilot may be guided by visual signals on only display devices or with guidance from airport personnel also viewing the visual signals on display devices to drive the aircraft safely in reverse with the electric taxi system along the pushback path to the pushback end location.
B64F 1/12 - Installations au sol ou installations pour ponts d'envol des porte-avions pour l’ancrage des aéronefs
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64F 1/22 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manœuvre des aéronefs
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
10.
Aircraft ground travel monitoring system with integrated cockpit head-up display system
A system and method are provided that direct a real time global view with images of an aircraft's entire exterior environment from an external monitoring system located on an aircraft equipped with landing gear wheel-mounted electric taxi drive systems powering ground travel to an integrated head-up display worn by a pilot driving the aircraft with the electric taxi drive systems within an airport ramp area. The real time global view and images produced by the monitoring system are communicated to the integrated head-up display in the form of an actual picture of the ramp area environment exterior to the aircraft viewable by the pilot with the head-up display in real time as the pilot maneuvers the aircraft within the ramp area with the electric taxi systems. The pilot can change the images viewed in the head-up display by changing head position.
A method is provided that extends available aircraft engine warm up and cool down times without extending total aircraft time on the ground. Aircraft that have engines with longer than average or longer than typical warm up and cool down times and are equipped with electric taxi systems are driven during hybrid taxi-out and taxi-in periods when the aircraft engines at lowest throttle settings are operating simultaneously with the electric taxi drive systems to move the aircraft during ground travel. The hybrid taxi-out and taxi-in periods ensure optimal steady, even warm up and cool down of engine components by takeoff and upon arrival and avoid thermally-induced structural deformations of engine components that adversely affect engines during flight. Aircraft engines may be designed to rely on the extended warm up and cool down times provided by the hybrid taxi periods without increasing aircraft ground travel time or negatively impacting airport operations.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A stator core design and motor winding method maximizing slot fill are provided. A stator core ring section and open U-shaped slot elements are each formed of multiple layers of lamination steel. Laminations forming the slots have a U-shaped profile corresponding to that of the slots. A straight portion of each lamination adjacent to the slot opening is folded to form stator teeth. Laminations forming the ring section and the slots may have a uniform or variable axial thicknesses and materials. A movable jig configures conducting wire and insulating material into a desired configuration for insertion into the open slots, fills each slot with the wire and insulating material, and partially crimps the open end of the filled slot, leaving an opening. When all slots are filled, the stator core is compressed to a final diameter, inserted into a ring-shaped stator element, and sealed to form a complete stator assembly.
H02K 1/16 - Noyaux statoriques à encoches pour enroulements
H02K 15/10 - Application d'un isolant sous forme solide à des enroulements, des stators ou des rotors, p.ex. application de rubans isolants
H02K 15/085 - Exécution des enroulements par pose des conducteurs dans ou autour des parties formant le noyau par pose des conducteurs dans des stators encochés
H02K 15/02 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques des corps statoriques ou rotoriques
13.
Airport parking system for electric taxi driven aircraft
A system is provided that guides aircraft driven with landing gear wheel-mounted electric taxi drive systems without reliance on airport ground personnel to park the aircraft parallel to an airport terminal with connections to multiple passenger loading bridges, automatically docks the aircraft, and connects the multiple loading bridges to multiple forward and rear doors. Cooperative on-aircraft monitoring systems, airport docking systems, loading bridge and terminal monitoring systems, and processors are integrated to use real time information and guide the aircraft to safely maneuver into and automatically dock in a parallel orientation at a parking location with multiple aircraft forward and rear doors connected to multiple loading bridges. The system may automatically undock the aircraft and retract the loading bridges and guide the electric taxi drive system-driven aircraft out of the parking location without reliance on airport ground personnel.
A monitoring system and method are provided for real time monitoring of flaps, landing gears, or tail skids to determine safe taxi, takeoff, and flight readiness. Monitoring units, including scanning LiDAR devices combined with cameras or sensors, mounted in aircraft exterior locations produce a stream of meshed data that is securely transmitted to a processing system to generate a real time visual display of the flaps, landing gears, or tail skid for communication to aircraft pilots to ensure safe aircraft taxi, takeoff, and flight readiness. Actual flap position alignment with optimal flap setting, proper retraction and extension positions of landing gears, and tail skid condition is ensured. Safety of aircraft taxi, takeoff and flight and airport operations are improved when the present system and method are used to prevent incidents related to misaligned flaps and improperly positioned landing gears or tail skids.
Reduced and low work function materials capable of optimizing electron emission performance in a range of vacuum and nanoscale electronic devices and processes and a method for reducing work function and producing reduced and low work function materials are described. The reduced and low work function materials advantageously may be made from single crystal materials, preferably metals, and from amorphous materials with optimal thicknesses for the materials. A surface geometry is created that may significantly reduce work function and produce a reduced or low work function for the material. It is anticipated that low and ultra-low work function materials may be produced by the present invention and that these materials will have particular utility in the optimization of electron emissions in a wide range of vacuum microelectronics and other nanoscale electronics and processes.
C30B 33/00 - Post-traitement des monocristaux ou des matériaux polycristallins homogènes de structure déterminée
C30B 29/60 - Monocristaux ou matériaux polycristallins homogènes de structure déterminée caractérisés par leurs matériaux ou par leur forme caractérisés par la forme
B82Y 10/00 - Nanotechnologie pour le traitement, le stockage ou la transmission d’informations, p. ex. calcul quantique ou logique à un électron
An integrated monitoring system and method are provided with the capability for monitoring ground surface movements of electric taxi drive system-driven aircraft, ground vehicles and personnel, and objects within airport ramp areas. Monitoring units may include a scanning LiDAR device with and without cameras or other sensing devices to transmit meshed real time encrypted data from multiple locations to an artificial intelligence-based processing system that generates a visual display of the monitored area for communication to aircraft cockpits and locations responsible for controlling ramp operations. Monitoring units may be mounted in single or multiple exterior locations on aircraft and/or in locations on ground vehicles and equipment, ground personnel, and the airside portion of an airport terminal.
B64F 1/305 - Passerelles reliant l'aérogare et un aéronef, p. ex. télescopiques, réglables en hauteur
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G01S 17/933 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour prévenir les collisions d’aéronefs ou d'engins spatiaux
B64D 43/00 - Aménagements ou adaptations des instruments
G01S 17/86 - Combinaisons de systèmes lidar avec des systèmes autres que lidar, radar ou sonar, p. ex. avec des goniomètres
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
An improved ground collision avoidance system and method is provided for aircraft driven during ground operations by electric taxi drive systems. One or more monitoring devices employing scanning LiDAR technology may be mounted in exterior locations on or near aircraft landing gears or aerodynamically in locations on the aircraft fuselage selected to generate panoramic three-dimensional images from any point of view within or without the aircraft as the aircraft is driven independently within an airport ramp area. The point of view images are transmitted in real time to displays in the aircraft cockpit and may be transmitted to displays outside and remote from the aircraft, allowing the pilot and airport personnel to monitor the aircraft moving within the ramp environment and to respond quickly to control the aircraft's electric taxi drive system-powered ground travel to avoid and prevent a potential collision.
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
An epicyclic gearbox with an integral arrangement of meshing gear elements, including an annulus gear, planet gears, and sun gears, to transfer power from a motive power source to a driven element with a range of applications is provided. The annulus gear, in contact with the power source, forms an exterior gearbox input and is in meshing contact with a number of stepped planet gears supported on floating planet carriers. Each stepped planet gear is positioned internally of the annulus gear and includes two planet stages in meshing contact with corresponding sun gear stages. One of the sun gear stages is an interior gearbox output and transfers power to a machine or device to be driven. Meshing surfaces of the gear elements support helical teeth or spur teeth, with numbers of teeth on meshing gear elements selected for optimal torque transfer from the exterior input to the interior output.
F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
19.
Cockpit control system for controlling ground travel in aircraft equipped with engine-free electric taxi system
A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with engine-free electric taxi drive systems are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi drive systems or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64D 43/00 - Aménagements ou adaptations des instruments
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
20.
Aircraft electric taxi system design and operation
A method for designing and operating an aircraft nose landing gear wheel-mounted electric taxi system to move aircraft with optimal torque during a broad range of ground travel conditions. Electric taxi system components may be sized to produce optimal ground travel torque to move aircraft during the majority of aircraft ground travel conditions and operated to produce a maximum or breakaway torque to move the aircraft with the electric taxi system when a higher level of torque is required. Turning the nose landing gear wheels to a selected angle or through a range of angles simultaneously as the electric taxi system is operated produces the breakaway torque required to get the aircraft moving. When lower torque is needed, the aircraft may be driven with the nose landing gear wheels parallel to the longitudinal axis to produce optimal torque for electric taxi system-powered aircraft ground travel.
An apparatus for supporting an air handling unit during servicing may comprise a support tray which defines a space for receiving the unit and may include opposite sides and opposite ends, with a front side and top of the tray being substantially open such that the is movable through the front side into the support tray. The apparatus may also include a support frame supporting the support tray above a ground surface and wheels on the support frame. The support frame may be configured to permit the tray to tilt end to end with respect to the support frame to adjust heights of the ends and to permit the tray to tilt side to side with respect to the support frame to adjust a height of the front side of the tray.
A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
F16D 11/14 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement avec des organes d'embrayage mobiles selon l'axe uniquement
A wobble gear system is provided with an arrangement of gear elements that permits a motive input to drive planet gear elements to increase the gear reduction ratio while maximizing efficiency of the wobble gear system. The wobble gear system may have eccentrically rotating or oscillating wobble elements including a wobble plate and compound planet gear elements that are non-collinear and may be driven by the motive input, increasing the realized gear ratio in a single stage without reducing efficiency. One wobble gear system embodiment may employ a plurality of ring-supported and driven compound planet gear elements with laterally offset non-collinear central axes to optimize eccentricity and enhance gear reduction ratios. The wobble gear system may be integrated with components of a vehicle drive wheel driven by an in-wheel motor to produce speeds and torques required to drive vehicles including automobiles and aircraft.
F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
F16H 35/00 - Transmissions ou mécanismes ayant d'autres caractéristiques de fonctionnement particulières
F16H 13/08 - Transmissions pour transmettre un mouvement rotatif à rapport de vitesse constant par friction entre des organes rotatifs avec organes à mouvement orbital avec billes ou rouleaux agissant de manière analogue
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
F16H 57/08 - Parties constitutives générales des transmissions des transmissions à organes à mouvement orbital
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
24.
Force limiting system and method for limiting loads in a powered aircraft landing gear drive wheel
A force limiting system and method are provided for limiting loads in aircraft nose or main landing gear having wheels powered by taxi drive systems mounted within the landing gear wheels to drive aircraft on the ground. The force limiting system may include mechanical components selected to limit or minimize spin-up mass and to releasably connect the taxi drive system to a landing gear wheel section so that operation of the taxi drive system to drive a landing gear wheel is prevented in the presence of a predetermined maximum load. The load limiting system employs mechanical components engineered to securely connect the taxi drive system to the landing gear wheel during operation and to release the taxi drive system from connection to the wheel when loads applied to system components exceed an established or recommended maximum load.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A clutch driven aircraft electric taxi system is provided with a clutch assembly designed to be automatically selectively engaged or disengaged as required to drive an aircraft autonomously during ground operations. The clutch assembly is mounted integrally with other electric taxi system components completely within an aircraft landing gear wheel and may be designed with one way overrunning or selectable clutch engagement capability in one or both rotational directions, preferably using an arrangement of ratcheting struts and clutch elements adapted specifically for use in an aircraft landing gear drive wheel environment. The clutch assembly may automatically disengage in response to predetermined defined conditions or operating parameters. A failsafe overrunning capability ensures that the clutch assembly will not engage taxi system drive components so that an aircraft's wheel will not be driven during aircraft operation when safety considerations dictate that the aircraft electric taxi system should not be engaged.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
F16D 41/12 - Roues libres ou embrayages à roue libre avec cliquet articulé coopérant avec des dents, des tenons ou des éléments analogues
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
F16D 41/06 - Roues libres ou embrayages à roue libre avec organes d'accouplement intermédiaires d'arrêt entre une surface intérieure et une surface extérieure
26.
Method for maximizing powered aircraft drive wheel traction
A method for maximizing traction in an aircraft drive wheel powered by non-engine drive means controllable to move the aircraft on the ground without reliance on the aircraft's brakes and dependence on friction defined by a mu-slip curve. The non-engine drive means is operated to control wheel speed and maintain the powered drive wheel in a maximized optimal traction condition when driving torques are applied to the drive wheel. Traction can be automatically maximized and maintained within an optimal range defined by a relationship between slippage and braking for maximum efficiency of aircraft ground travel under a wide variety of surface, weather, temperature, tire, and other conditions.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
27.
Method for using aircraft wheel tyre pressure to improve aircraft energy efficiency and drive system performance
A method is provided that enhances wheel drive assembly acceleration, heat reduction, and energy efficiency performance during ground travel in aircraft equipped with landing gear wheel-mounted drive assemblies to move aircraft on the ground without reliance on the aircraft's engines or external tow vehicles. Inflation pressure levels of tyres on the landing gear wheels are monitored with pressure and/or temperature sensors to determine and maintain an optimum defined high inflation pressure level for the specific kind of aircraft tyre or the aircraft. A clutch-activated drive assembly may be prevented from transferring torque and driving the aircraft when the optimum high inflation pressure levels are not present in the tyres during ground travel. Tyre pressures may be manually or automatically adjusted in response to processed sensor information to maintain the optimum high inflation pressure level in all tyres as the aircraft is driven with the drive assemblies or with engine thrust.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
28.
Clutch assembly for aircraft drive wheel drive system
A clutch assembly for an aircraft drive wheel drive system to move an aircraft independently on the ground is provided. The clutch is mounted within an aircraft drive wheel to be operatively engaged and disengaged to selectively actuate a roller traction or other drive system to activate a non-engine drive means to drive the wheel and the aircraft. One embodiment of the clutch assembly includes a plurality of pivoted sprag elements selectively activatable to transmit torque between inner and outer clutch members and activate the drive wheel drive system. The clutch assembly may also include mating crown gear and straight gear elements integrated with the drive system to reduce stresses on the drive system as the drive means is actuated. Various arrangements of sprags and clutch assembly components may be provided to monitor and selectively control disengagement of the clutch assembly and communicate disengagement to selectively prevent drive system actuation.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
F16D 41/06 - Roues libres ou embrayages à roue libre avec organes d'accouplement intermédiaires d'arrêt entre une surface intérieure et une surface extérieure
F16D 41/12 - Roues libres ou embrayages à roue libre avec cliquet articulé coopérant avec des dents, des tenons ou des éléments analogues
B60K 17/14 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission le moteur de la transmission à fluide ou électrique étant disposé dans la roue motrice ou la jouxtant
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
B60K 17/02 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type d'embrayage
29.
Space-maximizing clutch arrangement for vehicle drive wheel
A vehicle wheel drive assembly, particularly useful in an aircraft, is provided. The vehicle wheel drive assembly is mounted completely within a space defined by structural dimensions of a vehicle wheel and includes a drive means controllable to power the wheel and move the vehicle autonomously on a ground surface, a gear assembly drivingly connected to the drive means, and a clutch assembly operatively connected to the gear assembly. The clutch assembly is operatively mounted with respect to the gear assembly completely within an interior portion of a vehicle wheel axle on which the wheel drive assembly is mounted, thereby maximizing the space functionally available for all of the other components of the wheel drive assembly.
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
B60K 17/02 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type d'embrayage
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
F16D 11/14 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement avec des organes d'embrayage mobiles selon l'axe uniquement
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
An identification system and method are provided for aircraft equipped with electric taxi systems for autonomous ground movement that enables airport ground personnel and others outside the aircraft to safely and easily identify the aircraft moving on ground surfaces at an airport as equipped with a pilot-controlled electric taxi system and to distinguish these aircraft from aircraft not moved by electric taxi systems. The identification system may be mounted with nose or main landing gear drive wheels supporting the electric taxi system. The identification system includes an identifying lighting system with lighting elements of a selected number, shape, color, or arrangement positioned on at least a visible face of one or more landing gear wheels. Automatic or manual controls may actuate the identification system to identify electric taxi system-equipped aircraft when the aircraft are moved with the electric taxi system or are stopped.
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
B64D 47/06 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage pour signaler la présence de l'aéronef
B64D 45/08 - Aides à l'atterrissageDispositifs de sécurité pour éviter la prise de sol brutale optiques
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
32.
Torque transmission in an aircraft drive wheel drive system
A torque transmission system is provided for an aircraft drive wheel drive system mounted on nose or main landing gear wheels to move the aircraft autonomously on the ground that effectively transmits torque through drive system components. The drive system includes a drive means capable of generating sufficient torque to move the aircraft, a drive system capable of generating a high torque capacity that activates the drive means, a clutch assembly that can be selectively engaged to control torque transmission to the drive system and activate the drive means, and a landing gear torque takeout element. The clutch assembly is configured to be inactivated and prevented from transmitting torque to other drive wheel drive system components when an overtorque event occurs. Aircraft drive wheel drive system components in the present torque transmission system are designed to withstand torque in excess of a determined maximum for the system.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
33.
Space-maximizing clutch arrangement for vehicle drive wheel
A vehicle wheel drive assembly, particularly useful in an aircraft, is provided. The vehicle wheel drive assembly is mounted completely within a space defined by structural dimensions of a vehicle wheel and includes drive means controllable to power the wheel and move the vehicle autonomously on a ground surface, a gear assembly drivingly connected to the drive means, and a clutch assembly operatively connected to the gear assembly. The clutch assembly is operatively mounted with respect to the gear assembly completely within an interior portion of a vehicle wheel axle on which the wheel drive assembly is mounted, thereby maximizing the space functionally available for all of the other components of the wheel drive assembly.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
34.
Clutch driven aircraft electric taxi system and method
A clutch driven aircraft electric taxi system is provided with a clutch assembly designed to be automatically selectively engaged or disengaged as required to drive an aircraft autonomously during ground operations. The clutch assembly is mounted integrally with other electric taxi system components completely within an aircraft landing gear wheel and may be designed with one way overrunning or selectable clutch engagement capability in one or both rotational directions, preferably using an arrangement of ratcheting struts and clutch elements adapted specifically for use in an aircraft landing gear drive wheel environment. The clutch assembly may automatically disengage in response to predetermined defined conditions or operating parameters. A failsafe overrunning capability ensures that the clutch assembly will not engage taxi system drive components so that an aircraft's wheel will not be driven during aircraft operation when safety considerations dictate that the aircraft electric taxi system should not be engaged.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with an engine-free electric taxi system are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi system or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64D 43/00 - Aménagements ou adaptations des instruments
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
A monitoring system is provided to ensure continued efficient reliable operation of an aircraft drive wheel drive system, preferably an aircraft drive wheel drive system driven by actuating drive system-actuated drive means, designed to drive an aircraft autonomously during ground operations. The monitoring system includes an array of sensor elements capable of obtaining desired information relating to selected drive system operating parameters and performance indicators during aircraft ground operations. The sensor elements are designed to be functionally located externally of drive system components to obtain information during aircraft ground movement under a range of operating conditions. The operating parameters and/or performance indicators to be monitored preferably include at least drive wheel speed and direction, drive means speed, drive means temperature, and drive means clutch engagement. It is contemplated that the monitoring system could be expanded to include sensors for additional drive system parameters and/or performance indicators.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A method for increasing the effective value and extending the economic life of aircraft is provided. When older or new aircraft are enabled and controlled to move autonomously on the ground without reliance on aircraft engines or external tow vehicles by equipping the aircraft with cost-saving wheel drive systems controllable to move the aircraft autonomously on the ground, substantial reductions in aircraft operating costs can be realized, and the value of aging airline fleets, as well as new aircraft, can be increased significantly. Unexpected reductions in aircraft effective economic age and increases in value can be achieved, particularly when aircraft equipped with cost-saving wheel drive systems experience large numbers of short flights and a large amount of taxi time.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
38.
Method for increasing value of airport terminal exterior advertising
A method for increasing and optimizing the value of airport terminal exterior advertising is provided that significantly increases exposure of exterior advertising displays on the airside or non-public side of an airport terminal to passengers on arriving, parked, and departing aircraft. The movement of aircraft equipped with non-engine drive means on landing gear wheels for autonomous ground movement is controlled within an airport ramp area so that the aircraft moves in only a forward direction toward and away from a terminal parking place and parks in an orientation parallel to the terminal. The direction and orientation of aircraft ground travel and parking parallel to a terminal enhances and improves the visibility of exterior advertising displays to a maximum percentage of the passengers in the aircraft as the aircraft travels within the ramp area and parks between arrival and departure.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 3/00 - Commande de la position ou de la direction
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
G09F 15/02 - Placards, affiches ou moyens d'information analogues pour ceux-ci
G06Q 30/02 - MarketingEstimation ou détermination des prixCollecte de fonds
G09F 23/00 - Publicité sur ou dans des articles spécifiques, p. ex. cendriers, boîtes aux lettres
39.
Training system and simulation method for ground travel in aircraft equipped with non-engine drive means
A training system and method for operating aircraft equipped with non-engine drive means during independent ground travel is provided. The system and method of the present invention is designed specifically to train pilots, ground personnel, and air traffic control to move an aircraft safely and efficiently on the ground during taxi and pushback using the aircraft's non-engine drive means to propel the aircraft independently during ground travel. Simulations and procedures for training pilots and ramp personnel in the conduct of pushback operations and forward taxi with an aircraft equipped with non-engine drive means are also provided.
A surface travel system for military aircraft is provided that enables efficient, quiet, and safe ground operations of one or more aircraft in a wide range of military missions and operations. The surface travel system includes controllable onboard drive means that effectively drives one or more of the aircraft's wheels to move the aircraft autonomously, efficiently, quietly, and safely on any travel surface required for a military mission. The present invention allows the rapid safe deployment of multiple aircraft from tight spaces and enhances the readiness and availability of aircraft for a wide range of military operations.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
41.
Method for defining and controlling aircraft taxi profile
A system and method are provided for defining, optimizing, and controlling taxi profiles for aircraft equipped with onboard non-engine drive means controllable to drive one or more nose or main landing gear wheels to drive an aircraft autonomously during taxi. An onboard taxi profile control system may employ smart software to determine selected taxi operational data at an airport and use this data to control and maintain torque of the drive means at desired selected levels that move the aircraft during taxi in response to determined taxi data or predetermined programmed taxi parameters. The system is designed to set default taxi profiles for each taxi cycle to achieve efficient aircraft taxi and to extend operational life of drive means components. Taxi profiles are modified and updated at periodic intervals or in real time in response to actual taxi conditions to optimize aircraft taxi at a specific airport.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 17/02 - Commande d'un coupleCommande de la puissance mécanique caractérisée par l'utilisation de moyens électriques
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
42.
Electric vehicle traction control system and method
A traction control system and method are provided for electric vehicles with at least one drive wheel powered by an electric drive motor to maintain optimum maximum traction while the vehicle is driven on the ground. The traction control system includes drive means capable of transmitting torque through a vehicle drive wheel and controllable to move the vehicle over a ground surface. A preferred drive means is an electric motor designed to move the vehicle at desired ground speeds in response to operator input. Operator input requests a desired speed, and the system determines drive wheel torque required to produce the desired speed and provides maximum current to produce maximum torque to drive the vehicle with optimum traction at the desired speed. The system uses constant feedback to find maximum current corresponding to torque required for an inputted speed request to automatically control traction in any electric powered vehicle.
B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p. ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désiréesAdaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p. ex. vitesse, couple, variation programmée de la vitesse
B60L 7/00 - Systèmes de freins électrodynamiques pour véhicules, en général
B60L 7/18 - Freinage dynamo-électrique par récupération commandant l'effet de freinage
B60L 11/14 - avec possibilité de propulsion mécanique directe
B60L 11/18 - utilisant de l'énergie fournie par des piles primaires, des piles secondaires ou des piles à combustibles
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A powered aircraft wheel is designed to include multiple wheel sections configured to define a cavity within the wheel and to support completely within the wheel cavity an onboard non-engine drive means controllable to move an aircraft autonomously without reliance on aircraft engines during taxi and ground travel. Each part of the powered wheel may be constructed of a material specifically selected to emphasize a functional property of the material that is optimal for the function of the wheel part at a specific location. The selected combination of functionally distinct materials gives the powered aircraft wheel a unique optimal structural and functional capability.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
This application describes the software invented to control a dual electric motor system. The dual electric motor system is a Chorus Motor system applied to electric drive for aircraft taxi. The software uses closed-loop control together with several other control laws to operate the motors. Knowledge of the current operating state of the motors, together with knowledge of the commands given to taxi forward, taxi in reverse, or brake in reverse, is used to configure the motors to optimal operating parameters. The software architecture is described along with the pilot interface and many details of software implementation.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
46.
Method for adding value to operation of long haul aircraft
A method is provided for adding available takeoff and landing slots when aircraft designed for long haul flight are moved quietly and efficiently on the ground without operation of aircraft engines at airports with slot controls and airports that are constrained from operation at certain times by curfews that limit operating hours for these long haul aircraft. Long haul aircraft are powered and driven by onboard non-engine drive means or moved manually or automatically by tugs, tow vehicles, or other transfer apparatus to arrive at a runway before expiration of a morning curfew and to be ready for takeoff as soon as curfew is lifted. Long haul aircraft may land immediately before an evening curfew starts and to move without engines to an airport arrival location after evening curfew starts, effectively expanding and increasing the number of available takeoff and landing slots for long haul aircraft.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projetsPlanification d’entreprise ou d’organisationModélisation d’entreprise ou d’organisation
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
An auxiliary drive wheel taxi system for driving an aircraft autonomously without reliance on engine operation during ground travel is designed for installation in an aircraft location other than on nose or main landing gear components. The auxiliary drive wheel taxi system may be mounted in an integral housing located internally or externally on an aircraft's body at a selected location relative to main or nose landing gears and includes one or more auxiliary drive wheels mounted on an extensible strut adapted to extend from and retract into the housing. An electric, hydraulic, or pneumatic non-engine drive means controllable to provide torque required to rotate the drive wheel and drive the aircraft at desired taxi speeds may be mounted in a selected location to drive the auxiliary drive wheel. The manually or automatically controllable auxiliary taxi system is operable only to drive the aircraft during taxi.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
48.
Electric power connector for aircraft drive wheel drive system
An electric connector assembly is provided that is designed to provide a simple and reliable electric connection between a source of electric power on an aircraft and a plurality of electrical connections, such as those from stator windings, in an electric drive means powering an aircraft landing gear drive wheel. The plurality of drive means electrical connections are individually connected to power distribution elements designed to significantly reduce the number of connectors required to establish an electrical connection between the drive means and an aircraft power supply. The reduced number of connectors is directed out of the wheel and guided along a path by a path guide element to a connector element designed to connect directly with a wire harness or other connection with an aircraft source of electric power. This electric connector design facilitates disconnection and reconnection when removal and remounting of the drive wheel is required.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
A controllable aircraft taxi system is provided that enables the simultaneous control of aircraft autonomous ground movement and direction of aircraft autonomous ground movement. Independently controlled non-engine drive means capable of driving an aircraft landing gear wheel to move an aircraft autonomously on the ground without reliance on the aircraft's main engines are mounted to provide driving torque to aircraft a selected number of main landing gear wheels. The aircraft nose landing gear steering system is provided with steering angle detection and measurement means adapted to communicate with main landing gear wheel non-engine drive means, enabling simultaneous control over both autonomous aircraft ground travel and direction of autonomous aircraft ground travel. The present invention overcomes steering challenges presented by using non-engine drive means on main landing gear wheels to drive aircraft autonomously during taxi.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
An aircraft passenger boarding system is provided for aircraft equipped for pilot-controllable engines-off taxi that enables a pilot to drive the aircraft without engines in a forward direction into and out of an optimum parallel or angled gate parking orientation that permits terminal connections to both forward and aft doors on a terminal-facing side of the aircraft. Selected defined classes of passengers board the aircraft separately, through a designated loading bridge connected to a forward door or through a designated loading bridge connected to an aft door, to be seated in a designated front or rear aircraft section. An airline may flexibly allocate variably sized sections of the aircraft interior for each defined class, depending on the relative numbers of passengers in each class. Airport terminal interior gate space may be used to separate passenger classes as required for separate boarding through a forward door or an aft door.
A system and method is provided for improving efficiency of aircraft gate services and reducing time spent by an aircraft parked parallel to an airport terminal wherein aircraft utilities and gate services provided during turnaround are supported by an arrangement of flexibly movable, service and utility-carrying extendable passenger boarding bridges that enable passenger and baggage exchange concurrently with connection of utilities and provision of gate services to the aircraft. Baggage transfer is facilitated by conveyors mounted on one or more loading bridges and designed to provide a direct connection between an aircraft and a terminal. Aircraft are maneuvered by a pilot into and out of a parallel parking location in a forward direction by an engines-off electric taxi system, enabling loading bridge, utility, and service connections to be made to multiple aircraft doors as soon as the aircraft reaches a parking location and then quickly disconnected upon departure.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64F 1/305 - Passerelles reliant l'aérogare et un aéronef, p. ex. télescopiques, réglables en hauteur
B64D 9/00 - Appareillage pour manutention du fretAppareillage pour faciliter l'embarquement des passagers ou autres
52.
Aircraft ground travel traction control system and method
A traction control system and method are provided for an aircraft equipped with a ground travel drive system with drive wheels powered by onboard wheel drive means that are capable of translating torque through the aircraft drive wheels and that are automatically controllable to control traction without reliance on the aircraft's brakes to keep the aircraft moving efficiently and autonomously on the ground under a range of environmental conditions.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
G05D 13/62 - Commande de la vitesse linéaireCommande de la vitesse angulaireCommande de l'accélération ou de la décélération, p. ex. d'une machine motrice caractérisée par l'utilisation de moyens électriques, p. ex. l'emploi de dynamos-tachymétriques, l'emploi de transducteurs convertissant des valeurs électriques en un déplacement
G05D 17/02 - Commande d'un coupleCommande de la puissance mécanique caractérisée par l'utilisation de moyens électriques
53.
Method for maintaining a supply of available aircraft equipped with non-engine drive means for use by airlines
A method for maintaining a supply of available aircraft equipped with non-engine drive means for autonomous ground movement is provided that enables an air carrier, particularly a low cost carrier, to operate reliably, efficiently, and economically to provide substantially uninterrupted air transport service. The present method is designed to enable airlines with fleets of older aircraft retrofitted with non-engine drive means for autonomous ground movement to operate economically and efficiently through a cooperative arrangement with a maintenance, repair, and overhaul provider that maintains and ensures an available supply network of spare and backup aircraft. The supply network may be global in geographic scope and may provide spare or backup aircraft equipped with non-engine drive means to one or more airlines.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projetsPlanification d’entreprise ou d’organisationModélisation d’entreprise ou d’organisation
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
54.
Airport terminal traffic and parking management system
An airport terminal traffic and parking management system, which can be automated, is provided wherein one or more and preferably a plurality of the aircraft at an airport are moved on the ground between landing and takeoff without operation of aircraft engines or risks from jet blast and engine ingestion. Aircraft can be moved in a forward direction by tow vehicles, aircraft-moving transfer apparatus, or the like after landing to park in an efficient orientation relative to an airport terminal. Passengers deplaning and boarding and aircraft servicing can use all accessible aircraft doors to minimize time at a gate. Aircraft cleared for departure can be turned and moved in a forward direction to a takeoff runway, where the aircraft-moving apparatus is detached. Airport terminal aircraft traffic and parking are most effectively managed when a significant number of aircraft at an airport are moved by external vehicles as described.
A permanent wireless onboard to ground operations communications system is provided for an aircraft equipped with a pilot-controllable drive wheel drive system for autonomous ground movement without reliance on the aircraft's engines or external tow vehicles, including an onboard wireless communications link installed to remain permanently with the aircraft designed to interface wirelessly with ground personnel at any airport, aerodrome, or airfield where the aircraft lands immediately upon landing. The permanent wireless onboard to ground operations communications system provides a substantially instantaneous connection between a pilot and ground personnel to facilitate guidance of pilot-controlled autonomous ground movement during taxi, parking in nose-in and parallel orientations, and pushback without reliance on visual signals. The present communications system establishes and maintains cockpit to ground communications during pilot-controlled autonomous aircraft ground movement to enhance the safety of ramp operations and improve the speed at which ramp operations can be safely conducted.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
An aircraft drive wheel drive system is provided with a torque coupling clutch assembly that transfers torque to a roller traction drive system actuating a non-engine drive means to drive an aircraft landing gear wheel and move the aircraft autonomously in a desired ground direction and at a desired ground speed. The wheel drive system and clutch assembly are mounted completely within the wheel where the clutch assembly is selectively engaged to control torque transmission to the drive system, which selectively transfers actuating torque to the non-engine drive means. A preferred selectable one way clutch is adapted to controllably transfer torque to the wheel drive system and has both failsafe overrunning and selective engagement capability in one or both rotational directions so that torque required to drive the aircraft wheel and move the aircraft at a desired ground speed and direction is transferred only when required by aircraft operating conditions.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60B 25/12 - Anneaux d'appui pour le talon du pneumatique, p. ex. fendu avec partie formant rive intégrée
F16D 41/16 - Roues libres ou embrayages à roue libre avec cliquet articulé coopérant avec des dents, des tenons ou des éléments analogues l'action étant réversible
A powered self push back method and system for an aircraft are provided to move an aircraft on the ground safely during push back without assistance from an external tug vehicle or the aircraft main engines. The method employs constant cooperative communication and signals between the pilot and the ground crew during the push back process to ensure that push back of the aircraft is safe, efficient, and reduces aircraft turnaround time. The powered self push back system used in conjunction with this method includes at least one powered self-propelled aircraft drive wheel powered by a wheel drive assembly that can be activated by pilot input controls or by remote control exteriorly of or interiorly to the aircraft in response to ground crew signals to activate the driver to rotate the drive wheel in a reverse, push back direction, causing the aircraft to move in the push back direction or in a forward direction for taxi and takeoff in accordance with activation of the controls.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
B64D 27/00 - Aménagement ou montage des groupes moteurs sur aéronefsAéronefs caractérisés par le type ou la position des groupes moteurs
58.
Sprag clutch assembly for aircraft drive wheel drive system
A sprag clutch assembly for an aircraft drive wheel drive system capable of moving an aircraft autonomously on the ground in both forward and reverse directions is provided. The clutch is mounted within an aircraft drive wheel to be operatively engaged to control drive means braking torque when the aircraft is driven in a forward or reverse direction. The clutch assembly includes a plurality of pivoted sprag elements activatable to transmit torque and configured so that ratcheting occurs only when the aircraft drive wheel is driven in a forward direction and a braking torque is applied when the aircraft drive wheel is driven in reverse when the relative speed of the drive system is slower than the drive wheel speed, thereby permitting the drive system drive motor to function as a brake when the clutch assembly is engaged and the aircraft is reversing.
F16D 41/069 - Roues libres ou embrayages à roue libre avec organes d'accouplement intermédiaires d'arrêt entre une surface intérieure et une surface extérieure les organes intermédiaires d'arrêt agissant en pivotant ou basculant, p. ex. cales
F16D 41/07 - Roues libres ou embrayages à roue libre avec organes d'accouplement intermédiaires d'arrêt entre une surface intérieure et une surface extérieure les organes intermédiaires d'arrêt agissant en pivotant ou basculant, p. ex. cales entre deux surfaces cylindriques
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
F16D 41/14 - Roues libres ou embrayages à roue libre avec cliquet articulé coopérant avec des dents, des tenons ou des éléments analogues la course effective du cliquet étant réglable
F16D 27/00 - Embrayages actionnés magnétiquementLeur commande ou leurs circuits électriques
B60B 25/12 - Anneaux d'appui pour le talon du pneumatique, p. ex. fendu avec partie formant rive intégrée
59.
Method for accelerated powered self push back of an aircraft
A method for accelerated power push back of an aircraft equipped with a pilot-controlled engines-off taxi system that drives the aircraft without reliance on the aircraft's main engines or tugs is provided. An aircraft is quickly and efficiently moved out of a gate where it is positioned in a nose-in orientation. The pilot controls the taxi system to drive the aircraft in reverse along a perpendicular path away from the terminal to a location where there is sufficient space for the aircraft to stop and turn, and the aircraft is turned and driven in a forward direction to a takeoff runway. Pilot reliance on ground personnel guidance during push back maneuvers is minimized by providing a monitoring system designed to monitor gate and ramp areas around the aircraft in any visibility or environmental conditions and provide feedback to the pilot.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
B64D 27/00 - Aménagement ou montage des groupes moteurs sur aéronefsAéronefs caractérisés par le type ou la position des groupes moteurs
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A method for monitoring an autonomous accelerated pushback process in an aircraft equipped with an engines-off taxi system is provided to maximize safety and facilitate the accelerated pushback process. The aircraft is equipped with a monitoring system including a number of different kinds of sensors and monitoring devices positioned to maximally monitor the aircraft's exterior ground environment and communicate the presence or absence of obstructions in the aircraft's path while the pilot is controlling the engines-off taxi system to drive the aircraft in reverse away from a terminal gate and then turn in place at a selected location before driving forward to a taxiway. The sensors and monitoring devices may be a combination of cameras, ultrasound, global positioning, radar, and LiDAR or LADAR devices, and proximity sensors located at varying heights adapted to continuously or intermittently scan or sweep the aircraft exterior and ground environment during aircraft ground movement.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G01S 15/93 - Systèmes sonar, spécialement adaptés à des applications spécifiques pour prévenir les collisions
G01S 17/93 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour prévenir les collisions
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p. ex. sonar, chercheur de direction
G01S 13/93 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour prévenir les collisions
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A method for reducing aircraft turnaround time by improving airport ramp safety is provided. The method minimizes the time interval between an aircraft's landing and takeoff by independently moving the aircraft on the ground without the aircraft's engines by eliminating hazards from jet blast, the possibility of engine ingestion, and the time previously required to wait in the gate area upon arrival or at departure until jet blast or engine ingestion did not pose a danger. Turnaround time is further reduced by providing an onboard driver controllable to drive at least one of the aircraft's wheels between landing and takeoff, thereby eliminating the need for a tow vehicle and the time required to move the aircraft with a tow vehicle.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
B64F 1/305 - Passerelles reliant l'aérogare et un aéronef, p. ex. télescopiques, réglables en hauteur
62.
Method for maximizing powered aircraft drive wheel traction
A method for maximizing traction in an aircraft drive wheel powered by non-engine drive means controllable to move the aircraft on the ground without reliance on the aircraft's brakes and dependence on friction defined by a mu-slip curve. The non-engine drive means is operated to control wheel speed and maintain the powered drive wheel in a maximized optimal traction condition when driving torques are applied to the drive wheel. Traction can be automatically maximized and maintained within an optimal range defined by a relationship between slippage and braking for maximum efficiency of aircraft ground travel under a wide variety of surface, weather, temperature, tire, and other conditions.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
63.
Heat dissipation system for aircraft drive wheel drive assembly
A system is provided for dissipating heat in an onboard non-engine powered aircraft wheel drive assembly with drive means that power one or more aircraft wheels to drive the aircraft autonomously on the ground without directly using the aircraft engines. The heat dissipation system is integral with a wheel drive assembly mounted substantially completely within a nose or main landing gear wheel. A reservoir mounted outboard or inboard of the wheel drive assembly increases thermal distribution mass and fluidically communicates with wheel drive assembly components to automatically circulate heat transfer fluid between the wheel drive assembly and the reservoir when the operating temperature exceeds a predetermined maximum temperature during aircraft ground travel. The heat dissipating system can be retrofitted in an existing aircraft to improve thermal distribution and prolong wheel drive assembly and drive means operation and useful life.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p. ex. de l'huile
H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
B60K 1/00 - Agencement ou montage des ensembles de propulsion électriques
B60K 11/02 - Dispositions des ensembles de propulsion relatives au refroidissement avec liquide de refroidissement
An efficient system and method are provided wherein aircraft may be retrofitted with non-engine drive means controllable to power landing gear wheels to move the aircraft autonomously during ground movement without engines or tow vehicles so that existing landing gear structures are employed to achieve force distribution and load transfer. Non-engine drive means capable of powering a landing gear wheel to move the aircraft during taxi are integrated into existing landing gear designs so that excess drive forces are transferred and distributed through previously evaluated and certificated landing gear structures, including tow fittings, determined to be capable of handling such forces, which eliminates changes to the landing gear and facilitates retrofit and certification. Engines-off taxi technology can be rapidly designed and developed to be retrofitted on existing aircraft nose and/or main landing gear and then efficiently certificated.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
65.
Integrated vehicle wheel motor structured to manage heat
A wheel design with heat management capability is provided for an aircraft landing gear wheel that is specifically configured to maximize the space available within a landing gear wheel well to support a geared motor assembly that drives the aircraft wheel when the aircraft is on the ground. A thermal interface between the geared motor assembly and a support wall effectively directs heat generated by brakes, motor, or gear components through the wheel ultimately to be shed entirely outside the aircraft to prevent damage to the wheel and motor components. The heat dissipating wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p. ex. des ponts de chaleur
B60K 11/00 - Dispositions des ensembles de propulsion relatives au refroidissement
66.
Airport terminal aircraft gate traffic management system and method
An airport terminal gate traffic management system is provided that maximizes efficiency and safety of passenger transfer and aircraft servicing and minimizes aircraft time parked at a terminal. Aircraft are driven forward into and out of gates by controllable landing gear wheel non-engine drive means and parked in a parallel or perpendicular orientation relative to the terminal that facilitates passenger transfer through a maximum number of aircraft doors. Passenger transfer and aircraft servicing may begin upon aircraft arrival using all available accessible aircraft doors. Departing aircraft may be turned by an unassisted pilot and driven forward with the controllable non-engine drive means to a takeoff runway. Airport terminal aircraft gate traffic is most effectively and efficiently managed when a significant number of aircraft using an airport are equipped with non-engine drive means controllable to move them into and out of a parking orientation optimal for passenger transfer.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64F 1/305 - Passerelles reliant l'aérogare et un aéronef, p. ex. télescopiques, réglables en hauteur
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
67.
Monitoring and control system for enhancing ground movement safety in aircraft equipped with non-engine drive means
An improved monitoring and control system capable of providing automatic control of ground movement in an aircraft equipped with non-engine drive means for autonomous ground movement to enhance airport ground safety and efficient ground travel is provided. The monitoring and control system is installed on aircraft equipped with non-engine drive means controllable to move the aircraft autonomously on the ground and includes monitoring means positioned in locations on the aircraft selected to obtain a maximum amount of information relating to an aircraft's ground position and operation, processor means, data transmission means, and manual or automatic control means to control and direct operation of an aircraft's non-engine drive means to move the aircraft autonomously, safely and efficiently on the ground. The improved monitoring and control system can be employed with one or a number of aircraft simultaneously to increase safety and efficiency of airport ground operations.
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
68.
Steering control in an aircraft equipped with a wheel drive system
Control of aircraft steering during ground travel is provided in an aircraft equipped with an engines-off wheel drive system controllable to move the aircraft autonomously on the ground without reliance on the aircraft's main engines or external tow vehicles. The wheel drive system is designed to interact with the aircraft's nose wheel hydraulic steering system to augment or replace the hydraulic steering system with the operation of the wheel drive system at taxi speeds, particularly at very low taxi speeds and even when the aircraft is stopped, to steer the aircraft as it maneuvers through turns during ground travel between landing and takeoff and at other times.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
A bearing arrangement for an aircraft landing gear wheel is provided that effectively supports the wheel on an axle while maximizing internal wheel volume available for mounting a non-engine drive motor used to power the wheel and/or brakes or other structures within the maximized wheel volume. The bearing arrangement is preferably employed with a two-part aircraft wheel mounted on a landing gear axle and includes bearing structures located only on wheel sections adjacent to the axle. A specifically configured cantilevered joint portion of inboard and outboard wheel sections supports weight and loads bearing structures, eliminating the need for and space required by a high speed bearing. Stiffness necessary for strength and structural integrity is provided by the materials selected to form the wheel sections.
B60B 19/06 - Roues non prévues ailleurs ou ayant des caractéristiques précisées dans l'un des sous-groupes du présent groupe avec des compartiments pour liquides, ou pour matériaux de remplissage ou de chargeRoues flottantes
B60B 37/10 - Combinaisons roue-essieu, p. ex. trains de roues les roues pouvant tourner individuellement chacune autour des essieux
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60B 25/04 - Jantes avec anneaux de rive, d'appui ou de verrouillage démontables
70.
Electric vehicle traction control system and method
A traction control system and method are provided for electric vehicles with at least one drive wheel powered by an electric drive motor to maintain optimum maximum traction while the vehicle is driven on the ground. The traction control system includes drive means capable of transmitting torque through a vehicle drive wheel and controllable to move the vehicle over a ground surface. A preferred drive means is an electric motor designed to move the vehicle at desired ground speeds in response to operator input. Operator input requests a desired speed, and the system determines drive wheel torque required to produce the desired speed and provides maximum current to produce maximum torque to drive the vehicle with optimum traction at the desired speed. The system uses constant feedback to find maximum current corresponding to torque required for an inputted speed request to automatically control traction in any electric powered vehicle.
B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p. ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désiréesAdaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p. ex. vitesse, couple, variation programmée de la vitesse
A method is provided for automatically or manually optimizing independent ground travel operation in an aircraft equipped with one or more self-propelled nose or main wheels powered by a driver means, wherein selected operating parameters indicative of optimized ground travel are monitored by sensors or detectors to provide data and information relating to the selected parameters during operation of the ground travel system. Selected operating parameters can include, for example, speed, direction of travel, torque, component thermal data, aircraft location data, and operator inputs, commands, and feedback, as well as other operational data or information. Data is collected, recorded, and analyzed to enable changes to be made to the ground travel system components in real time automatically by intelligent software or manually by a system operator or at a later time to ensure optimum operation of the system.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs
72.
Method for improving ground travel capability and enhancing stealth in unmanned aerial vehicles
A method for improving ground movement capability and enhancing stealth in unmanned aerial vehicles is provided. The present method comprises providing, in an unmanned aerial vehicle equipped with wheels, one or more onboard drive means capable of translating torque through the vehicle wheels and controllable to move the unmanned aerial vehicle on the ground without reliance on the unmanned aerial vehicle main motive power source. The onboard drive means is controllably powered by a power source with substantially no acoustic signature to move the unmanned aerial vehicle quietly on the ground with only a minimal audible or visible footprint. This method provides a significant expansion of ground movement capability and expands the potential ground uses of unmanned aerial vehicles, particularly in military applications. The present method can also be applied to move any manned aerial vehicle or aircraft on the ground with only minimal audible or visible footprints.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
73.
System and method for maintaining aircraft ground travel speed and direction
A system and method for setting, controlling, or maintaining a selected taxi speed and route for one or more aircraft equipped with an onboard non-engine powered drive means powering one or more aircraft wheels to move the aircraft during taxi is provided. Taxi speed and/or route can be set, maintained, or controlled by the aircraft pilot or ground traffic control in conjunction with taxi speed and travel of other aircraft and ground vehicles. A pilot activates a speed control to set and control taxi speed. The aircraft will automatically travel on the ground at that speed without input from the pilot until it is necessary to change the speed manually or automatically. Airport ground traffic control can generate taxi profiles for all non-engine driven aircraft to automatically control, subject to pilot capability to override, the taxi of multiple aircraft at an airport in conjunction with ground vehicle movement.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
The invention disclosed is a self-propelled aircraft undercarriage for driving an aircraft on the ground, comprising: an axle; a strut supporting said axle; at least one wheel rotatably mounted on said axle; and drive means for driving said at least one wheel; characterized in that said drive means is disk shaped and is external to said wheel. In one embodiment of the invention, said drive means is mounted on said axle between said strut and said wheel. In a second embodiment, said drive means is mounted on said axle, on the side of said wheel furthest from said strut.
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
75.
Drive system with harmonic drive for self-propelled aircraft wheel
A drive system with harmonic drive designed to meet the high power and torque requirements required to drive an aircraft independently on the ground is provided. The drive system includes an electric motor driven by a harmonic drive assembly that may be configured to be integral with the motor. This drive system with harmonic drive can be effectively installed in an existing aircraft nose wheel or main wheel without changes to other components.
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
76.
Integrated direct drive starter/generator for turbines
A starter/generator machine for a turbine with a turbine enclosure, an air duct, and a plurality of fan blades is provided. The starter/generator machine includes a plurality of stator elements spaced at intervals in a ring shape adjacent to the air duct and a plurality of rotor elements mounted on the fan blades. The stator elements and the rotor elements are mounted to interact magnetically to exert a force sufficient to move the rotor elements. The stator elements are shaped to minimize air flow interference and are formed with a core, at least one pole, and multiple windings. The spacing between the stator elements and the rotor elements forms an air gap on the order of 5-10 mm, and the number of stator elements is different from the number of rotor elements.
F02C 1/00 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de gaz chauds ou de gaz sous pression non chauffés, comme fluide de travail
77.
Method for enhancing pilot efficiency and aircraft safety during ground travel
A method for enhancing pilot and cockpit crew efficiency and increasing aircraft safety during aircraft ground travel between landing and takeoff is provided. The present method is most effective in enhancing pilot efficiency and aircraft safety in an aircraft equipped with at least one powered, self-propelled drive wheel that drives the aircraft on the ground independently of the aircraft main engines or external tow vehicles that is controlled by the pilot and cockpit crew to maneuver the aircraft during ground travel.
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
A compact in-wheel vehicle motor and gearing system designed to meet high power and torque requirements for driving a vehicle on the ground independently of other power sources is provided. The motor and gearing system includes a motor assembly with an outside rotor element mounted for rotation about an inside stator element and a gear assembly with a plurality of gear stages mounted inside the stator and drivingly connected to the motor assembly. The motor assembly and gear assembly are mounted interiorly of the wheel and completely within a space defined by the internal dimensions of the wheel. This motor and gearing system can be effectively installed in an existing aircraft wheel without changes to other components to produce a drive wheel with the torque and power required to move the aircraft independently on the ground.
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
B60L 3/00 - Dispositifs électriques de sécurité sur véhicules propulsés électriquementContrôle des paramètres de fonctionnement, p. ex. de la vitesse, de la décélération ou de la consommation d’énergie
B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p. ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désiréesAdaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p. ex. vitesse, couple, variation programmée de la vitesse
F16H 1/46 - Systèmes consistant en plusieurs trains d'engrenages, chacun comportant des engrenages orbitaux
79.
Split circumference aircraft wheel assembly with integrated drive motor assembly
A split circumference wheel assembly is provided for an aircraft landing gear wheel configured to maximize the space available within a landing gear wheel well to support a motor driver assembly with drive means that drives the aircraft wheel on the ground. The split circumference wheel assembly includes separable inboard and outboard support walls that are spaced axially apart a maximized distance so that the motor driver assembly is completely contained within the maximized space defined. A preferred wheel assembly employs a demountable flange and a locking ring to integrally and removably support the motor driver assembly within the maximized wheel volume to drive one or more aircraft wheels and move the aircraft independently on the ground. The wheel and motor driver assembly described herein are designed to be retrofitted in an existing aircraft wheel.
A method for extending the useful and economic life of an aircraft and improving aircraft efficiency is provided. This method produces significant fuel savings on the ground and in flight as well as cost-effective and efficient operation of and reduced maintenance requirements for older aircraft. The increased economic viability of the continued use of older aircraft is achieved by equipping an aircraft with at least one onboard drive wheel assembly controllably powered to drive the aircraft during ground travel independently of aircraft engines or external tow vehicles. The substantial elimination of damage to an aircraft's airframe, brakes, landing gear, and engine components resulting from tow vehicle attachment, brake application during ground travel with operating aircraft engines, or by FOD produces cleaner, more efficient engine operation during flight. Significant and substantial potential cost savings realized by the present method makes the continued use of older aircraft a viable option.
A failsafe system and method for ensuring the safe operation of an aircraft with a ground movement system to drive the aircraft independently on the ground is provided. The system includes at least one aircraft nose or main drive wheel powered by an onboard wheel driver responsive to sensed aircraft and ground movement system operating parameters to continue operation in response to parameters within normal limits or to prevent continued operation if sensed parameters are outside normal limits and indicate continued operation to be unsafe. The onboard wheel driver includes a locking assembly responsive automatically or manually to signals indicating sensed parameters to lock the onboard wheel driver in an activated or an inactivated condition, depending on whether operation of the ground movement system can be continued safely.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
82.
Integrated aircraft ground navigation control system
An aircraft ground control system that moves an aircraft on the ground between landing and take off without external mechanical assistance from airport tugs or tow vehicles or reliance on thrust produced by the aircraft's engines is provided. The aircraft ground control system interfaces only with an aircraft auxiliary power unit or other aircraft power supply, but otherwise operates independently of aircraft systems. A system integrator and controller links cockpit controls designed to actuate the transmission of power to system components and to activate system components only under predetermined conditions with selectively activatable drivers in driving connection with one or more aircraft wheels to move the aircraft on the ground at selected torques and speeds.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
This application describes the software invented to control an electric motor system. The electric motor system is mounted on one or more aircraft main wheels or nose wheels to drive an aircraft independently on the ground without aircraft engines or tow vehicles. The software uses closed-loop control together with several other control laws to operate the drive motor or motors. Knowledge of the current operating state of the drive motor, together with knowledge of the commands given to taxi forward, taxi in reverse, or brake in reverse, is used to configure the motors to optimal operating parameters. The software architecture is described along with the pilot interface and many details of software implementation.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G06F 17/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
An integral motor and wheel assembly for aircraft landing gear is provided that includes an electric motor packaged within at least one gear wheel and configured to fit completely within the space provided in an existing aircraft for the landing gear components. The motor is positioned within the wheel to minimize the spin-up weight and to maximize the space within a given volume allocated for the motor. Installation of this motor and gear wheel assembly in an existing aircraft landing gear is designed to permit the continued use of existing landing gear components, including tires, axles, and pistons, so that the assembly can be easily retrofitted into existing aircraft.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs
85.
Wheel structure for integrating an electric drive motor
A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a motor driver assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the motor driver assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
86.
Self-propelled undercarriage wheel having a low profile tire
An undercarriage wheel is disclosed comprising an axle member that supports a drive member, for example but not limited to a compact high torque electric motor, a wheel member driven by said drive member, and a tire attached to the wheel member, wherein the tire bulges in the width dimension of the wheel, wherein the drive member protrudes from the wheel member and thus occupies at least some of the additional width made available by the bulge of the tire. A further aspect of the invention is an undercarriage wheel that comprises an axle member that supports a drive member, for example but not limited to a compact high torque electric motor, a wheel member driven by said drive member, and a low-profile tire attached to the wheel member. Since the profile of the tire is low, additional space is available inside the wheel for the drive member. Preferably, the drive member occupies at least some of this additional space, and has sufficient power to be able to propel an aircraft to which the undercarriage assembly is attached, either alone or in combination with other self-propelled undercarriage assemblies attached to the aircraft.
A thermionic or thermotunneling converter consisting of two electrodes maintained at a desired distance from one another by means of spacers in which the electrodes comprise silicon coated with a hard material, or comprise a ceramic or other refractory material. The spacers are formed by oxidizing one electrode, protecting certain oxidized areas and removing the remainder of the oxidized layer. The protected oxidized areas remain as spacers. These spacers have the effect of maintaining the electrodes at a desired distance without the need for active elements, thus greatly reducing costs.
H01L 37/00 - Dispositifs thermoélectriques sans jonction de matériaux différents; Dispositifs thermomagnétiques, p.ex. utilisant l'effet Nernst-Ettinghausen; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives
H01L 35/30 - DISPOSITIFS À SEMI-CONDUCTEURS; DISPOSITIFS ÉLECTRIQUES À L'ÉTAT SOLIDE NON PRÉVUS AILLEURS - Détails fonctionnant exclusivement par effet Peltier ou effet Seebeck caractérisés par les moyens d'échange de chaleur à la jonction
H01L 21/00 - Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de dispositifs à semi-conducteurs ou de dispositifs à l'état solide, ou bien de leurs parties constitutives
88.
MOS transistor on the basis of quantum interferance effect
A new type of Metal Oxide Semiconductor (MOS) transistor that works on the basis of the Quantum Interference Depression (QID) effect is disclosed. QID occurs inside an n-type semiconductor source-drain electrode of special geometry. Due to QID the Fermi level of said semiconductor increases locally inside the source drain electrode, thereby creating a localized potential energy barrier in the path of electrons moving from source to drain regions. The height of the barrier depends on the degree of QID. QID is in turn regulated by the gate voltage via the charge depletion and hence change in effective dimensions of the special geometry of the semiconductor electrode. A gate voltage modulated potential energy barrier and is thus formed whereby current in said MOS transistor is controlled.
H01L 29/775 - Transistors à effet de champ avec un canal à gaz de porteurs de charge à une dimension, p.ex. FET à fil quantique
H01L 29/66 - Types de dispositifs semi-conducteurs
H01L 49/00 - Dispositifs à l'état solide non couverts par les groupes et et non couverts par une autre sous-classe; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives
B82Y 10/00 - Nanotechnologie pour le traitement, le stockage ou la transmission d’informations, p. ex. calcul quantique ou logique à un électron
H01L 29/12 - Corps semi-conducteurs caractérisés par les matériaux dont ils sont constitués
89.
Transistor on the basis of new quantum interference effect
A quantum interference transistor comprising a thin metal film having a protrusion and a thin insulating layer between the metal film and protrusion. A potential barrier is formed in the region beneath the protrusion as a result of quantum interference caused by the geometry of the film and protrusion. A voltage applied between the electrically isolated protrusion (“island”) and the thin film leads to a change in the electron wave function of the island which in turn leads to a change in the Fermi level of the metal film in the entire region beneath the protrusion. Consequently, a potential barrier may or may not exist depending on the applied voltage, thus providing the present invention with the transistor-like property of switching between open and closed states.
This application describes the software invented to control a dual electric motor system. The dual electric motor system is a Chorus Motor system applied to electric drive for aircraft taxi. The software uses closed-loop control together with several other control laws to operate the motors. Knowledge of the current operating state of the motors, together with knowledge of the commands given to taxi forward, taxi in reverse, or brake in reverse, is used to configure the motors to optimal operating parameters. The software architecture is described along with the pilot interface and many details of software implementation.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G06F 17/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
B64C 25/50 - Atterrisseurs orientablesAmortissement du shimmy
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
A method for reducing the turnaround time of an aircraft having at least one self-propelled undercarriage wheel comprising the step of: moving the aircraft to a required location using at least one self-propelled undercarriage wheel; wherein thrust equipment, (e.g. turbines) are turned on only when needed for takeoff or prior to landing, and are turned off until takeoff or after landing; whereby departing equipment, arriving equipment, and turnaround equipment are not at risk from operating thrust equipment, (e.g. turbines). An apparatus for reducing the turnaround time of an aircraft is disclosed comprising a control unit for facilitating voice communication between a pilot and ground staff. Said control unit may further comprise a control arm for inputting the required direction of movement of said nosewheel; means for transmitting direction information to said self-propelled nosewheel; means for receiving direction information at said self-propelled nosewheel; and means for controlling the direction of said nosewheel. The control unit may also comprise means for turning on and off an APU, parking brakes, and other aircraft features.
G06F 19/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des applications spécifiques (spécialement adaptés à des fonctions spécifiques G06F 17/00;systèmes ou méthodes de traitement de données spécialement adaptés à des fins administratives, commerciales, financières, de gestion, de surveillance ou de prévision G06Q;informatique médicale G16H)
The present invention describes a drive system for an aircraft involving one or more nose wheel motors. Data regarding the nose wheel rotation is used to control the ground travel of the aircraft, to predict potential problems, to provide more precise control over the aircraft, and to improve aircraft safety.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
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