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703results about "Energy efficient operational measures" patented technology
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Package delivery by means of an automated multi-copter uas/uav dispatched from a conventional delivery vehicle
ActiveUS20160200438A1Substantial fuel savingReduce operating costsRemote controlled aircraftVehicular energy storageDocking stationDelivery vehicle
Methods and associated systems for autonomous package delivery utilize a UAS / UAV, an infrared positioning senor, and a docking station integrated with a package delivery vehicle. The UAS / UAV accepts a package for delivery from the docking station on the delivery vehicle and uploads the delivery destination. The UAS / UAV autonomously launches from its docked position on the delivery vehicle. The UAS / UAV autonomously flies to the delivery destination by means of GPS navigation. The UAS / UAV is guided in final delivery by means of a human supervised live video feed from the UAS / UAV. The UAS / UAV is assisted in the descent and delivery of the parcel by precision sensors and if necessary by means of remote human control. The UAS / UAV autonomously returns to the delivery vehicle by means of GPS navigation and precision sensors. The UAS / UAV autonomously docks with the delivery vehicle for recharging and preparation for the next delivery sequence.
Owner:WORKHORSE GRP INC
Powered nose aircraft wheel system
InactiveUS7445178B2Improves arrival and departure efficiency and productivityEasy to useLiquid handling installationsEnergy efficient operational measuresNoseAuxiliary power unit
A powered nose aircraft wheel system (130) for an aircraft (12) includes landing gear (104) that extends from the aircraft (12). A wheel axel (136) is coupled to the landing gear (104). A wheel (134) is coupled to the wheel axel (136). A wheel motor (106) is coupled to the wheel axel (136) and the wheel (134). A controller (120) is coupled to the wheel motor (106) and rotates the wheel (134). A method of taxiing an aircraft (12) includes permitting the wheel (134) of the aircraft (12) to freely spin during the landing of the aircraft (12). Power is transferred from an auxiliary power unit (73) of the aircraft (12) to the wheel motor (106). The wheel (134) is rotated via the wheel motor (106). The aircraft (12) is steered and the speed of the wheel (134) is controlled via one or more controllers selected from an onboard controller (18, 118, 120) and an offboard controller (45, 58, 59).
Owner:THE BOEING CO
Automated aircraft towing vehicle system
InactiveUS6305484B1Extension of timeReduce idle timeEnergy efficient operational measuresAutomatic initiationsJet engineCoupling
An automated aircraft towing vehicle system for use with aircraft is provided. When coupled to an aircraft the towing tractor vehicle facilitates the movement of the aircraft without the requirement for use of the aircraft's jet engines. The towing vehicle system comprises a towing tractor vehicle having remotely controllable steering, braking, and acceleration. The remote system controller is located in the aircraft being towed such that the pilot of the aircraft being towed is capable of controlling the starting, stopping and steering of the towing tractor vehicle. The towing tractor vehicle further includes a remotely controllable de-coupling means. When the aircraft is towed to the desired location, the decoupling of the aircraft from the towing tractor vehicle is controllable by the remote system controller.
Owner:LEBLANC EDWARD L
Landing gear method and apparatus for braking and maneuvering
ActiveUS20050224642A1Improve braking effectIncrease flexibilityEnergy efficient operational measuresElectric devicesEngineeringElectric power
Aircraft landing gear comprised of a wheel hub motor / generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The wheel hub motor / generator can provide motive force to the wheel when electrical power is applied, which may be applied prior to touch-down thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway thus greatly reducing the sliding friction wear of said tire. After touchdown the wheel hub motor / generator may be used as a generator thus applying a regenerative braking force and / or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and / or stored for later use in providing a source for motive power to the aircraft wheels for the purpose of taxiing and ground maneuvers of said aircraft.
Owner:DELOS AEROSPACE
Integrated multifunctional powered wheel system for aircraft
ActiveUS20090218440A1Improve braking effectWeight increaseEnergy efficient operational measuresWheel arrangementsDrive wheelFlight vehicle
Owner:AIRBUS SAS +1
Geared wheel motor design
InactiveUS7469858B2High levelLower levelEnergy efficient operational measuresToothed gearingsGear wheelGear system
The present invention is a compound planetary gear system which has a moveable sun gear and a lockable sun gear to change the gear ratio between a high gear ratio and a pseudo 1:1 slipping ratio. The system makes use of a ratchet and pawl mechanism to provide a safety backup for when the lockable sun gear is locked. The invention may be used to move the aircraft from a stationary position, for taxiing, and for pre-rotating the wheels prior to landing.
Owner:BOREALIS TECH LTD
Rapidly convertible hybrid aircraft and manufacturing method
InactiveUS20110036939A1Easy to convertAvoid many safety and emissionInfluencers by generating vorticesConvertible aircraftsCruise speedControl system
A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature will also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.
Owner:EASTER WILLIAM CRAIG
System and method for integrating air and ground transportation of passengers and cargo
ActiveUS7344109B1Alleviate challengeMitigating issueEnergy efficient operational measuresSeating arrangementsJet aeroplaneAviation
A system and method for integrating air and ground transportation of passengers and cargo. The system comprises a plurality of universal passenger containers. The system further comprises a plurality of universal cargo containers. An airplane is provided with a hollow fuselage adapted to be loaded with a plurality of passenger and / or cargo containers. A flatbed trailer can be provided to carry a passenger or a cargo container. A tractor vehicle can be provided to transport flatbed trailers between airplanes, locations within the airport, and points of origin and destination outside the airport complex. A system can be provided to load and unload passenger and cargo containers into and out of airplanes at the airport. A system is provided comprised of an airport complex including take-off and landing runways, taxiways, airplane staging areas, apparatus for detection of weapons in passenger and cargo containers, and air terminals with arrival and departure gates and baggage handling conveyors. A system is also provided comprised of remote air terminals at strategic locations a distance from the airport complex.
Owner:REZAI SOHEIL
Aircraft kinetic landing energy conversion system
ActiveUS20080258014A1Increase braking powerAvoid heatArresting gearRailway vehiclesElectric potential energyElectric generator
A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor / generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor / generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator. Additionally, the generator is employable as a motor, receiving energy from the storage system for traction power to the associated aircraft wheel. An induction grid or a surface mounted conductive layer mounted into or onto a runway is employed for transferring energy to and from the motor / generator.
Owner:THE BOEING CO
Landing gear method and apparatus for braking and maneuvering
InactiveUS7226018B2Reduce wearImprove stabilityElectric devicesEnergy efficient operational measuresElectric generatorAirplane
Aircraft landing gear comprised of a wheel hub motor / generator disks stack, includes alternating rotor and stator disks mounted with respect to the wheel support and wheel. The invention can provide motive force to the wheel when electrical power is applied, e.g. prior to touch-down, thus decreasing the difference in relative velocities of the tire radial velocity with that of the relative velocity of the runway and reducing the sliding friction wear of the tire. After touchdown the wheel hub motor / generator may be used as a generator thus applying a regenerative braking force and / or a motorized braking action to the wheel. The energy generated upon landing maybe dissipated through a resistor and / or stored for later use in providing a source for motive power to the aircraft wheels for taxiing and ground maneuvers of the aircraft. Methods and apparatuses for nose gear steering and ABS braking using the disclosed invention are described.
Owner:DELOS AEROSPACE
Nosewheel control apparatus
An apparatus for driving a taxiing aircraft is disclosed, comprising, in an aircraft, two self-propelled nosewheels, each having an electric motor; equipment for flight; dual-function controlling means for controlling said equipment for flight and said nosewheels, said dual-function controlling means being disposed in the cockpit of said aircraft; sensing means; and switching means, —wherein said switching means are operable to switch the function of said dual-function controlling means between controlling said equipment for flight and controlling said nosewheels. Said dual function controlling means may control speed and / or steering of the aircraft. Second controlling means may be provided, and may be disposed externally to the aircraft.
Owner:BOREALIS TECH LTD
Motor for driving aircraft, located adjacent to undercarriage wheel
ActiveUS20090114765A1Energy efficient operational measuresAlighting gearAirplaneAutomotive engineering
Owner:BOREALIS TECH LTD
Drive unit for aircraft running gear wheels
InactiveUS20140225421A1Extended service lifeEnergy efficient operational measuresAircraft stabilisationGear wheelSprocket
A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), is characterized in that the drive unit (16) comprises at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6).
Owner:L 3 COMM MAGNET MOTOR
Aircraft electric brake and generator therefor
InactiveUS20070284939A1Braking element arrangementsEnergy efficient operational measuresElectricityEngineering
An aircraft braking system includes a brake disk stack (22) that has at least one brake rotor (26) rotatable with an aircraft wheel (16) and at least one brake stator (24), at least one actuator (36) movable in response to a braking command to compress the brake disk stack (22) and slow the wheel (16), at least one actuator motor (32) operably connected to the at least one actuator (36) for moving the at least one actuator (36), a generator (40, 82, 100) having a generator rotor (42) and a generator stator (44), the generator (40, 82, 100) being operably connectable to the aircraft wheel (16) such that said generator rotor (42) rotates when the wheel (16) rotates, and a controller (50) electrically connected to the generator (40, 82, 100) and the at least one actuator motor (32). Also a method of generating electrical power from an aircraft wheel (16).
Owner:HONEYWELL INT INC
Method of calculating approach trajectory for aircraft
InactiveUS20080262665A1Minimize environmentalMaximum performanceAnalogue computers for vehiclesEnergy efficient operational measuresFlight vehicleAirplane
The general field of the invention relates to a method of calculating a so-called continuous descent approach procedure for aircraft. The method comprises calculation steps making it possible to determine a minimum distance making it possible to attain the runway by using the highest possible descent angles allowed by the performance of the aircraft, a maximum distance making it possible to attain the runway by using the lowest possible descent angles allowed by the performance of the aircraft, a step of comparing the minimum and maximum distances with a reference distance, the continuous descent approach procedure being possible if this reference distance is less than the maximum distance and greater than the minimum distance. The method also envisages replacing certain indeterminate points of the flight plan by points arising from the minimum and maximum distance calculations.
Owner:THALES SA
Aircraft landing gear
ActiveUS20120153075A1Large caliberSignificant torque magnifying gear ratioEnergy efficient operational measuresAlighting gearGear wheelFlight vehicle
An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.
Owner:AIRBUS OPERATIONS LTD
Systems and Methods for Tracking Moving Objects
Systems and methods for tracking moving objects in accordance with embodiments of the invention are disclosed. In one embodiment of the invention, an object tracking system comprises a processor, a communications interface, and a memory configured to store an object tracking application. The object tracking application configures the processor to receive a sequence of images; estimate and subtract background pixel values from pixels in a sequence of images; compute sets of summed intensity values for different per frame pixel offsets from a sequence of images; identify summed intensity values from a set of summed intensity values exceeding a threshold; cluster identified summed intensity values exceeding the threshold corresponding to single moving objects; and identify a location of at least one moving object in an image based on at least one summed intensity value cluster.
Owner:CALIFORNIA INST OF TECH
Methods and systems for tailored allocation of arrivals
ActiveUS20100241345A1Analogue computers for vehiclesEnergy efficient operational measuresData sourceWeather station
A tailored arrival allocation system (TAAS) for determining a descent profile for an aircraft is described. TAAS includes a gateway operable for establishing communications between TAAS and aircraft, and for establishing communications between TAAS and at least one of a source of weather data, an air traffic services facility, and an airlines operations center. A processing device communicatively coupled to the gateway calculates a descent profile based on data received from a plurality of an air traffic services coordination function, an airline operations center function, data from the aircraft, and data received from a weather station that allows the aircraft to meet the required time at one or more metering fixes during the descent. Output interfaces provide data relating to the calculated descent profile to the processing device. The gateway communicates with a flight management computer for the aircraft to incorporate the calculated descent profile onto the flight management computer.
Owner:THE BOEING CO
Aircraft undercarriage with motorization and transmission
ActiveUS20100147995A1More protective effectGreat freedomEnergy efficient operational measuresWheel arrangementsFlight vehicleAirplane
The aircraft includes an undercarriage having an upper portion, at least one wheel for running on the ground, and a shock absorber connecting the wheel to the upper portion. The aircraft also includes a motor for driving the wheel, the motor being rigidly fastened to the upper portion.
Owner:AIRBUS +1
Roadway for decelerating and/or accelerating a vehicle including an aircraft
InactiveUS6969213B2Minimizing braking systemMinimizing tireIn situ pavingsArresting gearTransfer mechanismAirplane
A roadway upon which a vehicle travels is provided in which the vehicle is decelerated. The roadway includes: a movable surface extending in a direction of the vehicle's travel; and a potential energy storage mechanism operatively connected to the movable surface for converting a kinetic energy of the vehicle into potential energy upon movement of the movable surface thereby slowing the vehicle. Also provided is a roadway upon which a wheeled vehicle travels in which the vehicle is accelerated. The roadway includes: a movable surface extending in a direction of the vehicle's travel; and a potential energy transfer mechanism operatively connected to the movable surface for transferring a stored potential energy associated with the movable surface into kinetic energy upon movement of the movable surface thereby propelling the vehicle.
Owner:OMNITEK PARTNERS LLC
Method of adapting a segment of an aircraft trajectory with constant ground gradient segment according to at least one performance criterion
ActiveUS20160085239A1Optimization pathEasy to useEnergy efficient operational measuresDigital data processing detailsState variableEngineering
A method for adapting an aircraft constant-gradient descent segment comprises: an acquisition step in which state variables characterizing the aircraft, environment variables characterizing the environment thereof and path variables characterizing the predicted path thereof at one of the initial and final points of the segment are acquired; a calculation step whereby a limit ground gradient for at least one performance criterion is calculated from the state variables, environment variables and path variables; a validity verification step checking the validity of the path initially predicted against the most restrictive limit ground gradient; and when the path initially predicted is not valid: a feasibility verification step checking the feasibility of a command to modify at least one state variable; if feasibility is verified, a prediction of executing the command; otherwise, a prediction of modifying one of the initial and final points of the segment with respect to constraints of the flight plan.
Owner:THALES SA
Aircraft handler
An aircraft handler (10) for use with an undercarriage of an aircraft, the handler being self-propelled and comprising a generally “U” shaped body (11) having arms (12 &13) linked by a bridge (14) at one end thereof with a pair of drive wheels (16 &17) located one at the free end of each arm, with at least one wheel(15) located adjacent the bridge(14). A pair of clamping jaws (51) are mounted on the body (11) between the drive wheels (16 &17) and the bridge (14)and jaws (51) have a lower profile than the arms (12 &17). The drive wheel (16 &17) are driven by DC electric motors powered by batteries stored in the arms.
Owner:DOUGLAS EQUIPMENT +1
Landing gear method and apparatus for braking and maneuvering
InactiveUS20060038068A1Reduce wearImprove stabilityEnergy efficient operational measuresElectric devicesElectric powerElectric generator
Owner:DELOS AEROSPACE
Turnaround methods
ActiveUS7891609B2Reduce turnaround timeImprove efficiencyAnalogue computers for vehiclesEnergy efficient operational measuresVoice communicationFlight vehicle
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.
Owner:BOREALIS TECH LTD
Rapidly convertible hybrid aircraft and manufacturing method
InactiveUS8371520B2Easy to convertAvoid many safety and emissionInfluencers by generating vorticesConvertible aircraftsOperational systemSynchronous control
A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.
Owner:EASTER WILLIAM CRAIG
Method and system for recovering the energy state of an aircraft during descent
ActiveUS20160063867A1Easy to followImprove recovery authorityAnalogue computers for vehiclesEnergy efficient operational measuresAirplaneTime constrained
A method and system is provided for the recovery of an aircraft energy upset in a time-constrained descent. The system includes a computational unit to assess a number of adjustments involving a combination of speed changes, aerodynamic brake deployment and track miles adjustments that alter the energy dissipation profile whilst allowing the aircraft to maintain a pre-determined time-of-arrival over an incoming waypoint along the original descent path.
Owner:UNIVERSITY OF MALTA
Modular aircraft ground support cart
InactiveUS7461516B2Air-treating devicesAc-dc conversion without reversalSupporting systemFlight vehicle
A modular aircraft support system is disclosed. In one embodiment, the modular system includes a mobile cart and an air conditioning system configured to provide conditioned air to an aircraft. The embodiment also includes a modular power converter for converting input power to a desired output power, which can be input to a supported aircraft. The cart is configured to receive a plurality of different interchangeable power converters, such as a 115 VAC, 400 Hz power converter or a 270 VDC power converter. In some embodiments, a variety of other components are also coupled to the mobile cart, including a local generator and engine. The generator may supply power to the air conditioning system and to the converter.
Owner:HOBARD BROS CO
Motor controller
ActiveUS20120018574A1Low costLower Level RequirementsEnergy efficient operational measuresDigital data processing detailsCOLA (software architecture)Software architecture
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.
Owner:BOREALIS TECH LTD
Planetary gear system and gear reducer
ActiveUS20130095974A1Reduce restlessnessReduce power lossEnergy efficient operational measuresEngine fuctionsReduction driveGear system
Owner:KAWASAKI HEAVY IND LTD
Motor and gearing system for aircraft wheel
ActiveUS20130062466A1High torqueMinimal spaceRailway vehiclesMotor depositionSystems designDrive wheel
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.
Owner:BOREALIS TECH LTD
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