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3739results about "Power plant type" patented technology
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Power line sentry charging
A rechargeable battery energized unmanned aerial vehicle having surveillance capability and an ability to clandestinely collect propulsion and other energy needs from a conveniently located and possibly enemy owned energy transmission line. Energy collection is by way of a parked vehicle engagement with the transmission line in a current flow dependent, magnetic field determined, rather than shunt, voltage dependent, conductor coupling. Surveillance during both a parked or docked condition and during aerial vehicle movement is contemplated.
Owner:US SEC THE AIR FORCE THE
Parallel Hybrid-Electric Propulsion Systems for Unmanned Aircraft
An unmanned air vehicle is provided, which includes an airframe and a parallel hybrid-electric propulsion system mounted on the airframe. The parallel hybrid-electric propulsion system includes an internal combustion engine and an electric motor. A hybrid controller is configured to control both the internal combustion engine and the electric motor. A propeller is connected to a mechanical link. The mechanical link couples the internal combustion engine and the electric motor to the propeller to drive the propeller. An alternate unmanned air vehicle includes a second propeller driven by the electric motor. In this alternate unmanned air vehicle, the internal combustion engine is decoupled from the electric motor.
Owner:GOVERNMENT OF THE UNITED STATES AS REPRESENTD BY THE SEC OF THE AIR FORCE
Reconfigurable battery-operated vehicle system
InactiveUS20140061376A1Reduce weightStable structureUnmanned surface vesselsRemote controlled aircraftReconfigurable antennaComputer module
A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.
Owner:AEROVIRONMENT INC
Long range hybrid electric airplane
InactiveUS20080184906A1Long range of flightLow system efficiencyPropellersAircraft stabilisationOperational costsCombustion
An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.
Owner:KEJHA JOSEPH B
Aircraft Capable of Vertical Take-Off
ActiveUS20160207625A1Good hover characteristicIncrease cruising speedAircraft stabilisationUnmanned aerial vehiclesJet aeroplaneQuadcopter
The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive.
Owner:AIRBUS DEFENCE & SPACE
Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
ActiveUS20150266571A1Reduce resistanceReduce drag in all flight modesPropellersEfficient propulsion technologiesLevel flightFlight vehicle
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.
Owner:JOBY AERO INC
Electrical architecture for a rotary wing aircraft with a hybrid power plant
ActiveUS20120025032A1Reduce loadSave energy consumptionAircraft power plant componentsPropulsion by batteries/cellsOn boardEngineering
A hybrid power plant (5) for an aircraft (1) comprises at least: a hybrid drive system (37) having a main on-board electricity network (16) and an auxiliary electricity network (34); and a selective adaptation interface (38) arranged to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks (16; 34). At least one engine and a hybrid drive auxiliary electrical machine (7, 31) are mechanically connected to a transmission (8); said machine (7) being electrically connected to at least one auxiliary electrical bus (36) in parallel with at least one auxiliary device for delivering electric charge.
Owner:EUROCOPTER
Systems and methods for UAV battery power backup
ActiveUS20160039300A1Avoid data lossIncrease the itineraryPower installationsCharging stationsElectrical batteryStandby power
Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV) while providing continuous power to at least one system on the UAV. The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and / or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV. The UAV and / or the energy provision station may have a backup energy source to provide continuous power to the UAV.
Owner:SZ DJI TECH CO LTD
Micro hybrid generator system drone
ActiveUS20160137304A1Power plant cooling arrangmentsElectric power distributionElectrical batteryAC power
An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.
Owner:ISTARI
Hybrid jet/electric vtol aircraft
ActiveUS20130062455A1Improve efficiencyLess thrust capacityAircraft navigation controlEfficient propulsion technologiesJet aeroplaneElectricity
A fixed-wing VTOL aircraft features an array of electric lift fans distributed over the surface of the aircraft. A generator is (selectively) coupled to the gas turbine engine of the aircraft. During VTOL operation of the aircraft, the engine drives the generator to generate electricity to power the lifting fans. Power to the lifting fans is reduced as the aircraft gains forward speed and is increasingly supported by the wings.
Owner:SONIC BLUE AEROSPACE
Lift Propulsion and Stabilizing System and Procedure For Vertical Take-Off and Landing Aircraft
InactiveUS20130251525A1Inhibition effectLow costElectric power distributionPropellersLeading edgeTurbine
Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and / or rotary and / or c) the engine flow directed downwards and / or d) pressure air jets injected on leading edges control fins, and / or e) water jets and / or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and / or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft.
Owner:SAIZ MANUEL M
Vehicle control system and methods
InactiveUS20130261914A1Hybrid vehiclesInstruments for road network navigationMaximum torqueElectricity
A control system that makes adjustments, such as limiting the maximum speed or maximum torque in a vehicle, is provided. These adjustments can be based on knowledge about the vehicle and trip, and on the estimated energy remaining. The control system is applicable to a wide range of vehicles, including ground, air, water, and sea vehicles, as well as vehicles powered by battery, electricity, compressed natural gas, or even liquid fuel propulsion systems. The control system may be used to adjust vehicle operation in route to assure the vehicle reaches a destination and to inform or counteract a human vehicle operator. Control system can also be used in racing applications to calculate the fastest-possible race speed and drive torque for a given race length; or alternatively, in endurance racing or delivery applications to optimize the vehicle speed and / or drive torque for a given race length or route.
Owner:W MORRISON CONSULTING GRP
Distributed propulsion system and method of control
This invention relates to a method and apparatus for controlling power distribution in an electrical aircraft propulsive system having at least one electrical propulsion unit which includes a plurality of rotatable blades, each blade having an adjustable pitch; a pitch adjusting mechanism for adjusting the pitch of the blades; at least one electrical machine electrically connected to the electrical propulsion unit so as to provide electrical power when in use; and, a control system, the method comprising the steps of: determining the required propulsion; determining whether the propulsive units are delivering the required propulsion; and, adjusting the pitch angle of the blades of at least one propulsive unit so as to increase or decrease the propulsion provided by that propulsive unit.
Owner:ROLLS ROYCE PLC
Aerodynamic integration of a payload container with a vertical take-off and landing aircraft
ActiveUS20100012769A1Compact spacePower plant fuel tanksUnmanned aerial vehiclesFlight vehicleModularity
A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention.
Owner:SIKORSKY AIRCRAFT CORP
Unmanned Aircraft and Operation Method for the Same
InactiveUS20150285165A1Low powerIncrease powerPower installationsUnmanned aerial vehiclesJet aeroplaneExternal combustion engine
Owner:AIRBUS DEFENCE & SPACE
Aircraft propulsion system
InactiveUS20060254255A1Highly compatible with environmentSynchronous generatorsMagnetic circuitCombustion chamberLiquid hydrogen
To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment. An electrical generator is coupled to a turbofan engine, the electrical generator is driven by output power of the turbofan engine to output electric power, and an electromagnetic driving fan is driven by the electric power. On the other hand, after bringing each of coils in the electromagnetic driving fan to a superconductive state, liquid hydrogen is introduced to a heat exchanger, collects the energy of exhaust as heat, is then vaporized, and thereafter supplied to a combustor and to a fuel cell. Further, the electromagnetic driving fan is changed in its rotational phase by a rotating mechanism portion, is made movable in a width direction of a wing and a wing chord direction by a slide mechanism portion, and can be stored inside or outside the wing by a storage mechanism portion.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY +1
Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades
ActiveUS9694911B2Reduce drag in all flight modesPropellersEfficient propulsion technologiesJet aeroplaneVertical take off and landing
An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.
Owner:JOBY AERO INC
Purebred and hybrid electric VTOL tilt rotor aircraft
Electrically powered Vertical Takeoff and Landing (VTOL) aircraft are presented. Contemplated VTOL aircraft can include one or more electrical energy stores capable of delivering electrical power to one or more electric motors disposed within one or more rotor housings, where the motors can drive the rotors. The VTOL aircraft can also include one or more sustainer energy / power sources (e.g., batteries, engines, generators, fuel-cells, semi-cells, etc.) capable of driving the motors should the energy stores fail or deplete. Various VTOL configurations are presented including an all-battery purebred design, a light hybrid design, and a heavy hybrid design. The contemplated configurations address safety, noise, and outwash concerns to allow such designs to operate in built-up areas while retaining competitive performance relative to existing aircraft.
Owner:OVERAIR INC
Vertical take-off and landing vehicle with increased cruise efficiency
Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.
Owner:NASA
Hybrid Propulsion Vertical Take-Off and Landing Aircraft
A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.
Owner:AURORA FLIGHT SCI CORP
Long Range Electric Aircraft and Method of Operating Same
ActiveUS20140339371A1Eliminate range anxietyReduce energy densityAircraft power plant componentsRemote controlled aircraftElectric aircraftAirplane
Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft.
Owner:AMPAIRE INC
System, apparatus and method for long endurance vertical takeoff and landing vehicle
InactiveUS20130206921A1High aspect ratioAircraft stabilisationUnmanned aerial vehiclesWing configurationVertical take off and landing
A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.
Owner:AURORA FLIGHT SCI CORP
Tri-Rotor Aircraft Capable of Vertical Takeoff and Landing and Transitioning to Forward Flight
ActiveUS20160200436A1Increase rangeImprove enduranceAircraft stabilisationUnmanned aerial vehiclesJet aeroplanePropeller
Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.
Owner:NASA
Energy Cell Regenerative System For Electrically Powered Aircraft
ActiveUS20170057650A1Stable electrical outputEfficient energy conversionMechanical apparatusPower installationsElectrical batteryElectric aircraft
A system for providing regenerative power for an aircraft to sustain flight includes multiple energy cells disposed within the aircraft, the energy cells being configured to supply power to a propulsion motor and electronics of the aircraft, a fan generator harnessing propeller blast created by an aircraft propeller and converting kinetic energy of the propeller blast into electrical energy, a charger receiving the electrical energy generated by the fan generator and using the electrical energy to recharge one or more of the energy cells, and a power transfer switch selectively connecting one of the energy cells to the propulsion motor and electronics of the aircraft, such that the energy cells are rotated one at a time to power the propulsion motor and electronics. During recharging, the one or more of the energy cells are disconnected by the power transfer switch.
Owner:ELECTRONAIR
Aircraft propulsion system
InactiveUS7555893B2Highly compatible with environmentMagnetic circuitAircraft power plant componentsSpacecraft propulsionFuel cells
Owner:JAPAN AEROSPACE EXPLORATION AGENCY +1
Solid oxide regenerative fuel cell for airplane power generation and storage
InactiveUS6854688B2Reactant parameters controlFuel cells groupingUnitized regenerative fuel cellElectrolysis
A Solid Oxide Regenerative Fuel Cell (SORFC) or a Solid Oxide Fuel Cell (SOFC) is incorporated into an electrically powered airplane to provide either regenerative or primary electrical energy. The SORFC, the SOFC, or any other suitable fuel cell within an airplane may also be used to heat payload or equipment within the airplane. The SORFC is not only capable of generating electrical energy from fuel and a suitable oxidizer, but can also generate fuel through electrolysis of oxidized fuel. Thus, the SORFC system powering an airplane can obtain oxygen oxidant reactant from the air and avoid the complexity, weight, volume, and cost associated with oxygen storage.
Owner:BLOOM ENERGY CORP
Hybrid Drive And Energy System For Aircraft
InactiveUS20130147204A1Reduce noiseReducing sound exposureHybrid vehiclesEfficient propulsion technologiesDynamoEnergy system
A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.
Owner:AIRBUS HELICOPTERS DEUT GMBH +1
Rocket or ballistic launch rotary wing vehicle
Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.
Owner:BLUE BEAR SYST RES
Aircraft capable of vertical takeoff
ActiveUS20160236774A1Good hovering characteristicHigh travel flight speedUnmanned aerial vehiclesPower plant typeJet aeroplanePropeller
An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.
Owner:AIRBUS DEFENCE & SPACE
Aerial vehicles and methods of use
An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.
Owner:UNIVERSITY OF KANSAS
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