371 results about "Electric aircraft" patented technology

A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.

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.

A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and / or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting / loading sharing systems that use clutches and gear assemblies to share and / or shift load between the turbines.

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.

This invention relates to electrically-driven propulsors for regional aircraft. These combine fans optimized for quiet regional operations with rotating variable pitch mechanisms contained within the hubs and highly efficient ring electric motors. The ring motors are used to drive annular fans at the inner or outer radius, or a conventional fan at the inner radius. The assembly combines a single fan, fixed or variable pitch, with a row of stators, or multiple counter-rotating fans without stators. Our focus is on propulsors optimized for quiet and efficient regional flights, but many elements apply to long-haul air and several other applications referred to herein.

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.

A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.

Methods and systems for a full-scale vertical takeoff and landing manned or unmanned electric aircraft, having an all-electric, non-hydrocarbon-powered lift and propulsion system, an integrated avionics system for navigation and guidance, and simple joystick and throttle controls to provide the operator with ‘drive by wire’ style direction control. The vehicle employs counter-rotating sets of propellers and lift is provided by multiple pairs of small electric motors driving directly-connected, counter-rotating sets of propellers. Automatic computer monitoring by one or a plurality of programmed redundant digital motor management computer or autopilot controls each motor-controller and motor to produce pitch, bank and elevation, while simultaneously restricting the flight regime that the pilot can command. Sensed multi-axis information and parameter values about vehicle state are used to provide stable vehicle control and to detect when stable vehicle operating limits are about to be exceeded.

An electrically actuated aircraft brake system and method which provides for brake wear measurement, brake running clearance adjustment, ram position-based control and improved construction and operation. Brake wear and running clearance measurement are obtained by analyzing the output of position sensing circuitry. The position sensing circuitry, preferably including a LVDT position sensor, is also used to determine braking load, a brake controller including circuitry for effecting displacement of one or more reciprocating rams to load a brake disk stack by a predetermined amount based on a present displacement value of the position signal obtained from the position sensor. The position sensor preferably includes a LVDT transducer connected between the reciprocating ram and a brake housing, and the motive device preferably includes a servo motor. Also provided is an actuator housing including a guideway for each ram, the guideway and ram having the same polygonal cross-section, whereby the ram nut is guided and restrained from rotation by the guideway as it is translated by a ball screw in threaded engagement with the ram nut for selective movement into and out of forceful engagement with the brake disk stack for applying and releasing braking force on a rotatable wheel. An electric motor is drivingly connected to each ball screw by a first gear integral with the ball screw, a second gear in mesh with the first gear, and a pinion on a rotating drive shaft of the electric motor.

Methods and systems for a full-scale vertical takeoff and landing manned or unmanned electric aircraft, having an all-electric, non-hydrocarbon-powered lift and propulsion system, an integrated avionics system for navigation and guidance, and simple joystick and throttle controls to provide the operator with ‘drive by wire’ style direction control. The vehicle employs counter-rotating sets of propellers and lift is provided by multiple pairs of small electric motors driving directly-connected, counter-rotating sets of propellers. Automatic computer monitoring by one or a plurality of programmed redundant digital motor management computer or autopilot controls each motor-controller and motor to produce pitch, bank and elevation, while simultaneously restricting the flight regime that the pilot can command. Sensed multi-axis information and parameter values about vehicle state are used to provide stable vehicle control and to detect when stable vehicle operating limits are about to be exceeded.

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.

A remote electro-aeroplane is mainly characterized in that the turn rudder surface is jointed to the tail stabilizer by a plastic film on their upper faces with a separation of the elastic foaming material from the plastic film on their lower faces at their joint, wherein two flexible cables or nylon wires are connected to the left and the right racks arranged on the left and the right turn rudder surfaces with their one end respectively and to the servo means within the remote receiving device with their another end, and the restoration mechanisms are provided beneath the left and the right turn rudder surfaces respectively. Based on this structure, the aeroplane has the advantages of easy control with smooth fly in case of making a turn, and is particularly suitable for the primary player.

The invention relates to a virtual mast used for scouting. The virtual mast is structurally composed of a rotor wing type electric aircraft, a small-size photoelectric load and a ground control unit, wherein the rotor wing type electric aircraft comprises an autopilot and a power device; the small-size photoelectric load comprises a CCD camera, a laser distance measuring machine and a thermal infrared imager; the CCD camera, the laser distance measuring machine and the thermal infrared imager adopt a common optical path design, and are packaged in a shell; the shell is connected to the bottom of the rotor wing type electric aircraft; the small-size photoelectric load is used for carrying out photoelectric monitoring on a scouting target or a scouting region; the ground control unit is used for collecting and processing a photoelectric signal obtained by a signal cable. According to the virtual mast used for scouting, the rotor wing type electric aircraft is loaded with a scouting device and a mooring manner is used for solving the energy supplying problem of the rotor wing type electric aircraft, so that the long-time air staying and scouting of the scouting device are realized; the virtual mast used for scouting has a wide application prospect.

An electric aircraft brake control system has a plurality of wheel and brake assemblies, each having a wheel, wheel speed transducer, brake assembly and a brake actuator. Electromechanical control units are uniquely associated with and connected to certain of the wheel and brake assemblies, and each of the electromechanical control units is provided with an antiskid system as an integral portion thereof. Brake data concentrators are provided for receiving data corresponding to various aircraft operational parameters, including brake pedal position, and provide operational signals to the electromechanical control unit as a function thereof. A controller for emergency and park braking is connected to the electromechanical actuator controllers through one of the brake data concentrators to effect emergency braking action on the brake assemblies, such emergency braking action having incident antiskid control. The system allows for a redundency in brake control circuitry and operation, which increases the dispatchability of an associated aircraft by ensuring continued effective operation of the aircraft even in view of a failure of one of the redundant circuits or systems. A reduction in weight is also achieve by reducing lengthy cable runs.

Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric -based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.

An all-electric aircraft is an important development direction for the modern aircraft, and the invention aims at the larger cooling and heating electric charge due to the coexistence of energy resources, an environmental control and a thermal management system and provides an airborne combined cooling and heating system, wherein the system is applicable to the all electric aircraft and utilizes the residual heat generated by a proton exchange membrane fuel cell to drive a lithium bromide absorption-type residual heat air conditioner so as to realize refrigeration and heat supply, thus solving the key problems of restricting the further development of the all-electric aircraft technology such as insufficiently utilized power generation residual heat objectively existing in divided production and supply of the cooling and heating power at home and abroad, excessively high environmental control system energy consumption, excessively large charge of the thermal management system, and the like. Furthermore, the invention also specifically introduces the improvement on the traditional proton exchange membrane fuel cell and the lithium bromide absorption-type residual heat air conditioner, thus leading the two devices to meet the use requirement of the all-electric aircraft.

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 an unmanned aerial vehicle (UAV) flying independent of and in proximity to the electric aircraft. The electric aircraft and methods of operating and recharging same may involve establishing, in-flight, an electrical connection between the aircraft and the UAV flying in proximity to the aircraft and transferring electricity from an electricity source associated with the UAV to the aircraft through the electrical connection.

The embodiment of the present invention relates to a high-energy safe rechargeable lithium-oxygen battery, including an anode and a cathode, wherein, the reactant of the cathode adopts metal lithium, the reactant of the anode adopts oxygen and water, a solid electrolyte membrane is provided between the anode and cathode, and a charge electrode is provided in the anode. The high-energy safe rechargeable lithium-oxygen battery implementing the embodiment of the present invention can resolve low energy density, poor safety and reliability, low cycle life and high cost problems of the traditional lithium ion power cell, all can solve the complicated storage and transport, high cost of barrier diaphragm and catalyst, and high expenditure problems of the hydrogen fuel battery. The high-energy safe rechargeable lithium-oxygen battery can be widely used in various large-capacity high-capacity movable devices and mechanical devices, such as electric bicycles, electric motorcycle cars, electric vehicles, electric boats, electric aircraft, satellite communications machines, rocket launchers and submarines communications power supplies and so on.

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.

A novel electrically driven window shade using an electromagnetic clutch and an override mechanism accessible to a passenger in the aircraft interior, whose shade is driven by an electric motor coupled to a drive sprocket through the electromagnetic clutch. The clutch and electric motor are typically wired in series with one another such that when the motor is energized the clutch is engaged, allowing the window shade to move between an opened and closed position. When the electric motor is de-energized, the clutch is disengaged and the novel override device may be used to manually move the shade between a raised or lowered position.

Battery modules for unmanned and human piloted electric aircraft comprise two planar substrates with electrochemical cells secured between to form load-bearing structural components from which aircraft with greater endurance can be constructed. The cells can be oriented perpendicular or parallel to the substrates, and in the latter case the substrates can include slots that the cells fit into. The cells can be secured to the substrates by adhesives, welding, soldering and the like, as well as by mechanical tensioners. Battery modules can be formed to the shapes of aircraft parts such as wings. Multirotor aircraft are disclosed in which the arms and other parts of the aircraft are constructed from such battery modules.

The present invention relates to the technical field of power supplies of electric vehicles, hybrid electric vehicles and electric aircrafts, especially to a constant temperature control battery pack. The constant temperature control battery pack comprises an inner box and a battery pack. Heat exchange liquid is arranged inside the inner box. A temperature detection device is arranged on an upper cover of the box. The constant temperature control battery pack further comprises a heating apparatus, a cooling apparatus, a first pipeline and a second pipeline. According to the present invention, the automatic constant temperature control system is provided for the relation between the electrochemical characteristics of the battery pack and the temperature changing, wherein the automatic constant temperature control system can be provided for heating the battery pack, cooling the battery pack, and holding the temperature of the battery pack to enable the battery pack to work in an optimal temperature range; the battery pack is prevented from influence due to the environmental temperature changing; the battery pack using is prevented from influence due to the using area; the performance of the battery pack can be provided at maximum at any temperature; the generated heat can be rapidly dissipated when the battery has the short-circuit fault, such that the misfire and the burning can not be generated; the capacity, the efficiency, the service life and the safety of the battery pack are improved; the constant temperature control battery pack provided by the present invention provides significant advances than the battery pack in the prior art.

The invention belongs to the field of aviation electrical systems, and especially relates to an energy feedback type aircraft electrical load simulation method and device, wherein a load simulator and a grid connected inverter are comprised. The simulation device comprises an isolation transformer which is used for providing right voltage or current for an integrated power supply and physically isolating a power grid and the simulation device, the integrated power supply used for providing a voltage source of an electrical load, and an electrical load simulation device which is used for simulating the electrical load. According to the invention, a power electronic converter technology is used to simulate the aircraft electrical load; on the basis that the preliminary laboratory demonstration phase load test of a start system, a distribution system and the like on an aircraft is completed, energy output by an electrical simulation load is recycled; energy is saved; a lot of heat can be avoided; the space of a cooling device is saved; noise pollution is greatly reduced; the cost is saved; and technology and research foundations are provided for developing existing wide body aircrafts and future green environment-friendly all-electric aircrafts.

The invention provides an electric aircraft with a plurality of ducted propellers, telescopic wing and telescopic aircraft body, which belongs to the field of air materials. According to the invention, the wing comprises a plurality of embedded wing sections; during taking off, landing and parking, the tail parts of the wing and the aircraft body can retract; after liftoff, the tail parts of the wing and the aircraft body are unfolded; and the plurality of ducted propellers capable of tilting are symmetrically distributed in front of and behind the wing and on left and right sides of the aircraft body. Through adoption of the layout, the aircraft can vertically take off and land and can also rapidly fly in a flat way; the floor area is reduced during vertical take off and landing and parking; and during flat flight, the plurality of ducted propellers can tilt for 90 degrees so that the flying speed and airborne period are increased. The takeoff and landing process is safe and reliable and the flight attitude is stable. The invention can be made into manned aircrafts and can be also made into unmanned aerial vehicles.

The invention discloses an all-electric aircraft brake system and an aircraft electric brake redundancy control method. Redundancy design is performed for elements, easy to damage, of a brake system, and drive control can simultaneously drive EMAs (electro-mechanical actuators) of four channels to actuate; a core control unit including DSPs (digital signal processors) and CPLDs (complex programmable logic devices) adopts double-redundancy design, and an electric circuit adopts four-redundancy design; power-driven circuits, motors, force sensors and Hall position sensors of a channel A and a channel B are divided into one group, and a 1#DSP and a 1#CPLD are taken as primary control units; power-driven circuits, motors and force sensors of a channel C and a channel D are divided into the other group, and a 2#DSP and a 2#CPLD are taken as secondary control units; the primary and secondary control units simultaneously drive the EMAs of the four channels to actuate. Double redundancy of the control units and four redundancy of the drive units are realized; the 1#DSP and the 2#DSP communicate with each other through an SPI (serial peripheral interface).

To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.

A method of in-flight operational assessment for an electric aircraft comprising detecting by a sensor an electrical parameter of an energy source. The method further includes receiving by a controller the electrical parameter from the sensor and determining a power-production capability of the energy source, using the electrical parameter. The method further includes calculating, by the controller, a projected power-consumption need of the electric aircraft and comparing the determined power-production capability of the energy source to the projected power-consumption need. The method further includes displaying, by a graphical user interface, an element of the power-production capability of the energy source.