369 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.

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.

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 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.

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.