1267results about "Power plant type" patented technology

An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.

A vertical take-off or landing (VTOL) aircraft is disclosed that includes a propulsion system comprising at least four tilting propulsion assemblies and two or more lifting propulsion assemblies. Actuation of the tilting mechanisms can convert the aircraft from a hover configuration, in which all propellers produce thrust generally upward to counteract the aircraft's weight, to a forward flight configuration, in which the four or more tilting propellers produce thrust generally in a forward direction parallel to the fuselage to overcome drag in cruise flight and the lifting propellers produce no thrust or a level of thrust generally less than that required in the hover configuration.

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

Embodiments relate generally to systems and VTOL aerial vehicles. An example central server system comprises: at least one central server system processor; and central server system memory storing central server system program instructions accessible by the at least one central server system processor, and configured to cause the at least one central server system processor to: receive vehicle registration data associated with a manned VTOL aerial vehicle; and determine that the vehicle registration data is associated with a manned VTOL aerial vehicle that is authorized to communicate with the central server system. Some embodiments include VTOL aerial vehicles in communication or communicable with a central server system.

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

A hybrid powerplant is provided for an aircraft. This hybrid powerplant includes a housing, an electric machine, a machine fluid circuit, a heat engine and a geartrain. The housing includes a machine containment zone and an engine compartment outside of the machine containment zone. The electric machine is arranged within the machine containment zone. The machine fluid circuit services the electric machine. The machine fluid circuit extends in the machine containment zone and is arranged outside of the engine compartment. The heat engine is arranged within the engine compartment. The geartrain is operatively connected to the electric machine and the heat engine.

A system and a method for controlling a propulsor assembly of an electric aircraft. The system may include an electric motor, wherein the electric motor may include a rotor and a stator, a propulsor driven by the electric motor configured to propel an electric aircraft. The propulsor may include a propeller. The propeller may include a blade. The system may include a cyclic control assembly configured to deflect the blade. The cyclic control assembly may include an actuator and a push rod mechanically connected to the actuator and the propulsor. The system may include a flight controller. The flight controller may be configured to receive sensor datum from at least a sensor communicatively connected to the electric aircraft, generate a deflection command as a function of the sensor datum and actuate the cyclic control assembly as a function of the deflection command.

A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.

A battery system is mounted on an eVTOL. The battery system includes a battery, an auxiliary battery, and a charge-related equipment. The battery supplies power to a drive target including a rotor blade of the eVTOL. The auxiliary battery charges the battery. The charge-related equipment controls charging from the auxiliary battery to the battery. The charge-related equipment has a function of electrically connecting or disconnecting the auxiliary battery and the battery. It is possible to reduce bias in ion concentration caused by discharge during a flight by temporarily charging the battery from the auxiliary battery and changing the direction of the current so as to reduce the temporary deterioration. Thus, the safety of the flight can be enhanced.

An electrostatic thruster for producing thrust by charging gas and / or liquid particles using a high voltage potential, the electrostatic thruster comprises at least two thruster cells, wherein each thruster cell comprises: - at least one emitter, - at least one collector, wherein the at least one collector is spaced from the at least one emitter by a thruster cell gap, wherein the electrostatic thruster further comprises a power source electrically connected to the at least one emitter and the at least one collector of each thruster cell, wherein the power source is configured to apply a voltage between the at least one emitter and the at least one collector of each thruster cell, wherein the at least two thruster cells are positioned in parallel to form a thruster cell array, wherein the thruster cell array further comprises an intermediate electrode powered by a current source that generates a substantially constant current.

A hybrid propulsion update system includes a controller in signal communication with a replaceable battery. The controller includes a tuning parameters storage unit configured to store at least one tuning parameter corresponding to the replaceable battery. The controller is configured to execute at least one optimization algorithm that utilizes the tuning parameters to control operation of the hybrid electric aircraft according to a first performance. The tuning parameters storage unit is configured to receive at least one updated tuning parameter from a controller updating device. The controller executes the at least one optimization algorithm that utilizes the at least one updated tuning parameter such that the hybrid electric aircraft operates according to a second performance that improves upon the first performance.

An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.

An electric aerial vehicle includes a center unit, a plurality of rotor units coupled to the center unit via one or more connecting arms, one or more battery assemblies, and a plurality of electrical circuitry components. The center unit includes a compartment. Each of the rotor units includes at least a propeller, a motor for driving the propeller, and an electrical speed-controller (ESC) module electrically coupled to the motor. The one or more battery assemblies provide electrical power to at least corresponding ones of the motors and corresponding ones of the ESC modules. The electrical circuitry components include a central control circuitry and at least one subsystem. Each of the battery assemblies extends horizontally along the one or more connecting arms towards a proximal end of a corresponding one of the one or more rotor units, wherein the proximal end is coupled to the center unit.

The present disclosure relates to a reconfigurable battery system and method of operating the same. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to determine a state of charge of a battery, determine a closed circuit voltage of the battery, determine a value of a parameter based on a ratio of the state of charge and the closed circuit voltage, and control a switch coupled to the battery based on the value of the parameter, the controlling of the switch to either cause the battery to be coupled to a battery string or cause the battery to be disconnected from the battery string.

The invention discloses a battery tank structure of an unmanned aerial vehicle (UAV) and relates to the technologies of battery tank structures of UAVs. The battery tank structure can solve the problem of large space occupation of a battery tank of an existing UAV. A main battery tank body is of a rectangular structure, is placed in the middle of a UAV body, the side wall of the tank body is provided with a plurality of positioning holes, and a battery locking mechanism is fixed by the positioning holes and fixedly connected to a battery after the battery is inserted into the battery tank; byfixing the battery locking mechanism to the positioning holes in different positions, the position of the battery in the whole UAV body is adjusted, and correspondingly the position of the gravity center of the UAV body is adjusted. The structure is mainly used for UAVs.

Examples provide electric propulsion systems; such a system comprising: a. a nacelle comprising an aerodynamic annular housing defining an internal annular volume and defining an inner duct, b. at least one fan stage comprising a fan bearing a plurality of aerodynamic surfaces / blades to generate thrust mounted within a fan shroud, and c. a powertrain comprising at least one electric motor to drive the fan shroud and at least one electrical power source to power the electric motor; and d, wherein i. the fan shroud is disposed within the inner duct, ii. at least part of the powertrain is disposed within the internal annular volume, iii. the at least one electric motor is disposed within the central hub and iv. the hub-to-tip ratio is between 0.1 and 0.4, preferably, between 0.2 and 0.3.

A motor includes a rotor and a stator including a stator core including a core back and teeth, and a coil including a conductor including a wound portion wound around the teeth and an end extending from the wound portion. An axial position of the end is within a range from an end on one side to an end on the other side in an axial direction of the wound portion.

An assembly for a propulsion system of an aircraft includes a gearbox module, an electric motor assembly, a first accessory load assembly, and a propulsor. The gearbox module includes a gear assembly and an output shaft. The gear assembly includes a main gear and a plurality of offset gears. The electric motor assembly includes an electric motor. The electric motor includes a rotor. The rotor is mounted to a first offset gear of the plurality of offset gears. The rotor is configured for rotation about a rotational axis to drive rotation of the gear assembly and the output shaft. The first accessory load assembly includes at least one first accessory load. The at least one first accessory load is mounted to a second offset gear of the plurality of offset gears. The propulsor is coupled to the output shaft.

The invention discloses a performance simulation calculation method for an aviation hybrid electric power system. The method comprises the following steps: firstly, constructing a sub-component calculation model covering an aerodynamic thermal component, a power generation subsystem, a power conversion and transmission subsystem, a battery subsystem, a motor and an aerodynamic system; establishing a reverse logic calculation framework driven by a load side demand, and realizing hierarchical reverse parameter solution from a load end to a power source end; and establishing a power balance equation at a bus end, carrying out iterative solution by adopting a Newton-Rafson algorithm, and realizing dynamic distribution and coordination control of multi-source energy in combination with an energy constraint module. According to the method, through a reverse solution and bus end balance strategy, the simulation calculation efficiency and convergence of the complex aviation hybrid electric power system are remarkably improved, and meanwhile, the adaptability and expandability of the model to different topological architectures and task profiles are enhanced; and an efficient and high-credibility calculation tool is provided for design, performance evaluation and energy management strategy optimization of the hybrid electric propulsion system of the aircraft.

The present invention relates to a vertical take-off and landing (VTOL) aircraft featuring a central fuselage and at least two power units. Each power unit is connected to at least two separate lifting rotors via transmission lines, ensuring that each power unit is linked to at least two rotors diametrically opposed relative to the centre of gravity of the aircraft. The lifting rotors might be driven by power transmission lines of hydrostatic type. The power units on either side might be housed in separate pods which might be incorporated into the main fuselage or arranged as separate pods. These separate pods might also function as floats / pontoons for the aircraft to land, take-off and manoeuvre on water.

A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a voltage regulator configured to convert voltage between a battery cell voltage and a bus voltage.

An aerial vehicle connected to or integrated with a work device, including a power source to generate power, a rotor to generate lift used for flight by rotating a propeller, and a power transmission to transmit driving power to the work device.

Embodiments provide an aircraft with one or more tilting fan assemblies that are configured to tilt between a forward flight position and a vertical lift position. The aircraft may also include a plurality of lift fan assemblies for vertical movement. The tilting fan assemblies may be coupled to the fuselage or wings of the aircraft via one or more tilting mechanisms. A control system coupled to the aircraft may control the one or more tilting mechanisms to move the tilting fan assemblies between the forward flight position and the vertical lift position. The tilting fan assemblies may be coupled to one or more support structures that are coupled the fuselage or wings of the aircraft.

Embodiments provide an aircraft with one or more tilting fan assemblies that are configured to tilt between a forward flight position and a vertical lift position. The aircraft may also include a plurality of lift fan assemblies for vertical movement. The tilting fan assemblies may be coupled to the fuselage or wings of the aircraft via one or more tilting mechanisms. A control system coupled to the aircraft may control the one or more tilting mechanisms to move the tilting fan assemblies between the forward flight position and the vertical lift position. The tilting fan assemblies may be coupled to one or more support structures that are coupled the fuselage or wings of the aircraft.

A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

An aircraft equipped with a multi-fan propulsion system for controlling flight orientation transitions is provided. In one example aspect, an aircraft includes a fuselage and a pair of wings. The aircraft includes a propulsion system having a first propulsor and a second propulsor each mounted to the fuselage. The first propulsor has a fan positioned primarily above and the second propulsor has a fan positioned primarily below the pair of wings. The aircraft also includes a computing system having one or more processors configured to cause, in response to a demand to change an orientation of the aircraft for a flight orientation transition, the fans of the first and second propulsors to produce different amounts of thrust with respect to one another so that the aircraft performs the flight orientation transition. The thrust differential causes the aircraft to transition between orientations.

The invention belongs to the field of wing-in-ground-effect ship system design, and discloses a wing-in-ground-effect ship adopting a hybrid power energy management and vector control cooperative system, which comprises a ship body, a hybrid energy system, an electric propulsion system, a data acquisition system and a flight control module. According to the invention, a plurality of groups of tilting ducted fans are adopted in front of and behind the wings, and the stable and efficient propulsion requirements of all working conditions of take-off, ground-effect flight, non-ground-effect flight, turning and short-distance landing of the wing-in-ground-effect ship are met through vector control and adjustment; an eddy current system and a power battery are adopted to achieve multi-mode switching work such as a pure electric mode, an eddy current mode, a mixed electric mode and a charging mode through a power grid, and the power requirement of the wing-in-ground-effect ship under all working conditions is met. The control strategy and cooperation scheme of the hybrid power energy management module and the ducted fan vector control module have the capability of remarkably improving the energy efficiency and the flight performance of the wing-in-ground-effect ship, and the problems that a traditional wing-in-ground-effect ship is low in energy utilization rate and poor in maneuverability are solved.

The invention provides a power-lift ultra-short-distance take-off and landing fixed-wing aircraft which is characterized in that on the basis of a traditional fixed-wing aircraft, a traditional fuel engine is adopted as a main power scheme, and electric propulsion power-lift devices which only work for a short time in the take-off and landing stages of the aircraft are arranged below wings. In this way, the maturity and high structural efficiency of the structure and system of a traditional fixed-wing aircraft are inherited, meanwhile, power lift augmentation is achieved by arranging a plurality of electrically-driven propellers which only work in the take-off and landing stages of the aircraft for a short time below the wings, and the lift coefficient of the aircraft in the take-off and landing stages is greatly increased; high reliability and low structural weight are kept, and meanwhile ultra-short-distance take-off and landing are achieved.

VTOL aircraft that takeoff and land as a multirotor and cruises as airplane. The aircraft comprises two major parts: First; winged carrier frame comprises wings, engines, propellers and landing gears. Second; tilting fuselage comprises cockpit, cabin and tail. Winged carrier frame is basically X / H frame multirotor that its thruster carrying arms are wing shaped. Aircraft vertically takeoff as multirotor after gaining safe altitude and forward airspeed then changes its flying axis that wings and thrust direction parallel to horizon. Lift generated by wings and thrust generated by thrusters that aircraft has basic airplane flying characteristics. Fuselage tilted to keep payload parallel to the horizon. Speed reduced, winged carrier frame and fuselage returned to multirotor for landing. It is easier to rotate fuselage than thrusters or wings. It is better to adjust thrust levels than vectoring to reduce the moving parts and aerodynamic effects.