686results about "Electric power distribution" patented technology

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.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a system of an aircraft is disclosed, configured to determine one or more desired commands for the aircraft, retrieve engine information for at least one electric propulsion unit (EPU) of a plurality of EPUs of the aircraft, wherein the engine information includes at least one time-based metric for temperature associated with the at least one EPU, generates control commands based on the received engine information, and controls effectors according to the generated control commands to meet the desired commands of the aircraft.

An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and / or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.

An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and / or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.

A method includes utilizing a learning model, which has been trained to mimic the nominal control outputs of a model predictive control, to generate a nominal control output for a system that is an aircraft system having one or more system constraints. The method also includes, based on the nominal control output, satisfying each of one or more system constraints, implementing the nominal control output; and, based on the nominal control output not satisfying one of the one or more system constraints, utilizing a safety stability filter that includes a control barrier function (CBF) portion and a control Lyapunov function (CLF) portion to modify the nominal control output and obtain a modified control output, and implementing the modified control output in the aircraft system. A system is also disclosed.

Disclosed is a crash handling system for an aircraft, comprising an altitude surveillance system adapted to receive altitude data from an altitude sensor and issue an altitude warning signal when a predetermined altitude condition is fulfilled, a crash detection unit, comprising an acceleration detector and issues a crash detection signal when a predetermined acceleration condition is fulfilled, a control unit operatively coupled to the altitude surveillance system and the crash detection unit to receive respective altitude warning signals and crash detection signals; and an energy storage system isolation means operatively coupled to the control unit to electrically isolate an energy storage system of the aircraft upon reception of an activation signal, wherein the control unit transitions from a disabled operation state to an enabled operation state when the altitude warning signal is received; and to issue the activation signal upon reception of the crash detection signal when in enabled state.

A power system including a power converter system and an electric machine is provided. In one aspect, the power converter system has first and second switching elements. The electric machine includes a first multiphase winding electrically coupled with the first switching elements and a second multiphase winding electrically coupled with the second switching elements. The first and second multiphase windings are arranged and configured to operate electrically opposite in phase with respect to one another. One or more processors control the first switching elements to generate first pulse width modulated (PWM) signals based on received voltage commands to render a first common mode signal and also control the second switching elements to generate second PWM signals based on received voltage commands to render a second common mode signal. The rendered first and second common mode signals have the same or similar waveform with opposite polarity with respect to one another.

An Unmanned Aerial Vehicle power management system is configured to match and manage power demands with combined power output from the power storage devices and dynamic generation via a turbine (combustion) motor, while preventing overcurrent and under voltage loads on the power storage devices. The powerplant and power management system of the present invention are, in one embodiment, directed for use with a vertical take-off and landing (VTOL) UAV having multiple forward propulsion propellers (FP) and multiple vertical lift (VL) propellers.

A electrical power system comprises: an electrical machine operable to output AC; a DC electrical network; a power electronics converter connected between the AC output of the electrical machine and the DC electrical network and including a plurality of transistors and associated diodes connected in parallel with the transistors; and a controller configured to control switching of the transistors of the converter so that, during normal operation of the electrical power system, the converter rectifies the AC output of the electrical machine to supply the DC electrical network with DC electrical power. The controller is further configured, responsive to a determination to the effect there is a fault in the DC electrical network, to control a voltage source, to inject a voltage to bias the diodes of the converter, and to control the switching of the transistors to control a level of current supplied to the faulted DC electrical network.

An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.

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.

This disclosure relates to systems and methods for providing a copilot replacement system (CPRS) that enables dual-pilot or multi-pilot aircraft to be operated by a single onboard pilot. Amongst other things, the CPRS solutions can include components that autonomously execute functions traditionally performed by an onboard copilot and / or can establish connections with one or more copilot ground base stations (GBSs) that enable ground-based copilots to remotely provide assistance with operating the aircraft.

A wing assembly for an aircraft, the wing assembly having a fixed wing and a wing tip device moveably mounted at the end of the fixed wing. A wiring harness extends between the fixed wing and the wing tip device, a length of the wiring harness being encased in a length of protective sleeve. The protective sleeve is pre-shaped, for example pre-molded, to follow a path along a helical curve.

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 electrical power supply system for an aircraft comprising: a string of a plurality of connected smart battery modules, wherein the string is configured to provide a common output voltage; wherein each of the smart battery modules comprises, terminals for outputting an output voltage to a device external to the smart battery module; a battery assembly configured to supply a DC voltage between two poles; a power converter electrically connected to the terminals and the poles, and a controller operably coupled to the semiconductor stage and configured to control the semiconductor stage for regulating the voltage conversation of the DC voltage into the output voltage a control unit operably coupled to the controller of each smart battery module and configured to set an output voltage and / or current setpoint or limit for each controller individually or configured to set an output voltage and / or current setpoint or limit for all controllers collectively.

This disclosure relates to systems and methods for providing a copilot replacement system (CPRS) that enables dual-pilot or multi-pilot aircraft to be operated by a single onboard pilot. Amongst other things, the CPRS solutions can include components that autonomously execute functions traditionally performed by an onboard copilot and / or can establish connections with one or more copilot ground base stations (GBSs) that enable ground-based copilots to remotely provide assistance with operating the aircraft.

A power electronics converter including: an input terminal; first and second DC output terminals; a branch having first and second semiconductor switches connected in series between the first and second DC output terminals, the input terminal connected to a node between the first and second semiconductor switches; a DC link capacitor connected between the first and second DC output terminals; a differential current sensor arranged to measure a differential current signal through the first or second DC terminals; and a controller configured to provide switching signals to each of the first and second switches of the power electronics converter, wherein the controller is further configured to detect a fault in a DC network connected between the first and second DC output terminals upon detection of a peak in an output from the differential current sensor.

The invention relates to a system (10) for de-icing the blades (14) of the propeller (12) of an aircraft, the system comprising an H-bridge inverter device (40); a rotary transformer (22) comprising a main primary winding (26), a primary measurement winding (28), and a secondary circuit (30) delivering a secondary alternating voltage (Vs); a rectifier device (50); a de-icing device (20); a control device (60) configured to control the switching elements of the inverter device in an out-of-phase manner, using the value of the voltage (Vpm) across the terminals of the primary measurement winding, measured during a measurement interval of predetermined duration starting at the instant (t11,t33) when the inverter device switches from a controlled state to a short-circuit state.

Disclosed is a wing assembly for an aircraft. The wing assembly comprises a fixed wing, a wing tip device, a wiring harness and a harness guide. The wing tip device is moveably mounted at a joint at an end of the fixed wing. The wing tip device is moveable about the joint between: (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved relative to the fixed wing such that the span of the wing is reduced. The wiring harness extends between the fixed wing and the wing tip device. The wiring harness comprises a plurality of conductors and is arranged to transmit electrical power and / or data to the wing tip device. The harness guide is located between the fixed wing and the wing tip device. The harness guide comprises a helical channel configured to receive the wiring harness and guide the wiring harness between the fixed wing and the wing tip device.

A propulsion system for an aircraft can include an electric power source and an propulsion assembly having a propulsor. An electric power bus can electrically connect the electric power source to the propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

To provide a power supply system, a moving body and a control method for the power supply system.SOLUTION: In a power supply system 26 mounted on an electrically-driven vertical takeoff / landing aircraft (eVTOL aircraft), a battery controller 94 provides a flight controller 86 with first information representing the upper limit of electric power that a battery can input / output continuously for a first period and second information representing the upper limit of electric power that the battery can input / output continuously for a second period, and a motor controller 98 controls a plurality of VTOL drive devices each having a VTOL electric motor and a plurality of cruise drive devices each having a cruise electric motor.SELECTED DRAWING: Figure 3

Systems, apparatus and methods are provided for securing firmware and mission data in memory of an unmanned aerial vehicle. The unmanned aerial vehicle may include a central body and at least one electric motor. The central body may include a flight controller with a processor, a firmware memory configured to receive and store firmware, and circuit board with a fixed portion and a removable portion with a programming interface connector providing access through a signal connection to a firmware memory operatively connected to the flight controller. The central body may further include a volatile mission memory configured to receive mission data and automatically be erased upon power interruption.

An aircraft propulsion system includes a hybrid-electric power plant for delivering power to an air mover for propelling an aircraft. The hybrid-electric power plant includes a heat engine operatively connected to a first air mover, and an electric motor operatively connected to a second air mover. The second air mover is positioned on a wing of the aircraft outboard from the heat engine. A method for reducing trailing vortices includes powering a first air mover of an aircraft with a heat engine during a take-off stage, a climb stage, a cruise-stage and / or a descent stage. The method includes powering a second air mover of the aircraft with an electrical motor during the take-off stage and / or the climb stage. The method includes freewheeling the second air mover during the cruise stage and / or the descent stage to generate mechanical energy and reduce wing tip vortices.

An aerial vehicle includes a communication apparatus, a receiver that obtains a current position, a flight controller that controls flight and can transmit information on the current position with the communication apparatus, a plurality of drive apparatuses that drive respective different ones of a plurality of propulsive mechanisms, a distributor that distributes supplied electric power to each of the plurality of drive apparatuses, a power supply module that supplies electric power from a battery to the communication apparatus, the receiver, and the flight controller through a first power path and supplies electric power to the distributor through a second power path, and a disconnection apparatus that cuts off supply of electric power from the power supply module to the distributor through the second power path when abnormality occurs.

The application discloses a kind of voltage effective value protection method and system for airborne power distribution system, belong to airborne high-power solid-state power controller technical field.The method of the present application comprises: by the airborne high-power solid-state power controller SSPC installed in airborne power distribution system, the real-time voltage effective value of aircraft AC voltage is determined;When the voltage fault of the airborne power distribution system occurs, the power supply of the airborne power distribution system is switched from aircraft AC power supply to standby power supply by SSPC in a preset period;And the voltage effective value output by the standby power supply is adjusted to be consistent with the real-time voltage effective value.The real-time voltage effective value of aircraft AC voltage is determined by SSPC, which greatly improves the effective value calculation speed and effectively improves the sensitivity of protection action.

A DC power distribution and protection system that comprises a DC power source 2, a power bus 3, 4 connecting the power source 2 with a load R or with a further power source 20, at least one capacitor

An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.

To provide a power supply system, an aircraft, and a power supply system control method that makes the remaining capacity of each battery approximately equal.SOLUTION: A power supply system 26 includes a power converter 36 that converts the power of any one of a plurality of batteries included in a high voltage circuit 32 and supplies it to one or more second loads 38, a switch 34 capable of selectively connecting any one of the plurality of batteries to the power converter, and a controller 70 that compares the remaining capacities SOC of the batteries, and controls the switch so as to connect a battery with the highest remaining capacity and the power converter when the difference between the highest remaining capacity and the lowest remaining capacity is greater than a predetermined threshold.SELECTED DRAWING: Figure 3

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system and in other types of vehicles. In some embodiments, an aircraft is disclosed, the aircraft comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command for the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on at least one dynamically changed torque command.