A system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The system includes an energy source of an aircraft. The system further includes a plurality of sensors configured to sense at least an electrical parameter of a load of the plurality of loads. The system further includes an aircraft controller configured to receive electrical parameter of a load of the plurality of loads from the plurality of sensors, compare the electrical parameter to at least a current allocation threshold, detect that the electrical parameter has reached the current allocation threshold, calculate a power reduction to the load, and reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft, wherein the electrical circuit comprises a circuit protection device.

A system comprises a drone having autonomous drive capability and an assist vehicle (AV) for transporting the drone in an assisted drive mode in which the drone is held at, and transported by, the assist vehicle. Control hardware and software are programmed to determine drone travel over a route having a first route section in which the drone travels autonomously and a second route section in which the drone travels in the assisted drive mode.

Disclosed herein is an electrode assembly, comprising in a stacked manner a first anode layer, an anode current collector layer, a second anode layer, a separator layer, a first cathode layer, a cathode current collector layer, and a second cathode layer. In the electrode assembly, the anode current collector layer and/or the cathode current collector layer comprises at least two conductive layers wherein between neighbouring pairs of conductive layers, a respective heat spreading layer is interposed.

A rotor control device includes: a vertical rotor control unit that controls each VTOL rotor based on a first allocation command value; a horizontal rotor control unit that controls each cruise rotor based on a second allocation command value; and an allocation command value calculation unit that sets, as the first allocation command value, a difference between a command value of a yaw moment and the second allocation command value, that sets the magnitude of the second allocation command value to 0 when the command value of the yaw moment is less than a threshold, and that sets the magnitude of the second allocation command value to a value greater than 0 when the command value of the yaw moment is equal to or greater than the threshold.

A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

A system and method for using unrecoverable energy in a battery cell is disclosed in this application. A system includes a battery cell, the battery cell includes an excess amount of cathode or anode that can function as half cells in an emergency. A user, such as a pilot, can command a controller to utilize unrecoverable energy based on battery data presented to the user.

A vertical take-off and landing (“VTOL”) aircraft has at least two flying wings (“FW”) with each FW equipped with multiple transverse-radial propellers or a propulsion system for producing a lift force and thrust force on the stationary or non-stationary FW. This VTOL/FWA is capable of exchanging payloads horizontally, as well as vertically, with a stationary or a moving object. In particular, the VTOL/FWA can “walk” on a building wall to adjust and anchor its position in order to rescue people from a high-rise-building window horizontally.

A system and method for flight control compensation for component degradation is illustrated. The system comprises a first flight component mechanically coupled to the electric aircraft and a second flight component mechanically coupled to the electric aircraft. A sensor is also coupled to both the first flight component and the second flight component, wherein the sensor is configured to detect a performance degradation datum in one of the first flight component and the second flight component and transmit the performance degradation datum to a flight controller. The system also comprises a flight controller communicatively coupled to the sensor, wherein the flight controller is configured to receive the performance degradation datum from the sensor and adjust operation of either the first flight component or the second flight component as a function of the performance degradation datum.

Aspects relate to methods and systems for optimizing battery recharge management for use with an electric vertical take-off and landing aircraft. An exemplary system includes an electric vertical take-off and landing (eVTOL) aircraft comprising at least battery mechanically coupled to the eVTOL aircraft cand configured to power at least an aircraft component of the eVTOL aircraft, wherein the at least a battery comprises a plurality of battery cells, and at least a sensor, configured to measure battery data associated with the at least a battery, and a server remote from the eVTOL and in communication with the at least a sensor, wherein the server is configured to receive the battery data from the at least a sensor, receive mission data associated with a planned flight mission of the eVTOL aircraft, and generate a recharge time as a function of the battery data and the mission data.

An electrical power distribution network of an electric power system of an aircraft is operated such that it sequentially adopts a plurality of different partial load sharing modes in a time variable manner, which provide for partial load sharing across electrical power sources (A, B, C, D) with respect to associated electrical loads (AA, BB, CC, DD), by sequentially switching between a plurality of different partial load sharing configurations of the electrical power distribution network, each partial load sharing configuration being associated to a particular one of the partial load sharing modes.