An autonomous base station for unmanned aerial vehicles (‘UAVs’) is disclosed, which includes a landing surface for a UAV, configured with at least one power transfer bus for supplying power to a power source of a UAV thereon. The base station further includes a networking module and data processing means operably connected to, and configured to control, the power transfer bus and the networking module. The data processing means is operably connected to the UAV through the networking module, and further configured to receive, store and process data from the UAV or another. The base station further includes a power supply operably connected to the or each power transfer bus, the or each networking module and the data processing means. A network of at least two such base stations is also disclosed, for sensing, modelling and monitoring an environment with UAVs.

An abnormality warning system provides an abnormality warning for multiple motor systems that drive a motor used correspondingly to each of multiple rotors included in an electric aircraft. The abnormality warning system includes an abnormality determination unit and a warning level setting unit. The abnormality determination unit determines an abnormal one of the motor systems. The warning level setting unit sets a warning level to warn abnormality, based on at least position information of the rotor in the electric aircraft or the usage of the rotor corresponding to a motor system determined to be abnormal by the abnormality determination unit.

A port for electric vehicles includes an off-loading zone for off-loading one or more passengers from an electric vehicle; a loading zone for loading one or more passengers onto the electric vehicle; and a charging zone for charging the electric vehicle while the electric vehicle is moving from the off-loading zone to the loading zone.

In accordance with at least one aspect of this disclosure, there is provided a system for aircraft power. The system includes a DC/DC converter having a DC input and a DC output and a switching circuit connecting the DC input to the DC output operable to vary voltage at the DC output. A control module is operatively connected to the switching circuit for variable control of the DC output. The control module includes machine readable instructions to cause the control module to receive input indicative of altitude and control the switching circuit to vary voltage of the DC output as a function of environmental conditions such as altitude and humidity. In embodiments the altitude sensor is operatively connected to the controller.

A system for predicting degradation of a battery for use in an electric vehicle id presented. The system includes a computing device communicatively connected to at least a pack monitor unit, wherein the at least a pack monitor unit is configured to detect a battery pack datum of a plurality of battery modules incorporated in a battery pack. The computing device is further configured to receive the battery pack datum as a function of the at least a pack monitor unit, generate, as a function of the battery pack datum, a battery pack model associated with the battery pack of the electric vehicle, and determine a battery degradation prediction as a function of the battery pack datum and the battery pack model.

Provided is a system including: a management unit configured to manage a plurality of battery packs connected in parallel, in which the management unit is configured to control the plurality of battery packs to cause the plurality of battery packs to be discharged alternately so that a discharge rate of each of the plurality of battery packs becomes higher than the discharge rate in a case of discharging all of the plurality of battery packs. The plurality of battery packs include a plurality of left-hand side battery packs and a plurality of right-hand side battery packs, and the management unit is configured to manage the plurality of battery packs to cause at least one of the plurality of battery packs in each of the plurality of left-hand side battery packs and the plurality of right-hand side battery packs to be discharged at a time in order.

A wireless power receiver coil is attached to a landing gear of a drone. The wireless power receiver coil is closer to the drone when the landing gear is in a retracted position and farther away from the drone when the landing gear is in an extended position. A length of the wireless power receiver coil may be the same length when the landing gear is in the retracted position and in the extended position. The wireless power receiver coil may be in a first orientation when the landing gear is in the retracted position and the wireless power receiver coil may be in a different orientation when the landing gear is in the extended position. The wireless power receiver coil may have a first shape when the landing gear is in the retracted position and may have a second shape when the landing gear is in the extended position.

Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid electric propulsion system also includes an energy storage system, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to detect a start condition of the gas turbine engine, control power delivery from the energy storage system to the electric motor based on detecting the start condition, and provide a compressor stall margin using a power-assist provided by the electric motor to the high speed spool over a targeted speed range during starting of the gas turbine engine.

A ducted propulsion assembly for an aircraft includes a duct and a plurality of stators. The distal ends of the stators are coupled to the duct. The ducted propulsion assembly includes a line replaceable centerbody assembly isostatically coupled to the proximal ends of the stators. The line replaceable centerbody assembly includes one or more electric motors driving an output driveshaft. The ducted propulsion assembly also includes a proprotor assembly interchangeably coupled to and rotatable with the output driveshaft of the line replaceable centerbody assembly. The proprotor assembly is rotatable in a rotational plane to generate thrust.