Exemplary disclosed embodiments include systems, methods, and devices for a ground maneuvering system for aircraft. The systems, methods, and devices may include a ground maneuvering system including at least one processor in communication with at least one sensor and at least one maneuvering vehicle. The at least one maneuvering vehicle includes one or more processors in communication with one or more sensors. The one or more processors can be configured to sense, using the one or more sensors, an area associated with a plurality of areas, to determine a location within area, or to maneuver the maneuvering vehicle to the location. The maneuvering vehicle may also include a movement system for maneuvering the maneuvering vehicle in or around the plurality of areas, and a platform configured for an aircraft.

The present disclosure provides a ground support equipment for servicing an aircraft on the ground. The ground support equipment comprises a pre-conditioned air. PCA, unit configured to provide pre-conditioned air to an aircraft on the ground. The ground support equipment also comprises a ground power unit. GPU, configured to provide power to the aircraft on the ground. The ground support equipment also comprises an input stage connectable to a power source and configured to provide a DC voltage. The input stage is operatively connected to the PCA unit and the GPU, and the GPU comprises an inverter circuit for transforming the DC voltage to a pre-determined output AC voltage for powering the aircraft.

The present disclosure provides a ground support equipment for servicing an aircraft on the ground. The ground support equipment comprises a pre-conditioned air. PCA, unit configured to provide pre-conditioned air to an aircraft on the ground. The ground support equipment also comprises a ground power unit. GPU, configured to provide power to the aircraft on the ground. The ground support equipment also comprises an input stage connectable to a power source and configured to provide a DC voltage. The input stage is operatively connected to the PCA unit and the GPU, and the GPU comprises an inverter circuit for transforming the DC voltage to a pre-determined output AC voltage for powering the aircraft.

An apparatus may include a substrate. The apparatus may also include a first charger terminal disposed on the substrate, including silver, and configured to apply a first electric potential to a first battery terminal of a battery. The apparatus may additionally include a second charger terminal disposed on the substrate, comprising silver, and configured to apply a second electric potential to a second battery terminal of the battery.

An apparatus may include a substrate. The apparatus may also include a first charger terminal disposed on the substrate, including silver, and configured to apply a first electric potential to a first battery terminal of a battery. The apparatus may additionally include a second charger terminal disposed on the substrate, comprising silver, and configured to apply a second electric potential to a second battery terminal of the battery.

Examples relate to thermal management systems for electric aircraft charging operations. A thermal conditioning system maintains coolant at controlled temperatures using a pressurized reservoir with an air separation system. A controller determines coolant composition by calculating density based on pressure measurements from a bottom-mounted sensor and volume measurements from multiple sources including float switches and flow sensors. The controller processes the measurements to determine glycol-to-water ratio and validates the calculations using conductivity sensing. The system maintains coolant temperature while regulating reservoir pressure through a pressurized headspace. An air separation system removes entrapped gases to maintain thermal conductivity. The system enables continuous monitoring and control of coolant properties during charging operations to maintain optimal battery pack temperatures.

A thermal management system for electric aircraft is disclosed, designed to control the temperature of battery packs during the charging process. The system includes a thermal conditioning system for maintaining coolant at a first temperature, a coolant circulator for transferring the coolant between the thermal conditioning system and the aircraft, and a temperature adjuster for blending coolant flows to achieve a desired combined temperature. A control unit receives battery temperature information and adjusts the temperature adjuster accordingly. The system can operate in various modes, including cooling, heating, or variable temperature modes, based on target temperature parameters. The system is further configured to transition between modes in response to the battery pack's thermal requirements during charging.

A thermal management system for electric aircraft is disclosed, designed to control the temperature of battery packs during the charging process. The system includes a thermal conditioning system for maintaining coolant at a first temperature, a coolant circulator for transferring the coolant between the thermal conditioning system and the aircraft, and a temperature adjuster for blending coolant flows to achieve a desired combined temperature. A control unit receives battery temperature information and adjusts the temperature adjuster accordingly. The system can operate in various modes, including cooling, heating, or variable temperature modes, based on target temperature parameters. The system is further configured to transition between modes in response to the battery pack's thermal requirements during charging.

Examples relate to thermal management systems for electric aircraft charging operations. A thermal conditioning system maintains coolant at controlled temperatures using a pressurized reservoir with an air separation system. A controller determines coolant composition by calculating density based on pressure measurements from a bottom-mounted sensor and volume measurements from multiple sources including float switches and flow sensors. The controller processes the measurements to determine glycol-to-water ratio and validates the calculations using conductivity sensing. The system maintains coolant temperature while regulating reservoir pressure through a pressurized headspace. An air separation system removes entrapped gases to maintain thermal conductivity. The system enables continuous monitoring and control of coolant properties during charging operations to maintain optimal battery pack temperatures.

A system for emergency shutdown of an electric charger using a de-energizing protocol is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a de-energizing protocol as a function of the disruption element.