A system for battery management for electric aircraft batteries includes an energy storage system configured to provide energy to the electric aircraft via a power supply connection, the energy storage system including: a battery pack, a sensor configured to detect a condition parameter of the battery pack and generate a battery datum based on the condition parameter, a pack monitoring unit (PMU) configured to receive the battery datum, and a high voltage disconnect configured to terminate the power supply connection between the battery pack and the electric aircraft; a high voltage bus electrically connected to the high voltage disconnect; a primary functional display configured to display information based on battery datum; and a first controller area network (CAN) bus and a second CAN bus communicatively connected to the PMU, the high voltage bus, and the primary functional display.

A hybrid multirotor propulsion system for an aircraft includes a plurality of propulsion units, each propulsion unit having a propeller, an electromotor and a peripheral differential gearbox; a plurality of driving elements, each of which is coupled to a respective one of the plurality of propulsion units; a mechanical power source; a main distributor gearbox; at least one electric machine; and a power management unit. The power management unit is configured according to a predetermined operating mode, which causes the mechanical power source to output first and second mechanical power components; and distributing the first mechanical power component to provide each driving element with a direct mechanical propeller power; and causes the electric machine to convert the second mechanical power component into electric power, part of which provides each electromotor with an electric propeller power. The direct mechanical propeller power causes each electromotor to convert the electric propeller power into an indirect mechanical propeller power, outputted to the peripheral differential gearbox; and causes the peripheral differential gearbox of each propulsion unit to aggregate the direct mechanical propeller power and the indirect mechanical propeller power to a total mechanical propeller power which drives the propeller of each propulsion unit.

A method of controlling an electric propulsion system of an aircraft. The propulsion system comprising an electric motor configured to drive a variable pitch propulsor. The method comprises determining a commanded thrust setting; determining one or more flight parameters; determining either a corresponding rotor governor speed and motor torque set-point, or a corresponding motor speed and rotor pitch angle set point, which provides the commanded thrust setting at the determined flight parameter having a maximum propulsion system efficiency; and controlling the rotor governor and electric motor in accordance with the determined respective set-points.

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 electrical power system includes: an electrical machine to output AC; DC electrical network; power electronics converter connected between the AC output of the electrical machine and the DC electrical network and having a phase leg having first and second branches respectively having first and second bi-directional MOSFETs; and controller controlling switching of the first and second bi-directional MOSFETs of each phase leg of the converter so that current is commutated between the phase leg first and second branches rectifying the AC input to DC to supply the DC electrical network with DC electrical power. The controller is responsive to a determination to the effect that there is a fault in the DC electrical network, to control the switching of each phase leg first and second bi-directional MOSFETs to switch the converter into a crow-bar configuration in which electrical machine current does not flow to the DC network.

A support for a busbar including two parts each having two surfaces substantially planar and perpendicular to one another and arranged to form, together with the two surfaces of the other part from the two parts, a through-cavity or a passage, a base including a hole or a fastener, and, a shape complementary to a shape of the other of the two parts, the shape being arranged to form, together with the shape of the other of the two parts, an attachment between the two parts. Advantageously, it is possible to obtain a support for a busbar, the support being robust, reliable, and inexpensive and able to be mounted in an easy and rapid manner.

A propulsive electric motor set for aircraft includes an electrical energy source and an electric motor provided with a drive shaft on which is mounted a propeller. The electric motor includes a first set of windings linked to the electrical energy source to provide a rotational drive function for the drive shaft. The electric motor further includes a second set of windings which, when the drive shaft is driven in rotation by an electric powering of the first set of windings, provides an electric generation function configured to supply non-propulsive loads of the aircraft. Thus, the non-propulsive loads of the aircraft can be electrically powered without any overload compromising the aerodynamics of the aircraft.

An electrical supply holding circuit includes a primary stage and a secondary stage. The primary stage includes a voltage connector connected to a supply network, and a primary winding connected to a voltage converter. The secondary stage includes a secondary winding facing the primary winding, the primary and secondary windings forming two coupled inductances, and a voltage controller to which the secondary winding is connected, the voltage controller being connected to a load and controlling a voltage across the terminals of the load. Directions of the currents flowing through the primary and secondary windings are the reverse of one another, and the voltage converter stops the supply to the primary winding when the supply voltage is less than a threshold voltage and resumes the supply to the primary winding when the supply voltage is greater than a threshold voltage.

Method and system for managing hydrogen fuel in hydrogen fuel cell-powered aircraft is disclosed. The method identifies unused hydrogen fuel in a fuel tank of the aircraft. Determines an amount of the unused hydrogen fuel in the fuel tank of the aircraft. Transfers the amount of the unused hydrogen fuel from the fuel tank of the aircraft into a hydrogen fuel cell of the aircraft and converts the amount of the unused hydrogen fuel into electricity via the hydrogen fuel cell of the aircraft.

Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.