An electrical power distribution network (306) of an electric power system (300) of an aircraft is operated in at least one normal operation mode such that it provides for load sharing across electrical power sources (A, B, C, D) with respect to electrical loads (AA, BB, CC, DD), wherein the electrical power distribution network (306), in case of an electrical fault, is operated in at least one electrical failure mitigating operation mode, which provides for electric fault isolation, such that a network portion of the electrical power distribution network (306) including the electrical fault is isolated from at least one other network portion of the of the electrical power distribution network.

An electrical power distribution network (306) of an electric power system (300) 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.

An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.

An electrical power distribution system includes a first high side sub-module including a high side converter and a high side energy storage device. The first high side sub-module is electrically coupled to a high side load that requires a high voltage or medium voltage DC, the high voltage DC being higher than the medium voltage DC. The system also includes a first low side sub-module including a low side converter and a low side energy storage device. The first high side sub-module and the first low side sub-module are configured to be inductively coupled. The first high side sub-module and the first low side sub-module form a first module.

System and methods for passive power sharing of parallel sources are provided. Aspects include a first DC power supply including a first generator and a rectifier circuit, a second DC power supply including a second generator and a second rectifier, wherein a first output of the first DC power supply and a second output of the second DC power supply are commonly coupled at a common bus point, a first current sensing device coupled between the first output of the first DC power supply and the common bus point, a first generator controller configured to receive a first current signal from the first current sensing device, analyze the first current signal to determine a first voltage droop value based on the first current signal, and operate the first DC power supply to reduce a first voltage output of the first DC power supply by the first voltage droop value.

An architecture for an aircraft comprises two air-conditioning systems, two converters, each intended to supply one of the air-conditioning systems, and at least one first electric machine which starts up a first main engine of the aircraft. The electrical architecture is configured such that the two converters can together supply the first electric machine. A method of operating the architecture is also provided.

A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

Apparatus and methods for mitigating abrupt release of energy due to a short circuit or other fault external to battery modules in a battery pack. Each battery module includes a plurality of weakened fusible links, which may connect an associated cell to a virtual cell busbar or connect dedicated busbars. After the fault has been cleared and faulted battery modules have been bypassed, the battery pack is ready for reconnection to the electrical network to provide power for the load(s). The battery management includes detection and isolation of a fault followed by execution of an algorithm for reconnection of the battery pack to the power distribution system after burnout of the fusible links. In addition, the respective activation times for reconnecting operative (not faulty) modules in a faulty battery string versus reconnecting other operative battery strings in the battery pack are coordinated.

A system for determining remaining useful energy in an electric aircraft, the system including a computing device where the computing device is configured to measure a internal state datum of a battery as a function of at least a sensor, receive the internal state datum from the at least a sensor, generate a useful energy remaining datum as a function of the internal state datum and a battery model, and display the useful energy remaining datum to a user.

Provided are embodiments for a system for performing input power detection. The system includes a first input for a first power source, a second input for a second power source, and a controller that is operably coupled to the first power source and the second power source. The system also includes a first path connecting a first circuit to the first power supply, wherein the first path comprises a first field effect transistor (FET) that is operated to inhibit leakage current flow to the first circuit, and a second path connecting a second circuit to the second power supply, wherein the second path comprises a second FET that is operated to inhibit leakage current flow to the second circuit. Also provided are embodiments for a method for performing input power detection.