An aircraft includes a battery pack, an internal support structure to support the battery pack in the aircraft, a first bracket rigidly coupling the battery pack to the support structure, and a second bracket rotationally coupling the battery pack to the support structure. The first and second brackets may be located on opposite sides of the battery pack. The internal support structure may be located in a wing of the aircraft and the first and second brackets may be aligned in a fore-aft direction of the aircraft. The internal support structure may be located in a nacelle of the aircraft and the first and second brackets may be aligned along a transverse direction of the aircraft. The second bracket may include two hangers to support a mass of the battery pack in tension.

A power distribution controller for a hybrid aircraft is configured to continuously: obtain a state-of-charge (SoC) measurement for a battery of the hybrid aircraft; obtain a fuel level measurement for a secondary energy source of the hybrid aircraft; receive a control input indicating one of a throttle level or an operating mode for one or more motors of the hybrid aircraft; calculate a ratio of energy to source from each of the battery and the secondary energy source in order to operate the one or more motors of the hybrid aircraft based on the control input, the SoC measurement, and the fuel level measurement; and transmit a control signal that causes energy to be apportioned from the battery and the secondary energy source to the one or more motors based on the determined ratio.

The present disclosure provides a structural member for a vehicle. The structural member comprises a plurality of finned spar members interlocked with one another, wherein each of the finned spar members include a main body, a plurality of web members extending from a flange, a circuit board formed on the main body, and a bus bar formed on the main body, wherein a compartment is formed between adjacent web members, each compartment being sized to receive a battery.

An apparatus for modular AC to AC frequency conversion is disclosed. An input AC source is configured to generate an input AC voltage at a first frequency. At least one primary low frequency (LF) conversion stage is configured to generate a DC voltage, and comprises a first pair of metal-oxide-semiconductor field effect transistors (MOSFETs). At least one primary high frequency (HF) conversion stage is configured to generate the DC voltage, and comprises a first pair of high electron mobility transistors (HEMTs). At least one secondary LF conversion stage is configured to receive the DC voltage and generate an output AC voltage at a second frequency, and comprises a second pair of MOSFETs. At least one secondary HF conversion stage is configured to receive the DC voltage and generate the output AC voltage at the second frequency, and comprises a second pair of HEMTs.

A method for managing operation of an aircraft system comprising at least one electrical energy storage set to be supplied with DC current connected to a DC current power supply bus, at least one electrical machine providing AC current by mechanical draw on a drive system connected to a current generation control unit, a bidirectional converter configured to convert a DC voltage into AC voltage, and a control module of the converter, the management method generating a command for the converter from the angular position (θ) of the electrical machine, from the intensity of the electrical current delivered by the electrical machine, and from the output electrical voltage of the converter.

Examples described herein provide a computer-implemented method that includes monitoring a hybrid electric turbine engine of an aircraft, the hybrid electric turbine engine including a first electric machine associated with a high speed spool and a second electric machine associated with a low speed spool. The method further includes receiving an indication of a failed electric machine, the failed electric machine being an electric machine on another hybrid electric turbine engine of the aircraft. The method further includes, responsive to detecting the failed electric machine, distributing power from one or more of the first electric machine or the second electric machine to a spool associated with the failed electric machine.

The invention relates to an electrically and thermally connecting device (3) for batteries and pieces of electrical distribution equipment of an aircraft, comprising a casing (5) containing a plurality of bare under-voltage parts (7), said connecting device (3) being intended to make contact with a portion of the casing (5) and at least one bare under-voltage part (7), said connecting device (3) furthermore comprising: at least one base (11) that is made from a thermally conductive material and that is intended to be fastened to the portion of the casing (5); at least one head (13) that comprises a springback connector and that is intended to make contact with the bare under-voltage parts (7) and the portion of the casing (5); and an intermediate element (15) that is intended to electrically connect the bare parts (7), said element (15) being clamped between a base (11) and a head (13). The invention also relates to a battery and to a piece of electrical distribution equipment for an aircraft.

A system includes a first AC bus configured to supply power from a first generator. A first generator line contactor (GLC) selectively connects the first AC bus to the first generator. A second AC bus is configured to supply power from a second generator. A second GLC selectively connecting the second AC bus to the second generator. An auxiliary generator line contactor (ALC) is connected to selectively supply power to the first and second AC buses from an auxiliary generator. A first bus tie contactor (BTC) electrically connects between the first GLC and the ALC. A second BTC electrically connects between the ALC and the second GLC. A ram air turbine (RAT) automatic deployment controller is operatively connected to automatically deploy a RAT based on the combined status of the first GLC, the second GLC, the ALC, the first BTC, and the second BTC.

Systems for a current limiting circuit are provided. Aspects include a first set of batteries coupled to a battery terminal, a power converter coupled to a power converter terminal, wherein the battery terminal is coupled to the power converter terminal, a first current limiting circuit in series with the first set of batteries, wherein the current limiting circuit comprises a first circuit comprising a first transistor in series with a first diode, a second circuit comprising a second transistor in series with a second diode, a first RL circuit, wherein the first RL circuit, the first circuit, and the second circuit are arranged in parallel, a controller configured to operate the first current limiter in a plurality of modes including a battery discharge mode including the controller operating the first transistor in an off state, and operating the second transistor in a switching state.

Systems and methods of operating for a smart power router for boosting and protection are provided. Aspects include a power router comprising a plurality of terminals, a first DC power supply coupled to the first terminal, a second DC power supply coupled to the second terminal, a first power converter, an interface bi-directional switch coupled between the first terminal and the second terminal, a first bi-directional switch coupled between the first terminal and the third terminal, the first bi-directional switch comprising a first transistor and a second transistor, a first RL circuit, a controller configured to operate the power router in a plurality of modes comprising a first voltage boosting mode, wherein operating the power router in the first voltage boosting mode comprises operating the interface bi-directional switch in an on state, operating the first transistor in an off state, and operating the second transistor in a switching state.