A modular battery system provides propulsive power to the rotor system of an aircraft. The modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel.

A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.

A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.

Presently disclosed subject matter integrates a method of using thousands of semi-autonomous unmanned aerial vehicles, herein called drones, to deliver vastly superior amounts of fire retardant over substantially larger and variably-shaped drop patterns. Each drone is able to swap its own batteries with freshly charged batteries and each drone is able to refill its container with water or fire retardant. Once launched, a swarm of drones can perform repeated trips from the water/retardant source to the fire without human involvement other than the high-level tasking of where to drop the retardant. Once a general drop destination and drop pattern shape is designated, the swarm can transport retardant to that location, form itself into the desired drop shape, and deploy retardant. The drone body is designed to be modular so different components can be attached with ease and no special training or knowledge required.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

A system and method of converting engines on a turboprop aircraft, including removing an existing engine and associated propeller from an aircraft fuselage, installing an engine mount adapter assembly to the fuselage, and installing a replacement engine to the engine mount adapter assembly, whereby at least some portions of the replacement engine are attached to the engine mount adapter assembly for structural support.

An integrated single stage ac-dc driver for powering LED loads includes a boost converter operating in a Discontinuous Conduction Mode, DCM, comprising a half-bridge, and a Zeta Asymmetrical Half Bridge, ZAHB, integrated with the boost converter such that the boost converter and the ZAHB share the half-bridge to perform power factor control, PFC, with a fixed duty cycle and control an output voltage.

A vehicle is provided that includes a basic structure; and coupled to the basic structure, power sources, a propulsion system and power distribution circuitry. The propulsion system includes a plurality of electric motors configured to power propulsors to generate propulsive forces that cause the vehicle to move. The power distribution circuitry is configured to deliver DC electric power from the power sources to the electric motors, the power distribution circuitry including a plurality of DC-to-DC converter assemblies configured to input the DC electric power from the power sources and deliver voltage-regulated outputs to the electric motors, a DC-to-DC converter assembly operatively coupled to multiple ones of the power sources and multiple ones of the electric motors, and the DC-to-DC converter assembly including a multiple-input and multiple-output (MIMO) transformer with a single transformer core.

Disclosed is a direct current power supply. The direct current power supply includes a voltage output defining a voltage rail and a ground. The direct current power supply includes a holdup capacitor operable to conduct with the voltage output. The direct current power supply includes a redundant power supply connected in series with the holdup capacitor between the voltage rail and the ground of the voltage output to provide the voltage output. The direct current power supply includes a first switch disposed between the holdup capacitor and the redundant power supply operable to create a conductive path between the holdup capacitor and the redundant power supply.