A floor module for a power generation system may comprise: a housing including a flexible top plate; a plurality of generator assemblies disposed within the housing, each generator in the plurality of generator assemblies comprising: a moveable portion disposed adjacent to the flexible top plate, the moveable portion including a shaft extending away from the flexible top late; and a piezoelectric transducer aligned with the shaft, the piezoelectric transducer configured to compress in response to the moveable portion translating toward the piezoelectric transducer from a force on the flexible top plate.

Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R≥2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has a respective index n=(1, . . . , N). The system further comprises, for each respective one of a plurality of the N load channels, a current limiting device (CLD) operable to limit an amount of current flowing from the power channels to a load connectable to the electrical power system via the respective load channel. The electrical power source may comprise one or more batteries.

In an aircraft seat power system, a Smart Power Distribution Connector (PDC) connects a power supply to multiple power outlets. Power to each outlet is monitored and controlled directly by the PDC that is in turn monitored and controlled by the power source. The power source and the PDC share a communication bus through which instructions and responses are communicated. The PDC has the ability to communicate with the outlets by sending instructions and monitoring and acting on the responses from the outlets. The system allows for power management from a supply of limited power. The PDC can provide current limiting, allowing the use of lighter weight and smaller wire and other components.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.

An air conditioning system that is designed to be retroactively added to, and removed from, an existing aircraft, vehicle, boat or similar confined space. The air conditioning system includes a cooler module that is carried into a first compartment to circulate and cool the air. The cooler module contains a condenser, an evaporator and a compressor. A heat exchanger module is mounted into a vented second compartment. The heat exchanger is capable of exchanging heat with the ambient air. The heat exchanger module is connected to the cooler module with tubes that contain a heat exchanger fluid. In order for the tubes to pass through a compartment barrier, fluid couplings are mounted through the barrier. The tubes connect to the fluid couplings on either side of the barrier. A control unit is provided within the pressurized cabin and/or cockpit for controlling the operations of the cooler module.

An electric aircraft includes rotors for providing lift for vertical take-off and landing of the aircraft, proprotors that are tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, a first battery pack for powering a first rotor and a first proprotor, a second battery pack for powering a second rotor and a second proprotor, a first electric power bus electrically connecting the first battery pack to the first rotor and proprotor, and a second electric power bus electrically connecting the second battery pack to the second rotor and proprotor, wherein the second electric power bus is electrically isolated from the first electric power bus.

A turboelectric distributed propulsion based on brushless doubly-fed machines (BDFMs) is provided, which minimizes power conversion, enhances mechanical reliability, and strengthens fault-tolerance capability of a DC-based propulsion system. A turboelectric distributed propulsion (TeDP) architecture using BDFMs for aviation applications, and a designed BDFM, inverter, and controller are provided. Simulations and systems are also provided.

An emergency power management system of a mobility, may include a fuse device connected to a battery and including a first circuit and a second circuit in which a first fuse and a second fuse are respectively provided and are connected in parallel, a pyro switch provided between the first circuit and the second circuit, and configured to establish electric connection with the first circuit in ordinary times and to release electric connection with the first circuit and to establish electric connection with the second circuit in a case of emergency, a determiner configured to determine abnormality of the first fuse based on current applied from the high-voltage battery or voltages at opposite end portions of the first fuse, and a controller configured to operate the pyro switch when abnormality occurs in the first fuse.

The disclosure relates to an electrical power system for providing a stabilised DC voltage to a power bus. Example embodiments include an electrical power system comprising: a DC power bus having first and second DC power bus terminals; an electrical storage unit having first and second terminals, the second terminal connected to the second DC power bus terminal; a DC:DC converter having first and second DC:AC converters and a transformer connected between the first and second DC:AC converters, the first DC:AC converter connected between the first terminal of the electrical storage unit and the first DC power bus terminal; and a controller connected to control a switching operation of one or both of the first and second DC:AC converters.