A power conversion system incorporated in a flight vehicle includes a power converter having a semiconductor element stored therein. An energy storage is disposed above the power converter in the vertical direction, the energy storage storing a solid or liquid energy source containing a neutron attenuating material. The power converter is provided with a movable mechanism that moves to shift in position according to a tilt of the flight vehicle. The movable mechanism includes slider rails and a slider movable unit.

An electric power system of a moving object includes a first polyphase rotating electric machine, a second polyphase rotating electric machine, a first polyphase terminal unit, a second polyphase terminal unit, a first polyphase cable, and a second polyphase cable. Each of the first and second polyphase terminal units includes a first phase terminal, a second phase terminal, and a third phase terminal. The first distance is smaller than the second distance that is smaller than the third distance. The fourth distance is smaller than the fifth distance that is smaller than the sixth distance.

An electric power system of a moving object includes a first polyphase rotating electric machine, a second polyphase rotating electric machine, a first polyphase terminal unit, a second polyphase terminal unit, a first polyphase cable, and a second polyphase cable. Each of the first and second polyphase terminal units includes a first phase terminal, a second phase terminal, and a third phase terminal. The first distance is smaller than the second distance that is smaller than the third distance. The fourth distance is smaller than the fifth distance that is smaller than the sixth distance.

A power supply system includes: a first connection circuit including a first connector and a second connector that are capable of connecting a first power supply circuit and a second power supply circuit to each other; a first positive side contactor provided in the first power supply circuit; a second positive side contactor provided in the second power supply circuit; a first control device for controlling the first connector and the first positive side contactor; and a second control device for controlling the second connector and the second positive side contactor.

When the supply of DC power from a first power generation device to a first power supply circuit is cut off, a control device disconnects the first power generation device from the first power supply circuit and a connection circuit using a contactor device, thereafter connects the first power supply circuit and a second power supply circuit to each other, causes electric power to be supplied from a second power generation device to between the first power generation device and the contactor device via a precharge circuit, and determines whether or not a short circuit has occurred between the first power generation device and the contactor device.

When the supply of electric power from a first power generation device to a first power supply circuit is cut off, a control device causes electric power to be supplied from a second power generation device to between the first power generation device and a contactor device via a precharge circuit and the contactor device, determines whether or not a short circuit has occurred between the first power generation device and the contactor device, and thereafter connects the first power supply circuit and a second power supply circuit to each other.

The present disclosure relates to a flight system and a failure responding method therefor. A flight system includes: a plurality of fuse boxes configured to control application of a voltage to at least one propulsion device; and an interlock control apparatus configured to control interlock lines between fuse boxes connected using the interlock lines among the fuse boxes to synchronize and control opening of the fuse boxes connected using the interlock lines.

A hybrid electric propulsion system includes a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine. A method for operating the hybrid electric propulsion system includes operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; reducing a fuel flow to a combustion section of the turbomachine in response to receiving the data indicative of the failure condition; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.

A hybrid airship (drone, UAV) capable of significantly extended flight times can use one of two technologies, or both together. The first technology uses a combination of a lifting gas (such as hydrogen or helium) in a central volume or balloon and multirotor technology for lift and maneuvering. The second technology equips the airship with an on board generator to charge the batteries during flight for extended flight operations, with an internal combustion engine (such as a high power to weight ratio gas turbine engine) driving the generator. A quadcopter or other multicopter configuration is desirable.

A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, and a turbine section with a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. An electric energy storage component is electrically connected to the electric motor, and electrically connected to at least one aircraft taxiing system. The gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations.