Provided are systems and methods for supplying electric power to removable storage compartments. The system includes an alignment body and a removable storage compartment. The alignment body is configured to align the storage compartment at a certain position, and includes a first conductive strip configured to be connected to ground, and a second conductive strip having positive voltage. The storage compartment includes at least a first and a second contact means. The first contact means is configured to be in contact with the first conductive strip, and the second contact means is configured to be in contact with the second conductive strip.

According to an embodiment there is provided a multilevel power supply comprising two power sources that share a common node, a switching arrangement, a charge storage device and an output terminal. The two power sources are configured to provide a first potential V.sub.1, a second potential V.sub.2 and a third potential V.sub.3, wherein V.sub.1>V.sub.2>V.sub.3. The switching arrangement is configured to charge the charge storage device between potentials V.sub.1 and V.sub.3 in a first switching state and to connect the charge storage device between potential V.sub.2 and the output in a second switching state.

According to an embodiment there is provided a multilevel power supply comprising two power sources that share a common node, a switching arrangement, a charge storage device and an output terminal. The two power sources are configured to provide a first potential V.sub.1, a second potential V.sub.2 and a third potential V.sub.3, wherein V.sub.1>V.sub.2>V.sub.3. The switching arrangement is configured to charge the charge storage device between potentials V.sub.1 and V.sub.3 in a first switching state and to connect the charge storage device between potential V.sub.2 and the output in a second switching state.

An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

The purpose of the invention is to provide a guideline for, when adding a new power cell to a power network, solving the problem of how to set an operation mode of a power conversion leg. Assuming that a power conversion leg (JRL) of the power router (JR) of a power cell (J) and a power conversion leg (KRL) of the power router (KR) of a power cell (K) are connected to each other and power is transferred from the power cell (J) to the power cell (K) when the utility grid breaks down, the leg operation modes of the leg (JRL) of the power router (JR) and leg (KRL) of the power router (KR) are set as follows: the power conversion leg (JRL) of the power router (JR) is set to a stand-alone mode; and the power conversion leg (KRL) of the power router (KR) is set to a designate power transmission/reception mode when the utility grid does not break down and to a master mode from the designate power transmission/reception mode when the utility grid breaks down.

The purpose of the invention is to provide a guideline for, when adding a new power cell to a power network, solving the problem of how to set an operation mode of a power conversion leg. Assuming that a power conversion leg (JRL) of the power router (JR) of a power cell (J) and a power conversion leg (KRL) of the power router (KR) of a power cell (K) are connected to each other and power is transferred from the power cell (J) to the power cell (K) when the utility grid breaks down, the leg operation modes of the leg (JRL) of the power router (JR) and leg (KRL) of the power router (KR) are set as follows: the power conversion leg (JRL) of the power router (JR) is set to a stand-alone mode; and the power conversion leg (KRL) of the power router (KR) is set to a designate power transmission/reception mode when the utility grid does not break down and to a master mode from the designate power transmission/reception mode when the utility grid breaks down.

A method is disclosed of controlling the operation of a system for providing electrical power to one or more electrical devices, the system comprising an adjustable power source root node and a plurality of adjustable power source remote nodes located remotely from the root node.

A method is disclosed of controlling the operation of a system for providing electrical power to one or more electrical devices, the system comprising an adjustable power source root node and a plurality of adjustable power source remote nodes located remotely from the root node.

An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.