The disclosed apparatus, system and method may include at least the delivery of device power to a single or plurality of workstations, which may include at least one power storage unit suitable to supply power to the plurality of workstations; a plurality of control units each associated with one of the plurality of workstations, wherein each of the control units receives power from the at least one power unit, is communicatively associated with the at least one power unit, and comprises a plurality of power outputs suitable to output power from the power unit to devices associated with the respective workstation; and may include at least one ambient energy collector suitable to provide accumulated power to the at least one power unit.

The disclosed apparatus, system and method may include at least the delivery of device power to a single or plurality of workstations, which may include at least one power storage unit suitable to supply power to the plurality of workstations; a plurality of control units each associated with one of the plurality of workstations, wherein each of the control units receives power from the at least one power unit, is communicatively associated with the at least one power unit, and comprises a plurality of power outputs suitable to output power from the power unit to devices associated with the respective workstation; and may include at least one ambient energy collector suitable to provide accumulated power to the at least one power unit.

An aircraft propelled by at least one turbojet engine on which power can be bled or injected via a high-pressure and/or low-pressure turbine shaft and including at least one gas turbine to provide power transients, having a system for converting and transporting electrical energy wherein each of the high-pressure and/or low-pressure turbine shafts is connected to a first doubly-fed asynchronous machine delivering, a first three-phase AC voltage over an AC distribution grid and a second polyphase AC voltage for a first AC/DC bidirectional converter supplying a DC voltage over a DC distribution grid, at least one second DC/AC bidirectional converter connected to the DC distribution grid converting this DC voltage into a third polyphase AC voltage supplying at least one second doubly-fed asynchronous machine engaged with a rotation shaft of the gas turbine, the second doubly-fed asynchronous machine further delivering a fourth polyphase AC voltage over the AC distribution grid.

An aircraft propelled by at least one turbojet engine on which power can be bled or injected via a high-pressure and/or low-pressure turbine shaft and including at least one gas turbine to provide power transients, having a system for converting and transporting electrical energy wherein each of the high-pressure and/or low-pressure turbine shafts is connected to a first doubly-fed asynchronous machine delivering, a first three-phase AC voltage over an AC distribution grid and a second polyphase AC voltage for a first AC/DC bidirectional converter supplying a DC voltage over a DC distribution grid, at least one second DC/AC bidirectional converter connected to the DC distribution grid converting this DC voltage into a third polyphase AC voltage supplying at least one second doubly-fed asynchronous machine engaged with a rotation shaft of the gas turbine, the second doubly-fed asynchronous machine further delivering a fourth polyphase AC voltage over the AC distribution grid.

An electrical power distribution splitter is designed to receive high wattage electrical power, e.g. 80W-600W, and then to “split” that power into multiple low output wattage electrical power, e.g. 60W/12V or 96W/24V. An IC and circle board in the distribution splitter is used to reduce output power in this manner. The result is the ability to input a single large wattage electrical power supply to a distribution splitter which then outputs multiple lower wattages to a variety of individual different circuits, and, in so doing, a Class 2 UL power supply can be utilized. This is especially important in the signage industry where, for example, one large wattage power electrical supply feeding into the power distribution splitter can supply multiple smaller wattage power to different circuits in one sign.

An electrical power distribution splitter is designed to receive high wattage electrical power, e.g. 80W-600W, and then to “split” that power into multiple low output wattage electrical power, e.g. 60W/12V or 96W/24V. An IC and circle board in the distribution splitter is used to reduce output power in this manner. The result is the ability to input a single large wattage electrical power supply to a distribution splitter which then outputs multiple lower wattages to a variety of individual different circuits, and, in so doing, a Class 2 UL power supply can be utilized. This is especially important in the signage industry where, for example, one large wattage power electrical supply feeding into the power distribution splitter can supply multiple smaller wattage power to different circuits in one sign.

An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

A method of operating an aircraft electrical power distribution system comprises determining a measure of ambient pressure; and setting a target operating voltage in accordance with the measure of ambient pressure. The method further comprises controlling the operating voltage in accordance with the set target operating voltage. The target operating voltage may refer to a distribution voltage of the aircraft. An aircraft electrical power distribution system is also disclosed, comprising: a sensor configured to determine a measure of ambient pressure; a controller configured to set a target operating voltage in accordance with the measure of ambient pressure, and a voltage regulator configured to regulate the operating voltage in accordance with the set target value.