Abstract: A power distribution system is provided for an aircraft on the ground, comprising a first electrical load, operably coupled to the aircraft on the ground and configured to receive at least a first portion of a predetermined maximum input power provided by a power supply; at least one second electrical load, electrically coupleable to the aircraft on the ground and configured to receive at least a second portion of said predetermined maximum input power provided by said power supply, and a controller, adapted to monitor at least one parameter of the power consumed by any one of said first electrical load and said at least one second electrical load, and control the power consumption of at least said first electrical load so that the total power consumption of said first electrical load and said at least one second electrical load does not exceed said predetermined maximum input power; wherein said predetermined maximum input power is provided via a single power line between said power supply and an input port

Abstract: Ground support equipment for powering an aircraft on the ground, the ground support equipment including: a solid state converter configured to power an aircraft on the ground from an airport power source having a pre-determined maximum power, and a battery charging unit configured to charge an external battery from the airport power source. The solid state converter is configured to measure an instantaneous power drawn by the aircraft. The solid state converter is configured to generate, for controlling the battery charging unit, a control signal indicative of a maximum power available for the battery charging unit based on the difference between the pre-determined maximum power of the airport power source and the instantaneous power drawn by the aircraft.

Abstract: A rectifier circuit being arranged for rectifying electrical power, comprising a three phase power input, a magnetic splitter circuit being arranged for receiving the three phase power input and splitting the three phase power into a first three phase system and a second three phase system, the first three phase system having signals lagging signals of the second three phase system, a twelve pulse rectifier with six input terminal to connect the first and the second three phase system, and to generate a rectified electrical power at a power output, a three phase inductance being connected in series with the three phase power input and the magnetic splitter circuit, and a plurality of power factor correction (PFC) capacitors, each comprising first and second terminals, said first terminals being connected to respective input terminals of the twelve pulse rectifier, and the second terminals being connected to at least one common electrical point.

Abstract: A preconditioned air unit for supplying preconditioned air to an aircraft parked on the ground, the preconditioned air unit comprising a main unit with a housing accommodating a flow duct with an air inlet for ambient air and an air outlet for connection to the parked aircraft, a blower connected with the flow duct for generation of an air flow from the air inlet toward the air outlet, and a plurality of compartments, each of which is configured for accommodation of a self-contained cooling module comprising at least one refrigeration system, each of which includes at least one compressor, at least one condenser, at least one expansion valve, and at least one evaporator connected in a flow circuit containing a refrigerant, and wherein each compartment is further configured so that the at least one evaporator interacts with the air flow in the flow duct when the self-contained cooling module is installed in the compartment, and wherein at least one self-contained cooling module is installed in the plurality of

Abstract: A preconditioned air unit for supplying preconditioned air to an aircraft parked on the ground, the preconditioned air unit comprising a housing accommodating a flow duct with an air inlet for ambient air and an air outlet for connection to the parked aircraft, a blower connected with the flow duct for generation of an air flow from the air inlet toward the air outlet, at least one refrigeration system, each of which includes at least one compressor, at least one condenser, at least one expansion valve, and at least one evaporator connected in a flow circuit containing a refrigerant, and wherein the at least one evaporator interacts with the air flow in the flow duct, and at least one variable frequency driver for power supply of at least one of the at least one compressor of the at least one refrigeration system.

Abstract: A rectifier circuit being arranged for rectifying electrical power, comprising a three phase power input, a magnetic splitter circuit being arranged for receiving the three phase power input and splitting the three phase power into a first three phase system and a second three phase system, the first three phase system having signals lagging signals of the second three phase system, a twelve pulse rectifier with six input terminal to connect the first and the second three phase system, and to generate a rectified electrical power at a power output, a three phase inductance being connected in series with the three phase power input and the magnetic splitter circuit, and a plurality of power factor correction (PFC) capacitors, each comprising first and second terminals, said first terminals being connected to respective input terminals of the twelve pulse rectifier, and the second terminals being connected to at least one common electrical point.

Abstract: A preconditioned air unit for supplying preconditioned air to an aircraft parked on the ground, the preconditioned air unit comprising a main unit with a housing accommodating a flow duct with an air inlet for ambient air and an air outlet for connection to the parked aircraft, a blower connected with the flow duct for generation of an air flow from the air inlet toward the air outlet, and a plurality of compartments, each of which is configured for accommodation of a self-contained cooling module comprising at least one refrigeration system, each of which includes at least one compressor, at least one condenser, at least one expansion valve, and at least one evaporator connected in a flow circuit containing a refrigerant, and wherein each compartment is further configured so that the at least one evaporator interacts with the air flow in the flow duct when the self-contained cooling module is installed in the compartment, and wherein at least one self-contained cooling module is installed in the plurality of

Abstract: A preconditioned air unit for supplying preconditioned air to an aircraft parked on the ground, the preconditioned air unit comprising a housing accommodating a flow duct with an air inlet for ambient air and an air outlet for connection to the parked aircraft, a blower connected with the flow duct for generation of an air flow from the air inlet toward the air outlet, at least one refrigeration system, each of which includes at least one compressor, at least one condenser, at least one expansion valve, and at least one evaporator connected in a flow circuit containing a refrigerant, and wherein the at least one evaporator interacts with the air flow in the flow duct, and at least one variable frequency driver for power supply of at least one of the at least one compressor of the at least one refrigeration system.

Abstract: The present invention relates to an aircraft service pit accommodating a GPU for supply of electrical power to an aircraft on the ground. More specifically it relates to a pit with a GPU comprising a housing enclosing a frequency converter for provision of a stabilized multi-phase alternating output voltage to an aircraft through an output cable.

Abstract: The present invention relates to a power converter for supply of electrical power to an aircraft on the ground. More specifically it relates to a power converter comprising a housing enclosing a frequency converter for provision of a stabilized multi-phase alternating output voltage to an aircraft through an output cable that is supplied from a cable drum integrated in the housing and facilitating connection to aircrafts with variable distances between their power sockets and the converter.