A system may wirelessly supply electrical power to an aircraft cabin component which moves relative to another aircraft cabin component. A first aircraft cabin component may include a solid state electrical power transmitter having an induction loop. The second aircraft cabin component may include a solid state electrical power receiver having a receiving coil. When a power source is connected to the solid state electrical power transmitter, the induction loop creates an oscillating magnetic field which passes through the receiving coil and induces a flow of alternating current through the receiving coil which drives the load.

A hybrid power generation system is presented. The hybrid power generation system includes a generator operable via a prime mover and configured to generate an alternating current (AC) power. The hybrid power generation system further includes a first power converter electrically coupled to the generator, where the first power converter includes a direct current (DC) link. Furthermore, the hybrid power generation system includes a DC power source configured to be coupled to the DC-link. Moreover, the hybrid power generation system also includes a second power converter. Additionally, the hybrid power generation system includes an integration control sub-system operatively coupled to the first power converter and the DC power source. The integration control sub-system includes at least one bypass switch disposed between the DC power source and the DC-link and configured to connect the DC power source to the DC-link via the second power converter or bypass the second power converter.

A hybrid power generation system is presented. The hybrid power generation system includes a generator operable via a prime mover and configured to generate an alternating current (AC) power. The hybrid power generation system further includes a first power converter electrically coupled to the generator, where the first power converter includes a direct current (DC) link. Furthermore, the hybrid power generation system includes a DC power source configured to be coupled to the DC-link. Moreover, the hybrid power generation system also includes a second power converter. Additionally, the hybrid power generation system includes an integration control sub-system operatively coupled to the first power converter and the DC power source. The integration control sub-system includes at least one bypass switch disposed between the DC power source and the DC-link and configured to connect the DC power source to the DC-link via the second power converter or bypass the second power converter.

A computer controls voltage supply for a system that includes a plurality of active cables. The computer determines that a first voltage source included in a first cable has failed to provide a required amount of voltage to the first cable. The computer switches the first cable to a second voltage source included in a second cable. The second voltage source provides voltage to the first cable.

A computer controls voltage supply for a system that includes a plurality of active cables. The computer determines that a first voltage source included in a first cable has failed to provide a required amount of voltage to the first cable. The computer switches the first cable to a second voltage source included in a second cable. The second voltage source provides voltage to the first cable.

A power supply unit includes a housing having at least one input terminal and at least one output terminal, an AC-DC converter which is arranged in the housing and which is connected to the input terminal, a DC-DC converter which is arranged in the housing and which is connected to the output terminal; and a capacitor which forms a structural part of the housing. Furthermore, an on-board power supply network of an aircraft or spacecraft is also described.

An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

A system for supplying electrical energy to at least one electrical load of an aircraft, this system including a main source of electrical energy connected to at least one electrical load through an electrical network, the system including a control device connected to the main source of electrical energy and configured to deliver a variable voltage level on the electrical network based on a predetermined voltage variation law depending on at least one parameter characterizing the altitude of the aircraft and according to the Paschen law with a predefined margin.

A system for supplying electrical energy to at least one electrical load of an aircraft, this system including a main source of electrical energy connected to at least one electrical load through an electrical network, the system including a control device connected to the main source of electrical energy and configured to deliver a variable voltage level on the electrical network based on a predetermined voltage variation law depending on at least one parameter characterizing the altitude of the aircraft and according to the Paschen law with a predefined margin.

A marine power system including multiple of fuel cells, multiple of D C/AC converters and at least one propulsion motor. In the marine power system, each fuel cell of the multiple of fuel cells is connectable to an input of a DC/AC converter of the multiple of DC/AC converters and at least one group of multiple of DC/AC converters is connectable to the at least one propulsion motor to provide variable frequency and amplitude voltage to the at least one propulsion motor. Further, at least one of the multiple of DC/AC converters is connectable to a fixed frequency AC bus to provide voltage with a fixed frequency and amplitude to the fixed frequency AC bus.