Abstract: The present invention relates to a polyurethane thermoplastic elastomer, to a composition comprising said polyurethane and a binder, for example bitumen and/or a biobased binder, and also to the use of the composition for the preparation of a waterproofing membrane, a soundproofing membrane, a liquid sealing system, a bituminous mix surfacing, a mastic asphalt surfacing, a primer, a varnish, a mastic, an adhesive or a binder emulsion

Abstract: A method for managing an electrical power supply system (1) of an aircraft, the power supply system (1) comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS1, MPS2), a plurality of contactors (C1-C18) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G1, G2) and/or the main power unit (MPS1, MPS2); and a management module which is capable of controlling the contactors (C1-C18), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS1, MPS2) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G1, G2).

Abstract: A method and a system for supplying electrical energy to an aircraft that is equipped with a plurality of loads to be powered, said power supply system comprising a plurality of power sources and an on-board energy management module, the energy management module being electrically connected to said power sources and to said loads to be powered. The energy management module is arranged so as to control a supply of power to at least one of said loads using at least two different power sources in parallel in the event of increased energy requirements, said load being initially powered by a single power source.

Abstract: A method for managing an electrical power supply system (1) of an aircraft, the power supply system (1) comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS1, MPS2), a plurality of contactors (C1-C18) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G1, G2) and/or the main power unit (MPS1, MPS2); and a management module which is capable of controlling the contactors (C1-C18), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS1, MPS2) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G1, G2).