Abstract: The present invention discloses an electric drive train comprising:—a rotor or propeller shaft (R),—an electric motor assembly (GEMD) configured to drive the rotor or propeller shaft (R), the electric motor assembly (GEMD) comprising a plurality of stacked electric motor elements (Ee1, Ee2, Ee3, Ee4),—a power branch of a first topology feeding a stacked electric motor element (Ee1) of the electric motor assembly (GEMD), said power branch (b1) comprising a RESS and an electric generator (G) supplying a power signal to said power branch (b1),—a power branch (b3) of a second topology dissimilar from the first topology, said power branch feeding another stacked electric motor element of the electric motor assembly (GEMD), said power branch (b3) comprising: # an electric generator (G) supplying a power signal to said power branch, a matrix converter (Mc3) feeding the another stacked electric motor element (Ee3), # or, an electric generator supplying Direct Current to said power branch and a motor controller feedin

Abstract: The present invention discloses an electric drive train comprising: a rotor or propeller shaft (R), an electric motor assembly (GEMD) configured to drive the rotor or propeller shaft (R), the electric motor assembly (GEMD) comprising a plurality of stacked electric motor elements (Ee1, Ee2, Ee3, Ee4), a power branch of a first topology feeding a stacked electric motor element (Ee1) of the electric motor assembly (GEMD), said power branch (b1) comprising a RESS and an electric generator (G) supplying a power signal to said power branch (b1), a power branch (b3) of a second topology dissimilar from the first topology, said power branch feeding another stacked electric motor element of the electric motor assembly (GEMD), said power branch (b3) comprising: # an electric generator (G) supplying a power signal to said power branch, a matrix converter (Mc3) feeding the another stacked electric motor element (Ee3), # or, an electric generator supplying Direct Current to said power branch and a motor controller feedin

Abstract: A fault tolerant optical apparatus resilient to ballistic impact damages, capable of enabling distributed processing and networking and using the spectrophotometric transmission properties of polymer film.

Abstract: A fault tolerant, optically or electrically managed, EMP resilient electromagnetic distributed direct drive powertrain applied to provide lift and/or propulsion and/or attitude control to an aircraft. The electromagnetic distributed direct drive being network based, capable of autonomous operations and decisions such as pilot input interpreting mode, load distribution, fault management, self-healing operations, electrical and mechanical health monitoring, as well as electrical and mechanical fault prediction.

Abstract: A fault tolerant optical apparatus resilient to ballistic impact damages, capable of enabling distributed processing and networking and using the spectrophotometric transmission properties of polymer film.

Abstract: Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: ·Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting

Abstract: A fault tolerant, optically or electrically managed, EMP resilient electromagnetic distributed direct drive powertrain applied to provide lift and/or propulsion and/or attitude control to an aircraft. The electromagnetic distributed direct drive being network based, capable of autonomous operations and decisions such as pilot input interpreting mode, load distribution, fault management, self-healing operations, electrical and mechanical health monitoring, as well as electrical and mechanical fault prediction.

Abstract: Apparatus for measuring the local electrical resistance of a surface, the apparatus comprising: a DC voltage source for applying a bias voltage (Vpol) to the sample (E) for characterizing; a measurement circuit (CM) capable of being connected to a conductive probe suitable for coming into contact with a surface (SE) of said sample in order to generate a signal (S) representative of a contact resistance between said conductive probe and said surface of the sample; and a control device (CMD) for controlling said measurement circuit; the apparatus being characterized in that said measurement circuit comprises: a measurement resistive two-terminal network (DM) presenting variable resistance and connected between said conductive probe and a ground of the circuit; and a calculation unit (UC) for generating said signal representative of a contact resistance between said conductive probe and said surface of the sample as a function of a voltage (Vs) across the terminals of said measurement resistive two-terminal n

Abstract: An aircraft comprising rotors and/or propellers rotated by a shaft and including a power unit. The distributed electric power unit is formed by stacked electric power elements, each conferring, on the shaft, a fraction of the total power necessary; the distributed electric power unit is in direct engagement with the shaft, with no movement transmission mechanism inserted between the unit and the shaft; each electric power element is directly connected to the rotation shaft and comprises a fixed stator, a moving rotor and a mechanical or electromagnetic free wheel in direct engagement with the shaft, said moving rotor co-operating with the free wheel to be coupled to the rotation shaft during normal operation of the electric power unit and to be disconnected from the shaft in the event of the failure of the electric element.

Abstract: Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said CND unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: Pr=the nominal mechanical power necessary for the propulsion and/or for the lifti

Abstract: The invention relates to a rotary- or fixed-wing aircraft comprising one or more rotors and/or one or more propellers, in which the rotor(s) and/or propeller(s) are rotated at a variable or constant speed by at least one shaft (Rp1, Rp2, Rp, RAC, H), and the aircraft includes a power unit (GEMD) configured to propel and/or lift the aircraft by rotating the shaft.

Abstract: Apparatus for measuring the local electrical resistance of a surface, the apparatus comprising: a DC voltage source for applying a bias voltage (Vpol) to the sample (E) for characterizing; a measurement circuit (CM) capable of being connected to a conductive probe suitable for coming into contact with a surface (SE) of said sample in order to generate a signal (S) representative of a contact resistance between said conductive probe and said surface of the sample; and a control device (CMD) for controlling said measurement circuit; the apparatus being characterized in that said measurement circuit comprises: a measurement resistive two-terminal network (DM) presenting variable resistance and connected between said conductive probe and a ground of the circuit; and a calculation unit (UC) for generating said signal representative of a contact resistance between said conductive probe and said surface of the sample as a function of a voltage (Vs) across the terminals of said measurement resistive two-terminal n