Abstract: A method for optimizing the architecture of the power supply of a load, includes the following steps: determination of a mission profile (16) sizing according to the power required by the load over time; definition of the sources of energy storage for hybridization; association of a characteristic behavior model with each source of energy storage; determination of the couples of sources of energy storage that can generate the mission profile with a minimum mass; and determination, from the potential couples of sources of energy storage, of the couple with the weakest mass.

Abstract: A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.

Abstract: A pipe for forming air flow pipelines in a structure that includes a flexible tube made from composite material, the tube having, on the length of same, sections for which the wall of the tube is stiffened by means of structural elements made from a rigid composite material incorporated into the wall of the tube. The structural elements are configured and arranged at the surface of the tube in such a way as to form a lattice framework surrounding the wall of the tube. The pipe further includes electrical conductors, disposed longitudinally on the wall of the pipe, the electrical conductors having a straight path at the stiffened sections of the pipe and a meandering path at certain of the non-stiffened sections of the pipe, the meandering allowing the conductor to tolerate the possible twisting of the pipe when it is installed in the structure.

Abstract: A device (10) for the electric power supply of a load (11), includes at least two energy storage elements (13, 14), elements for determining the power needs of the load (11), elements (16, 17) for monitoring each energy storage element (13, 14), which are able to provide information about a maximum instantaneous power of each energy storage element (13, 14), a calculation body (19) for determining a maximum secured power according to the electromotive force (Ebat(t)) and the resistance (Rbat(t)) of the Thévenin model, a maximum specified current and a maximum specified voltage, and elements (Cbat(t), Csc(t)) for controlling each energy storage element (13, 14), the elements being adjusted over time according to the power needs of the load (11) and the maximum secured power of each energy storage element (13, 14).

Abstract: The aircraft (10) includes: at least one electric motor (135); at least one stand-alone electrical power supply (110, 120) supplying power to the electric motor; propulsion elements (130) referred to as “auxiliary propulsion elements”, included in the group including: a stand-alone electrical power supply (130) supplying power to the electric motor, a power supply converting thermal energy into electrical energy and supplying power to the electric motor, and an internal combustion engine; and a structure (100) configured to integrate each electric motor, each stand-alone electrical power supply and the auxiliary propulsion elements, the parameters of the structure being substantially identical regardless of the auxiliary propulsion elements. A method of fitting out such an aircraft is also described.

Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: A method for processing local information acquired by a virtual representation and a device having an inertial unit and an image sensor. At least one image of a real environment of the device is captured. The localization of the device in the virtual representation, corresponding to the localization of the device in the real environment, is obtained by correlating the portions of the captured image and portions of the virtual representation, The inertial unit determines the displacement of the device. The localization of the device in the virtual representation is modified as a function of the displacement so that the real position of the device corresponds, during the displacement, to the localization of the device in the virtual representation.

Abstract: In order to produce a part (16) from a composite material, which is conductive at least on one of the surfaces thereof, the method consists of: the conductive overstitching (30) of a preform (20) of the part using electrically or thermally conductive threads (31, 32) with substantially parallel stitch lines (34) oriented in at least two intersecting directions. The parts obtained are adapted for the production of aircraft structures that may be subjected to lightning strikes and allow return currents from the electrical or electronic aircraft equipment and/or the discharge of heat by conduction.

Abstract: Disclosed is a method for measuring movement and/or deformation of a study part subjected to an external stress, the method implementing a color digital image acquisition device and image correlation unit. The method includes: acquisition (250) of a plurality of color digital images of the surface of the study part by way of the color digital image acquisition device during the application of an external stress on the study part, and processing (260) of the color digital images acquired in the step of acquisition of a plurality of color digital images so as to highlight contrasting details on variable scales.

Abstract: A transportation device to transport a passenger from door to door. The device includes a platform equipped with wheels to move along the ground, and at least one private seat having a power source and a connector. The private seat is secured to the platform. The transportation device further includes a connected virtual reality unit that can construct a virtual environment for the passenger. Additionally, a method for transporting a passenger using the transportation device.

Abstract: A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.

Abstract: An ultrasonic probe for contact measurement of an object and its manufacturing process. The ultrasonic probe has ultrasonic sensors securely fastened to a first face of a substrate. The opposite face of the substrate defines a measurement surface having a shape that is the imprint of the surface of the object to be measured to closely follow the latter when the surface of the object is brought into contact with the measurement surface.

Abstract: A method of managing a power demand to assure the operation of a pilotless aircraft. The aircraft includes an internal combustion engine supplying a maximum principal power which can vary. The management method is particularly suitable for a rotary wing pilotless aircraft. It guarantees the storage of an amount of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine. This recovery energy enables the control of autorotation and landing of the aircraft.

Abstract: A method for drilling through an assembly forming a stack of at least two different materials uses a drill bit having at least a first cutting edge and a second cutting edge inclined in an axial plane of the drill bit so that the end of the drill bit has a projecting conical shape. The first cutting edge is configured to drill a first material. The second cutting edge is made differently from the first cutting edge, to drill a second material. A first rotational drive axis of the drill bit is laterally offset during the drilling by an offset distance D relative to the axis of the drill bit in a direction opposite the first cutting edge when the drill bit is drilling through the first material, and alternately, in a direction opposite the second cutting edge when the drill bit is drilling through the second material.

Abstract: A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.

Abstract: An EMC filtering device comprises a printed circuit comprising at least two parallel layers of a high-permittivity material, which are positioned between two layers of an insulating material that are parallel to one another and to the high-permittivity material layers. A core made of a magnetic material comprises three cylindrical arms passing perpendicularly through the high-permittivity and insulating material layers. At least two windings winding around the first arm of the magnetic material core, the windings and the first arm forming a first coil. At least two windings winding around the second arm of the magnetic material core, the windings and the second arm forming a second coil. The two coils being coupled coils.

Abstract: A three-dimensional structural framework having inflatable rings and a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable rings in an inflated state. Shape-stabilizing elements are provided to stabilize the shape of the structural framework in space. Two inflatable rings are connected by at least one shape-stabilizing element. The structural framework is preferably used to produce stratospheric balloons.

Abstract: An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.

Abstract: A high-impedance passive device to radio-electrically decouple two antennas operating at least partially within a common frequency band and arranged on a surface of the carrier structure. A substrate of the device has a flexible dielectric material layer having a predetermined thickness with patches of conductive material arranged on its surface and a layer to attach the device onto the surface of the carrier structure. The patches having predetermined shape and arrangement. The body of the substrate separates the dielectric layer from the surface of the carrier structure. The substrate thickness is determined based on the size, number, and arrangement of the patches, and further it is based on the aerodynamic constraints imposed on the device. The device having an impedance to cause the desired decoupling in the common frequency band.