Abstract: In order to reduce the weight of a hybrid propulsion system for a multi-rotor rotary-wing aircraft, the system comprises at least one inverter configured to supply power in parallel to multiple electric motors intended to drive the corresponding propellers of the system.

Abstract: In order to reduce the weight of a hybrid propulsion system for a multi-rotor rotary-wing aircraft, the system comprises at least one inverter configured to supply power in parallel to multiple electric motors intended to drive the corresponding propellers of the system.

Abstract: The present invention pertains to a method for producing a frame for a working hull, specifically an aircraft fuselage wherein at least a part of the frame is in the form of a monolithic structure. The method includes the steps of draping unidirectional and multidirectional fabrics impregnated with resin on a form, placing inflatable bladders between the form and a counter form, closing a mold on the form, inflatable bladders and a counter-form, inflating the bladders to compress the fabrics and heat-set the resin impregnating the fabrics. Thereafter, the monolithic structure is removed from the mold.

Abstract: The invention relates to a device for reducing the damping flexibility of a suspension shock absorber for an undercarriage, in particular the main undercarriage of a helicopter, and a shock absorber and an undercarriage including it.The shock absorber is of the oleo-pneumatic type, and at least one of the incompressible and compressible fluids of the shock absorber is at least partially transferred from an expansion chamber (31) of the latter into a transfer chamber (42) of an accumulator (40) external to the shock absorber (1, 8), and in which the transfer chamber (42) is isolated from a return chamber (43) by a separating piston (41). The connection between the transfer chamber (42) and the corresponding expansion chamber (31) can be cut off by an electro-valve (44), in order to isolate the shock absorber (1, 8) from at least part of the low pressure gas chamber (34) of its expansion chamber (31).Application to the undercarriage equipment, in particular the main undercarriages of ship-borne helicopters.

Abstract: In order to reinforce a working hull, such as the fuselage of an aircraft and in particular that of a helicopter, a frame (C) is embodied made of a composite material in the form of a monolithic monobloc structure. This structure is constituted by a profile whose internal flange (16) and the external half-flanges (18) principally comprise unidirectional fibers which extend over its entire length. As a variant, the lower section of the frame is embodied separately in the form of a panel bordered over its entire periphery by lateral half-flanges which also principally comprise unidirectional fibers. After assembling the two sections of the frame, the half-flanges are then opposite each other in the elongation.