Abstract: An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).

Abstract: Aircraft landing gear (10) provided with at least one contact means (20) for making contact with a contact surface (S). The landing gear includes energy absorber means (30) provided with an inflatable airbag (31) secured to said contact means (20), said energy absorber means (30) being provided with control means (32) and with at least one inflation means (32) for inflating said airbag (31) under the control of said control means (32), said energy absorber means (30) including adjuster means (34) for adjusting the pressure that exists inside (INT) said airbag (31).

Abstract: An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).

Abstract: A hybrid helicopter (1) includes a central fuselage (2) defining a front end (3) and a rear end (4), the hybrid helicopter (1) having a main lift rotor (10), an additional lift surface (20), a mechanical interconnection system (40), and at least one turbine engine (61, 62) for continuously driving the main rotor (10) in rotation. Furthermore, the main rotor (10) is mechanically connected to the mechanical interconnection system (40) by rotary rotor mast (12), and the additional lift surface (20) is arranged at the rear of the hybrid helicopter (1) between the rotor mast (12) and the rear end (4) of the fuselage (2), each end zone (21?, 22?) of the wings (21, 22) of the additional lift surface (20) being provided with a vertical element (23, 24) fitted with a rudder (23?, 24?).

Abstract: A rigid hydraulic control shaft for conveying a fluid from a hydraulic valve to a hydraulic chamber of a propeller comprises a main segment. The main segment has a hollow rigid outer tube and a solid rigid inner bar. The inner bar has an outer periphery and at least one longitudinal groove disposed along the outer periphery. The outer periphery is configured to move in rotation and translation with an inner periphery of the outer tube. The main segment is configured to move in rotation and in translation with a piston disposed adjacent to the hydraulic chamber.

Abstract: Aircraft landing gear (10) provided with at least one contact means (20) for making contact with a contact surface (S). The landing gear includes energy absorber means (30) provided with an inflatable airbag (31) secured to said contact means (20), said energy absorber means (30) being provided with control means (32) and with at least one inflation means (32) for inflating said airbag (31) under the control of said control means (32), said energy absorber means (30) including adjuster means (34) for adjusting the pressure that exists inside (INT) said airbag (31).

Abstract: A hybrid helicopter (1) includes a central fuselage (2) defining a front end (3) and a rear end (4), the hybrid helicopter (1) having a main lift rotor (10), an additional lift surface (20), a mechanical interconnection system (40), and at least one turbine engine (61, 62) for continuously driving the main rotor (10) in rotation. Furthermore, the main rotor (10) is mechanically connected to the mechanical interconnection system (40) by rotary rotor mast (12), and the additional lift surface (20) is arranged at the rear of the hybrid helicopter (1) between the rotor mast (12) and the rear end (4) of the fuselage (2), each end zone (21?, 22?) of the wings (21, 22) of the additional lift surface (20) being provided with a vertical element (23, 24) fitted with a rudder (23?, 24?).

Abstract: A rigid hydraulic control shaft for conveying a fluid from a hydraulic valve to a hydraulic chamber of a propeller comprises a main segment. The main segment has a hollow rigid outer tube and a solid rigid inner bar. The inner bar has an outer periphery and at least one longitudinal groove disposed along the outer periphery. The outer periphery is configured to move in rotation and translation with an inner periphery of the outer tube. The main segment is configured to move in rotation and in translation with a piston disposed adjacent to the hydraulic chamber.

Abstract: A rope or cord system on a helicopter comprises a beam (18) fixed to the helicopter floor or roof in the vicinity of an opening (12). Ropes or cords (16) for the lowering to the ground of intervention personnel are attached to bolts (20) by rings (22). The operation of a handle (24) makes it possible to simultaneously and instantaneously release or jettison all the ropes (16) by pivoting a clasp (32) into each of the bolts in opposition to a spring (36). For this purpose the handle (24) simultaneously operates the pivoting latches (42), which cooperate with the clasps by complimentary cam surfaces (40, 46).