Abstract: A rotorcraft having an airframe, the airframe carrying at least one rotor that contributes to providing the rotorcraft with lift and/or propulsion, the rotorcraft having at least one undercarriage. The at least one undercarriage comprises at least one inclined wheel undercarriage, the inclined wheel undercarriage having an undercarriage leg carrying at least one axle, the at least one axle carrying at least one wheel, the at least one wheel not being in contact with any other wheel, the at least one wheel presenting positive or negative camber when the at least one wheel touches the ground and independently of forces exerted by said airframe on the inclined wheel undercarriage.

Abstract: A braking system for aircraft landing gear including a plurality of clamping zones for clamping a brake disk. The braking system comprises an actuator, a caliper, a rim rotatable about an axis of rotation, and the brake disk, which is floatingly mounted relative to the rim. The caliper comprises a stationary inner support, a movable intermediate support, and an outer support that is hinged relative to the inner support. Under action of the actuator, the movable intermediate support moves and causes the brake disk to move so that the brake disk is clamped between the intermediate support and the outer support, and then causes the outer support to tilt so that the brake disk is clamped between the inner support and the outer support.

Abstract: A braking system for aircraft landing gear including a plurality of clamping zones for clamping a brake disk. The braking system comprises an actuator, a caliper, a rim rotatable about an axis of rotation, and the brake disk, which is floatingly mounted relative to the rim. The caliper comprises a stationary inner support, a movable intermediate support, and an outer support that is hinged relative to the inner support. Under action of the actuator, the movable intermediate support moves and causes the brake disk to move so that the brake disk is clamped between the intermediate support and the outer support, and then causes the outer support to tilt so that the brake disk is damped between the inner support and the outer support.

Abstract: An external anchoring harpoon for an aircraft in order to anchor the aircraft on an anchor grid of a platform, the external anchoring harpoon comprises a frame connected to the aircraft, a harpoon head, and a deployment device for deploying the harpoon head. The deployment device comprises a cable, a movement device for moving the cable connected to the frame, the cable being connected to the harpoon head and to the movement device. The deployment device also comprises a main telescopic strut and two secondary telescopic struts so as to enable the harpoon head to be centered under the aircraft and so as to enable the harpoon head to be anchored to the anchor grid.

Abstract: A rotorcraft having an airframe, the airframe carrying at least one rotor that contributes to providing the rotorcraft with lift and/or propulsion, the rotorcraft having at least one undercarriage. The at least one undercarriage comprises at least one inclined wheel undercarriage, the inclined wheel undercarriage having an undercarriage leg carrying at least one axle, the at least one axle carrying at least one wheel, the at least one wheel not being in contact with any other wheel, the at least one wheel presenting positive or negative camber when the at least one wheel touches the ground and independently of forces exerted by said airframe on the inclined wheel undercarriage.

Abstract: An external anchoring harpoon for an aircraft in order to anchor the aircraft on an anchor grid of a platform, the external anchoring harpoon comprises a frame connected to the aircraft, a harpoon head, and a deployment device for deploying the harpoon head. The deployment device comprises a cable, a movement device for moving the cable connected to the frame, the cable being connected to the harpoon head and to the movement device. The deployment device also comprises a main telescopic strut and two secondary telescopic struts so as to enable the harpoon head to be centered under the aircraft and so as to enable the harpoon head to be anchored to the anchor grid.

Abstract: A rotorcraft (1) having a feed unit for feeding fuel to a power plant (13) of the rotorcraft (1). A middle floor (12b) is securely engaged with at least two frames (9a, 9b) of the fuselage, and being load-bearing relative to general forces supported by the fuselage. A bottom compartment (7) of the rotorcraft (1) does not have the load-bearing covering (8) of the fuselage, the bottom face of the fuselage being open to the outside providing the bottom compartment (7) with a bottom (17) open to the outside of the rotorcraft. The bottom face of the middle floor (12b) forms an anchor member for suspending at least one fuel tank (25, 26) that is accessible from outside the fuselage via said open bottom (17).

Abstract: A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).

Abstract: A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).

Abstract: A rotorcraft (1) having a feed unit for feeding fuel to a power plant (13) of the rotorcraft (1). A middle floor (12b) is securely engaged with at least two frames (9a, 9b) of the fuselage, and being load-bearing relative to general forces supported by the fuselage. A bottom compartment (7) of the rotorcraft (1) does not have the load-bearing covering (8) of the fuselage, the bottom face of the fuselage being open to the outside providing the bottom compartment (7) with a bottom (17) open to the outside of the rotorcraft. The bottom face of the middle floor (12b) forms an anchor member for suspending at least one fuel tank (25, 26) that is accessible from outside the fuselage via said open bottom (17).

Abstract: Surface-area safety means (10) comprising a barrier net (20) and at least one fastener means (30), each fastener means (30) having a fastener strap (40) fastened to a segment (25) of said barrier net (20) and co-operating with a fastener member (50) suitable for fastening said fastener strap (40) to said structure (2). The fastener means (30) also include a tensioning strap (60) fastened thereto, said tensioning strap (60) including at least two tensioning eyelets (61), said fastener strap (40) having a securing system (200) for securing it to a tensioning eyelet (61) and securing the fastener strap (40) to the tensioning strap (60) by passing through a particular tensioning eyelet in order to tension said barrier net (20) to the tension corresponding to the particular tensioning eyelet.

Abstract: A method of minimizing the consequences for the occupants of a rotary wing aircraft (1, 10) of an off-specification landing with forward and/or downward acceleration vectors. The aircraft (1, 10) extends along an anteroposterior longitudinal plane of symmetry (4) in elevation separating a first side (5) of said aircraft (1) from a second side (6) thereof. Said rotary wing (10) comprises at least one rotor (11) driven in rotation by a main gearbox (20) and being provided with a plurality of blades (12). Said main gearbox (20) being fastened to a structure (30) of said aircraft (1) by a plurality of fastener elements (40) comprising at least one first fastener element (51, 52) disposed on said first side (5) and at least one second fastener element (61, 62) disposed on said second side (6).

Abstract: A method of minimizing the consequences for the occupants of a rotary wing aircraft (1, 10) of an off-specification landing with forward and/or downward acceleration vectors. The aircraft (1, 10) extends along an anteroposterior longitudinal plane of symmetry (4) in elevation separating a first side (5) of said aircraft (1) from a second side (6) thereof. Said rotary wing (10) comprises at least one rotor (11) driven in rotation by a main gearbox (20) and being provided with a plurality of blades (12). Said main gearbox (20) being fastened to a structure (30) of said aircraft (1) by a plurality of fastener elements (40) comprising at least one first fastener element (51, 52) disposed on said first side (5) and at least one second fastener element (61, 62) disposed on said second side (6).