Airbus Helicopters

Pierre Prud'Homme Lacroix

Olivier Bistuer

Louis Delorme

Patrice Garcin

Remy-Elian Arnaud

Jean Paul Renaud

Julien Azzarello

Arnaud Boulouis

A landing gear provided with at least two first rollers mounted on two first free-wheels respectively connected to a first skid and configured, during a landing phase, to lock in the elastic return direction when the first skid moves in a first direction from the first skid towards a second skid and to be free in the sink direction during movement in a second direction, at least two second rollers being mounted on two respective second free-wheels connected to a second skid and configured, during a landing phase, to lock when the second skid moves in the second direction and to be free during movement in the first direction.

Skid landing gear with rollers

A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.

Aircraft provided with a buoyancy system, and a buoyancy method

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.

Rotorcraft having at least one undercarriage with at least one inclined wheel, and a method

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.

Caliper braking system for aircraft landing gear having a plurality of brake disk clamping zones

A system for providing an aircraft with protection against hard landings, the system comprising friction energy absorber systems arranged at the points the aircraft will impact against the ground in the event of a crash. The friction energy absorber system has two energy absorber devices arranged between a base and a cover along two non-parallel deformation axes, a support secured to the base and suitable for moving in translation relative to the cover, and a friction device. The friction device is arranged between the cover and the support and it generates a friction force along a translation axis parallel to a deformation axis such that the energy absorber device, after being plastically deformed during a crash, remains in contact with the support and the cover.

System for protecting an aircraft against hard landings

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.

Growing community of inventors

Vitrolles, France

Pierre Prud'Homme Lacroix