Airbus Helicopters

Eurocopter

Eurocopter France

Liebherr-aerospace Lindenberg Gmbh

Jacques Serge Bellera

Philippe Alain Rollet

Nicolas Queiras

Serge Joseph Mezan

Patrick Hellio

Marcelo Duval

Tobias Storz

A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

Method and a system for providing a rotorcraft with assistance in taking off

An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

Apparatus for sensing an elastic deformation of a hollow element

A method of the invention for controlling the pitch of the blades of a tail rotor of a rotary-wing aircraft includes the following operations:

Optimized method of controlling yaw for rotary-wing aircraft, and a system for implementing it

A flight control limiting system for a rotary-wing aircraft which generates servo-commands for at least one of a main rotor and a tail rotor. A set of first commands represents the position of at least one flight control which is movable between extreme positions, and may be controlled by the pilot. A set of second commands are generated by a flying aid system. The flight control limiting system limits the values of the set of second commands when the position of any of the flight controls is close to an extreme position, so that the servo-commands for that particular flight control corresponds to the set of first commands.

Flight control system for rotary-wing aircraft, especially for a

A cyclic stick system for a helicopter includes sensors for measuring at least one parameter representative of the current flight status of the helicopter. In response to the at least one parameter, the cyclic stick system either (1) continuously and automatically recenters the forces on the cyclic stick, thus canceling out the residual static forces, or (2) allows the pilot fully to feel the countering action of the elastic return device on the cyclic stick.

Force-gradient cyclic stick system for a helicopter

A rudder bar system for a helicopter controlled in yaw by acting on the tail rotor or an equivalent device has a capability, as a function of the parameters representative of the current flight status of the helicopter, of either automatically continuously recentering the forces on the rudder bar, which cancels out the residual static forces and gives the pilot a tactile sensation close to that given by a friction-type rudder bar, or allowing the pilot fully to feel the countering action of an elastic return device such as a spring.

Growing community of inventors

Aix-En-Provence, France

Jacques Serge Bellera