Airbus Helicopters

Airbus Helicopters Deutschland Gmbh

Liebherr-aerospace Lindenberg Gmbh

Patrick Hellio

Nicolas Queiras

Jean-Baptiste Vallart

Bernard Gemmati

Setareh Taheri

Jacques Serge Bellera

Bruno Chaduc

Patricia Gauthier

Karsten Krok

Marcelo Duval

Tobias Storz

A control system for an aircraft allowing a pilot of the aircraft to control aerodynamic means, the control system comprising a processing unit for generating control commands, the control commands being transmitted to control devices to modify a position of the aerodynamic means and to pilot the aircraft according to four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, the control system comprising a control member generating control setpoints, the control setpoints being transmitted to the processing unit generating the control commands under the dependency of the control setpoints, the control member being mechanically disconnected from the control devices.

Aircraft control system and associated aircraft

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 flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator.

Flight instrument displaying a variable rotational speed of a main rotor of an aircraft

For emergency piloting of a manual flight control system () of an aircraft (), in the event of flexible connection means () breaking, an upstream control device () takes authority over the electronic control unit () of series actuator (). An output pivoting quadrant () is subjected by a centering rod () to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant () forms a bearing point for the series actuator (), so that an emergency control actuate a airfoil surface ().

Emergency piloting by means of a series actuator for a manual flight control system in an aircraft

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Bouc Bel Air, France

Patrick Hellio