Airbus Helicopters

Airbus Helicopters Deutschland Gmbh

Airbus Deutschland Gmbh

Eads Deutschland Gmbh

Mtu Aero Engines Gmbh

Eurocopter

Eurocopter Deutschland Gmbh

Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Boris Grohmann

Stefan Storm

Thomas Lorkowski

Erwin Bayer

Rupert Pfaller

Thomas Rohr

Thibaut Marger

Pierre Estival

Christophe Tempier

Peter Jaenker

Marc Salesse-Lavergne

Andree Altmikus

Markus Bauer

Frank Hermle

Laurent Zamponi

Jean-Francois Hirsch

Bruno Chaduc

Johann Reichenberger

Gregor Paulmann

Peter Konstanzer

William Lagrevol

Nicolas Fontaine

Nicolas Avril

Jean-François Hirsch

Valerian Durand

Stephan Mangelsdorf

Christoph Maucher

Jens Klaubert

Axel Guse

Elif Ahci

Thomas Buro

Valérian Durand

An electromechanical actuator for electrical flight controls of an aircraft, the actuator comprising a transmission shaft, four electromechanical conversion members, each having a respective stator and rotor secured to the transmission shaft, and four control systems, each dedicated to respective ones of the electromechanical conversion members. The stator has teeth and windings surrounding at least one tooth, whereas the rotor is provided with permanent magnets. Each electromechanical conversion member is a flux-concentrating member and each winding is concentric and has a single layer. The electromechanical actuator is intended in particularly for controlling a hydraulic actuator via a mechanical transmission within an electrical flight control device of an aircraft.

Electromechanical actuator with stator teeth dimensioned to operate a saturation bend for electrical flight controls of an aircraft

A vehicle control system for controlling a vehicle and to a method of operating such a vehicle control system. The vehicle control system may include an inceptor adapted for controlling a servo-assisted control unit via a mechanical linkage, first and second force generating devices that are mechanically connected to the inceptor in parallel and provided for generating respective first and second forces that act in operation on the inceptor, a hands-on/off detection management unit, and a decoupling device that mechanically decouples the second force generating device from the inceptor based on a control signal from the hands-on/off detection management unit.

Vehicle control system for autonomous, remotely-controlled, or manual operation of a vehicle

A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.

Haptic alert mechanism for alerting an aircraft pilot, and an aircraft

A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor that is adapted for controlling a servo-assisted control unit of a vehicle control system, wherein the artificial force feel generating device comprises at least one force generating device that is mechanically connected to the inceptor for generating a tactile cue force acting in operation on the inceptor, and wherein a safety device is provided for limiting authority of the at least one force generating device, the method comprising at least the steps of: monitoring usage of the safety device during operation of the artificial force feel generating device, determining a current accumulated fatigue of the safety device on the basis of the monitored usage, and re-configuring the at least one force generating device on the basis of the current accumulated fatigue.

Method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system

An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, wherein at least one first force generating device and at least one second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.

Artificial force feel generating device for a vehicle control system of a vehicle and, in particular, of an aircraft

A blade () having an outer covering () defining a cavity (). A carriage () is arranged in said cavity (), the carriage () being provided with a torsion bar () and at least two arms () secured to the torsion bar (). The blade has one connection per arm provided both with an upstream guide gallery and with a downstream guide gallery, each arm extending transversely from an upstream end that slides in an upstream guide gallery to a downstream end that slides in a downstream guide gallery. At least one connection is a helical connection () obtained with the help of an upstream guide gallery () and the downstream guide gallery () of the segment () presenting distinct orientations, giving rise to movement in rotation (ROT) of the segment () under the effect of the carriage () moving in translation.

Adaptively-twistable blade, and an aircraft including such a blade

A control system () for controlling pitching stabilizer means of an aircraft, said system () being provided with at least one outlet shaft () and with a first actuator () and a second actuator (). The first and second actuators (and) are different, and the first actuator () is a slow actuator having a first driving portion that moves at a first speed, the second actuator () being a fast actuator having a second driving portion that moves at a second speed faster than the first speed, said control system () comprising a control device () connected to the first actuator () and to the second actuator () in order to cause said outlet shaft () to be driven either by the first driving portion () and/or by the second driving portion ().

System and a method for controlling pitching stabilizer means of an aircraft

An improved actuator arrangement for operating a driven element with different actuators. The actuator arrangement comprises a first actuator that drives a driven element in a first direction via a first output member and a second actuator that drives the driven element in a second direction opposite to the first direction via a second output member. The first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions. An additional connecting and supporting device is connected between the first and second output members to support the output members to bear transversal forces transversal to the moving direction and/or to bear pre-load force for pre-loading the actuators.

Actuator arrangement and control surface arrangement, especially for an aircraft

An electric circuit with one power amplifier (V) for at least two piezoelectric actuators (C, C), said piezoelectric actuators (C, C) being in preferably antagonist arrangement connected mechanically in series and being connected electrically with each other and operated or clocked by a control circuit, such as a pulse modulator circuit, for time-variant energizing of the piezoelectric actuators (C, C) in push-pull fashion, said power amplifier (V) being connected to a junction point between the two piezoelectric actuators (C, C), characterized in that said power amplifier (V) is connected to a one directional diode (D) and in that two buffer capacitors (CC) and two static resistors (R, R) are provided downstream the one directional diode (D) with regard to the power amplifier (V).

Electric circuit with power amplifier for piezoelectric actuators

Primary flight controls () for main and/or tail rotors () of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators () for control force amplification towards said main and/or tail rotor controls (). For each of the main and/or tail rotor controls () there is provided but one of the hydraulic servo actuators (), connected by one mechanical linkage () to one electro motor (), said one hydraulic servo actuator () being of the type having the one mechanical linkage () connected to its input () and its output () and the one electro motor () being of the direct drive type, the position of said electro motor () having a reference to said one mechanical linkage () and the torque delivered by said electro motor () to the hydraulic servo actuator () being related to the power consumption of said electro motor ().

Primary flight controls

The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (), at least one electric position sensor (') for said input signal (), at least one electric power supply (&#x2032;) and at least one controllable, electromechanical actuator (&#x2032;) fed by the at least one electric power supply (&#x2032;) and controlled by the at least one electric position sensor (&#x2032;). The mechanical input signal () is applied mechanically to the at least one controllable electromechanical actuator (&#x2032;).

Control system

A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.

Wing of an aircraft

A rotor blade including a rotor blade profile including a profile tip region, a profile trailing edge region including a trailing edge and a profile body having a profile core. A covering skin including an upper skin and a lower skin encase the profile core. A reversibly bendable flexural actuator including a first actuator end disposed at the trailing edge region of the rotor blade profile and a second actuator end projecting past the profile body toward the trailing edge. The second actuator end forms part of the trailing edge region and forms a movable rotor blade flap, the movable rotor blade flap being deformable into an arc-shaped rotor blade flap deflection upon a bending of the flexural actuator.

Rotor blade for a rotary wing aircraft

A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.

Growing community of inventors

Taufkirchen, Germany

Boris Grohmann