Airbus Operations Gmbh

Airbus Deutschland Gmbh

Michael Kordt

Vitalij Werthmann

Marianne Jacoba Reijerkerk

Michael Enzinger

Vitalij Wehrtmann

A system and method for minimizing buffeting in the case of an aircraft. Buffeting load control elements are provided in airfoils of the aircraft are arranged to be at least partly moved out of the airfoils by a control to reduce buffeting loads acting on the aircraft.

System and method for minimising buffeting

A wind tunnel balance, with a tunnel wall adaptor configured to fasten the wind tunnel balance to a wall of a wind tunnel, an actuator housing connected to the tunnel wall adaptor, a plurality of force sensors arranged between the actuator housing and the tunnel wall adaptor and which are configured to detect forces acting on the actuator housing, a pivot coupling, by means of which an airfoil model of an aircraft can be pivotably coupled to the actuator housing, and a plurality of piezoelectric actuators arranged in the actuator housing and which are configured to controllably deflect an airfoil model mounted on the pivot coupling in three spatial directions.

Wind tunnel balance and system with wing model and wind tunnel balance

A device and a method for calibrating load sensors which are provided at least one load cross-section of an aerofoil or control surface of an aircraft, the load sensors being calibrated on the basis of load coefficients (&#x3b1;) of the load sensors, which load coefficients a calculation unit calculates by evaluating a linear system of equations formed by means of mechanical loading of the aerofoil or control surface.

Method and device for calibrating load sensors

A device for adapting aerodynamic characteristics of a wing element, includes a winglet, movably attachable to a wing element. The winglet or parts of the winglet may be rotatable in relation to the wing element such that an associated rotary axis with a main direction of extension of the wing element encompasses an angle that differs from an angle of 90&#xb0;. In addition, a method is disclosed.

Concept of a variable winglet for lateral load reduction for combined lateral and vertical load reduction, and for improving the performance of means of locomotion

The present invention provides a method and a calculation system for an aircraft, with at least one sensor for detecting aeroelastic and flight-mechanical momenta of the aircraft, for detecting positions and movements of control surfaces of the aircraft or for detecting speeds of gusts of wind acting on the aircraft and comprising a calculation unit which calculates characteristic quantities of passenger comfort and cabin safety as well as momenta of the aircraft as a function of the sensor data provided by the sensors and a non-linear simulation model of the aircraft.

System and method for determining characteristic parameters in an aircraft

A device for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort, in an airplane having at least one sensor, a regulation unit connected to the sensor, and at least one actuator controlling, guiding and/or regulating surfaces of the aircraft. The controller modifies the rigid body modes and/or the one or more elastic modes of the aircraft. With only one sensor signal of a sensor, which is preferably an acceleration signal, an arbitrary number and an arbitrary combination of rigid body modes and/or elastic modes, respectively, may specifically be modified, and the modes obtained are not influenced.

Growing community of inventors

Hamburg, Germany

Michael Kordt