Abstract: 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.

Abstract: 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.

Abstract: 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 (?i) 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.

Abstract: 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.

Abstract: 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°. In addition, a method is disclosed.

Abstract: 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.

Abstract: 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 (?i) 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.

Abstract: A method and a system for the integrated determination of aerodynamic data, dynamic load distributions and local accelerations in an aircraft, in particular in an airplane, in flight. Sensors for directly and indirectly detecting aerodynamic parameters, local acceleration and/or structural loads of the aircraft are provided at the aircraft. A calculation unit, which is provided within the aircraft or at the ground station, calculates based on a non-linear simulation model of the aircraft the aerodynamic data, local accelerations and dynamic load distributions of the aircraft depending on the detected aerodynamic parameters of the aircraft. The calculation may take place in real time.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a system for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor element 6, at least one actuator, an active material integrated in the fuselage structure or a supporting active force or position set system, and at least one control unit 11. According to the invention, the amplitude characteristic and/or a phase characteristic of fuselage structure design loads, accelerations and/or deformations are/is modifiable such that a reduction in the design load or acceleration acting on a fuselage structure 5 of a means of transport occurs, as a result of which a significant reduction in weight or improvement in comfort of a means of transport is possible in a particular frequency interval.

Abstract: The present invention relates to a device for adapting aerodynamic characteristics of a wing element (1), wherein the device comprises a winglet (2), wherein the winglet (2) is movably attachable to the wing element (1), and wherein the winglet (2) or parts of the winglet is or are rotatable in relation to the wing element (1) such that an associated rotary axis (7) with a main direction of extension (6) of the wing element (1) encompasses an angle that differs from 90°.

Abstract: 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.

Abstract: The application describes a device 21 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 1,22 having at least one sensor means 8,27 as well as a regulation unit 33,42,66 connected to the one or the several sensor means 8, 27 and at least one actuator acting upon controlling, guiding and/or regulating surfaces 40 of the aircraft. By means of the controller 33,42,66, at least one respective rigid body mode and/or at least one elastic mode of the aircraft may be modified, whereby with only one sensor signal of a sensor means 8,27, which is preferably an acceleration signal, an arbitrary number and an arbitrary combination of rigid body modes or rigid body modes and/or elastic modes or modes, respectively, may specifically be modified, and the modes to be obtained are not influenced.

Abstract: The invention relates to a system for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor means 6, at least one actuator, and at least one control unit 11. According to the invention, an amplitude characteristic and/or phase characteristic of loads acting on the fuselage structure are/is modifiable such that a reduction in the load acting on a fuselage structure 5 of a means of transport occurs, as a result of which a significant reduction in the loads acting on the fuselage structure of a means of transport is possible in a particular frequency interval. Furthermore, the invention relates to a method for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor means 6, at least one actuator, and at least one control unit 11.