Abstract: A hybrid drive system for aircraft, in particular helicopters, with at least one energy generating module having an internal combustion engine and a generator that can be powered by the latter to generate electrical energy, and at least one electric motor for powering a drive means of the aircraft.

Abstract: The rotors of a helicopter are directly connected with electric high-torque motors, and are powered by the latter. Energy generation and rotor drive are separate from each other. The high-torque motor of the main rotor is pivoted to the cabin canopy, so that it can be tilted together with the main rotor.

Abstract: The rotors of a helicopter are powered by electric motors. The electrical energy required for this purpose is produced by a motor-generator unit, which comprises one or more internal combustion engines. The motor-generator unit can be secured under the cabin floor. This yields a hybrid helicopter that can set the rotational frequency of the rotors within a large interval.

Abstract: The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.

Abstract: An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.

Abstract: A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area.

Abstract: The invention relates to a method for controlling a rotary wing aircraft with at least one main rotor, comprising a rotor head and rotor blades (12), arranged such that each rotor blade (12) is supported to be able to pivot or twist around the lengthwise axis of its blade on the rotor head and has at least one control flap (14) that can be deflected. According to the invention, the rotary wing aircraft is controlled solely by changing the respective blade pitch angle (X) by means of changing the flap control angle (Y) of the assigned control flaps (14) by the resulting blade pitch angle (X3) being set by applying the resulting flap angle (Y4) to the control flap (14), and the flap angle (Y4) being computed using an algorithm, the input quantities comprising the flap control angle (Y1) depending on the pilot primary control and the flap correction angle (Y2) depending on the secondary control.

Abstract: An integratable sensor for an airfoil of an aircraft such as an airplane and a helicopter comprises a sensor capsule, in whose inner chamber a measuring element for measuring an environmental parameter is situated. A capsule carrier is implemented to accommodate and removably attach the sensor capsule and is integratable in an airfoil of an airplane or a helicopter. Elastic contact elements are used for secure electrical connection of the sensor capsule to the capsule carrier. The sensor capsule is replaceable, while the capsule carrier is permanently integrated in the airfoil, in particular in a rotor blade. The measuring element is, for example, a pressure sensor.

Abstract: An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement is arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.

Abstract: A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area.

Abstract: An integratable sensor for an airfoil of an aircraft such as an airplane and a helicopter comprises a sensor capsule, in whose inner chamber a measuring element for measuring an environmental parameter is situated. A capsule carrier is implemented to accommodate and removably attach the sensor capsule and is integratable in an airfoil of an airplane or a helicopter. Elastic contact elements are used for secure electrical connection of the sensor capsule to the capsule carrier. The sensor capsule is replaceable, while the capsule carrier is permanently integrated in the airfoil, in particular in a rotor blade. The measuring element is, for example, a pressure sensor.