Airbus Helicopters Deutschland Gmbh

Eads Deutschland Gmbh

Eurocopter Deutschland Gmbh

Daimler Chrysler Ag

Airbus Operations (s.a.s.)

Marius Bebesel

Sebastian Mores

Uwe Kiesewetter

Alessandro D'Alascio

Rupert Pfaller

Rudolf Maier

Michael Geiss

Qinyin Zhang

Marco Schneeberger

Stefan Haisch

Stefan Probst

Peter Jaenker

Andree Altmikus

Gerhard Mueller

Martin Blacha

Christian Wehle

Peter Jänker

Christian Reichensperger

Klaus Kicker

Thomas Ziemann

Reinhard Pongratz

Henning Strehlow

Thomas Kneisch

Dieter Roth

Christoph Geyer

Klaus Schmidts

Reinhard Reischl

Wilhelm Ficker

Delphine Hertens

Stefanie Link

Frederic Le Chuiton

Markus Paschek

Klaus Rittel

Manfred Bernhard

Alessandro D'alascio

Frédéric Le Chuiton

A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding that accommodates at most one of the at least two rotor assemblies, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein the air inlet region exhibits in circumferential direction of the cylindrical air duct an undulated geometry.

Thrust producing unit with at least two rotor assemblies and a shrouding

An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Aircraft with an airframe and at least one electrically powered thrust producing unit

A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Multirotor electric aircraft with redundant security architecture

A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.

Multirotor aircraft with an airframe and a thrust producing units arrangement

A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

Multirotor aircraft with an airframe and at least one wing

A thrust producing unit for producing thrust in a predetermined direction, comprising a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis, the first and second rotor axes being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles with respect to the predetermined direction, the associated inclination angles being comprised in a range between &#x2212;60&#xb0; and +60&#xb0;, and preferably amounting to 0&#xb0;, and wherein the first rotor assembly is arranged outside of the internal volume of the shrouding.

A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis.

Propeller assembly with at least two propeller blades

A helicopter with a fuselage (), at least one engine, a roll axis, at least one main rotor, and at least one housing () mounted to said fuselage (). An air inlet () and an air outlet () are provided along at least a part of a circumference of the at least one housing (), said air inlet () and said air outlet () being formed by angularly offset and separate gaps between an inside segment () and an outside segment () essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor () with a plurality of airfoil blades () is provided radial inside said at least one housing () between said air inlet () and said air outlet (), said at least one rotatable compressor () being drivable by said at least one engine about a fan axis () and each chord of said airfoil blades () is essentially radial oriented with regard to said fan axis ().

Helicopter with cross-flow fan

A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element.

Advanced pitch stabilizer

An aerodynamic blunt aft body () of a helicopter fuselage with two strakes () along an aft surface () and/or respective left hand and right hand side fuselage surfaces (). Each strake () is defined by first and second intersection lines () resulting from intersections of horizontal planes (z) with the surface of the aft surface () or the respective left hand and right hand side fuselage surfaces (). The strakes are defined by a two or three dimensional spline () from the surface () towards the aft surface () inside said first and second intersection lines () and inside the bounding box ().

Aerodynamic, blunt aft body

The invention is related to a helicopter () comprising a main rotor (), a cycloidal rotor () and a rotating cylinder (). The rotating cylinder () extends along a longitudinal axis of a tail boom (). The cycloidal rotor () extends at least partly along said same tail boom () and rotates outside the rotating cylinder ().

Helicopter with cycloidal rotor system

A device for monitoring particle contamination in flowing hydraulic fluids includes a mechanism for particle counting and particle sizing. Further, a method for monitoring particle contamination in flowing hydraulic fluids: determines fluid flow velocity; counts particles in the hydraulic fluid passing the light barrier for a fixed period of time; and obtains particle size distribution by using a range of different trigger levels. The monitoring device is insertable into an A/C hydraulic system to enable an online-monitoring of degradation of fluid quality during normal flight operations or on the ground. The device and method help lower costs for A/C maintenance and increase A/C availability since necessary service actions can be scheduled strategically.

Device and method for monitoring the particle contamination in flowing hydraulic fluids

Device and process for oscillation insulation in a transmission path. The device includes a first body structured and arranged to undergo an oscillation movement, at least one rigid connection element, a second body connected to the first body via the at least one rigid connection element, and an actuator device attached to the at least one connection element. A sensor unit is arranged in an interface area of the at least one connection element, and a regulator unit, connected to the sensor unit, is arranged to control the actuator device to perform an elastic deformation equivalent to an oscillation movement of the first body. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Device and process for oscillation insulation in a transmission path

A piezoelectric expansion actuator for d33 piezoelements, which allows vibrations in structures to be suppressed. An expansion actuator () includes a piezoelectric stack (), which consists of d33 piezoelectric elements and is arranged between output elements (), which are attached to the surface of the structure (). The invention applies to a piezoelectric extension actuator, which is used to control vibrations in structures. Alternatively, in order to damp vibrations between the main gearbox of a helicopter rotor and the cellular structure of the cockpit, a power application point of the output element () is arranged at a distance from the corresponding end plate of the piezoelectric stack () in the axial direction (X).

Piezoelectric extension actuator

A method for avoiding a collision of a rotating rotor blade of a rotary-wing aircraft with a blade vortex, and a device for executing the method. An aerodynamic parameter of the rotor blade of a rotary-wing aircraft is controlled, (for example, variation of the angle of incidence of the blade or profile variation of the blade), using a signal processing device that includes at least one open-loop and/or closed-loop control device, in such a way that a collision of the rotor blade with blade vortices becomes avoidable. The frequency content from the signal of the sound-pressure sensors is rapidly and precisely found. The harmonics are progressively adapted. A lesser calculation requirement per step and increase accuracy, as compared with an FFT analysis, is provided.

Growing community of inventors

Augsburg, Germany

Marius Bebesel