Airbus Helicopters Deutschland Gmbh

Eurocopter Deutschland Gmbh

Gerald Kuntze-Fechner

Rupert Pfaller

Sebastian Mores

Markus Bauer

Horst Bansemir

Christian Wehle

Martin Ortner

Alois Wagner

Karl Bauer

Stefan Emmerling

Bernhard Enenkl

Alessandro D'Alascio

Ulrich Denecke

Victoria Otto

Hermann Sahlstorfer

Christine Mueller

Martin Schulz

Benedikt Bammer

Dieter Schimke

Elif Ahci

Christine Muller

Christeline Salmon

Julius Vogl

Eugen Rink

Gerhard Hausmann

Hans-Philipp Klam

Christine Müller

A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.

Control system for controlling at least collective pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft

A pitch control device for a ducted tail rotor of a rotorcraft. The pitch control device comprises a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and a control transfer member with a ring-shaped connector and at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor.

Pitch control device for a ducted tail rotor of a rotorcraft

A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.

Multi-blade rotor for a rotary wing aircraft

A blade attachment () for a bearingless main rotor of a helicopter with an airfoil blade (), a flexbeam () including a flexbeam body () and a flexbeam head () at an end of the flexbeam body (). A control cuff () encloses and extends along at least a predominant portion of the flexbeam (). A separable junction arrangement between the flexbeam head (), the control cuff () and the root end of the airfoil blade () is mechanical with removable fasteners. The removable fasteners comprise a main bolt () and at least one supporting bolt ().

Blade attachment for a bearingless rotor of a helicopter

An airfoil blade () of a bearingless rotor of a helicopter. Said airfoil blade () has a pitch axis from a tip end to a root end and said root end is provided with junction means for a separable junction arrangement of said airfoil blade () with a flexbeam head (), and a control cuff (). Said junction arrangement is mechanical with removable fasteners respectively removable connecting said root end of said airfoil blade () to said control cuff () and said flexbeam head (). Said root end comprises at least two openings () being asymmetric with regard to said pitch axis.

Connection joint for attaching an airfoil blade to a helicopter's bearingless main rotor

A partly cruciform flexbeam () of a bearingless main rotor system of a helicopter with a hub drive and an airfoil blade. The partly cruciform flexbeam () comprises a flexbeam head () with a flat bearing laminate at one end, a root end () opposed to said flexbeam head () and a flexbeam body () between said flexbeam head () and said root end (), said flexbeam body () being torsion soft with a substantially cruciform cross section. The invention is as well related to a method of manufacturing such a partly cruciform flexbeam ().

Partly cruciform flexbeam and method of manufacturing such a flexbeam

The invention relates to a separable blade attachment () for a bearingless main rotor of a helicopter with an airfoil blade (), a flexbeam () and a control cuff () enclosing at least a predominant portion of said flexbeam (). A separable junction arrangement between said flexbeam head (), said control cuff () and said root end of said airfoil blade () is mechanical with removable fasteners. A stiffened link () is provided between respective trailing edges () of the control cuff () and said airfoil blade ().

Separable blade attachment for a bearingless rotor of a helicopter

An aerodynamic blade attachment () for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade () having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (); a control cuff () enclosing and extending along said flexbeam () and a separable junction arrangement between said flexbeam (), said control cuff () and said root end of said airfoil blade (). Said junction arrangement is mechanical between said flexbeam (), said control cuff () and said root end of said airfoil blade (). Removable fasteners () connect said root end of said airfoil blade () and said control cuff () with said flexbeam (). Said junction arrangement comprises fairing means (and) encompass the removable fasteners () and said flexbeam ().

Aerodynamic blade attachment for a bearingless rotor of a helicopter

A rotor blade (), in particular of a main rotor of a rotary-wing aircraft, made of fiber-reinforced plastic includes a blade section () and a connecting section () for fastening the rotor blade () to a drive device () which includes a sleeve-shaped connecting device (), is further developed in that the connecting device () includes flat fiber layers (Sto S) running substantially in the plane of extension of the connecting section ().

Rotor blade in flat design

A rotor blade in a fiber-reinforced composite design for a tail rotor of a rotary wing aircraft (helicopter), with a blade section (') having a blade skin (a, r) and a blade body (b . . . g, s, t), which blade section (&#x2032;) forms an aerodynamically effective profile, with a blade tip () that faces away from the hub of a drive device of the rotor; and with a coupling section (&#x2032;) which faces towards the hub, with an attachment device () for a tension-torque-transmission element () and for a control tube () is improved in that the blade section (&#x2032;) and the coupling section (&#x2032;) include spar tapes (a . . . g) that go all the way through and that are made of unidirectional fiber material.

Rotor blade made of a fibre-reinforced composite material and production method for it

A rotor wing in a fiber-reinforced composite design including fiber layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade () that includes a blade skin () and a blade body (-) that includes an aerodynamically effective profile, with a tension-torque-transmission element () connected to it, which is designed in one piece with the rotor blade (), and with fiber layers (-) that extend through the tension-torque-transmission element () and are scarf-join in the rotor blade (), is improved in that the fiber layers (-) extend right through from the tension-torque-transmission element () to the blade body (-). Furthermore, a method for producing the rotor wing is described.

Rotor wing with integrated tension-torque-transmission element and method for its production

A tension-torque-transmission element () for a rotor blade of a rotary wing aircraft (helicopter), in particular for a fenestron blade of a tail rotor, with a connecting section on the blade side and a connecting section () on the axis side, with a connecting eye () on each connecting section, and with a torque-transmission section () that connects the connecting sections (), is improved in that the tension-torque-transmission element () is designed in a fiber-reinforced composite design including several layers (A to G) of a textile fabric. A method for producing such a tension-torque-transmission element () is also described.

Tension-torque-transmission element for a fenestron blade and method for producing it

A system comprising a rotor blade (), in particular of the tail rotor of a rotary wing aircraft, in a fiber-reinforced composite design, with a blade section () and with a coupling section () for attaching the rotor blade () to the hub of a drive device, and comprising a separate sleeve-shaped control tube () with an essentially hollow-cylindrical shaft (), with an also essentially tubular tie section () to tie the control tube () to the rotor blade () by sliding it onto its coupling section (), is improved in that the coupling section () of the rotor blade () and the tie section () of the control tube () comprise a cross-sectional shape for positive-locking interconnection of the rotor blade () and the control tube ().

Rotor blade with control tube

A twist element for a bearingless rotor is made mostly of composite fiber material and has a cross section with a substantially symmetric, flattened shape that has approximately the contour of a horizontal, central section of a double cone. In addition, a bearingless rotor having at least one such twist element, and a rotorcraft, particularly a helicopter, having at least one rotor with at least one such twist element are provided.

Twist element for a bearingless rotor

A rotor blade arrangement includes a rotor blade with a hollow blade chamber therein, and a flap module removably arranged and secured in the blade chamber. The flap module includes a module housing received in the blade chamber, an actuator arranged in the housing, a flap pivotably arranged at an edge of the housing, and a power transmission linkage connecting the actuator to the flap. The module housing is inserted through an opening into the blade chamber, so that the flap protrudes and forms a continuation of the aerodynamic contour of the blade. The flap may be a trailing edge flap at the trailing edge or a leading edge nose flap at the leading edge of the blade. The flap module does not change the center of gravity of the blade. The entire flap module can be easily removed from the blade for adjustment, inspection, maintenance, repair or replacement.

Growing community of inventors

Gmund am Tegernsee, Germany

Gerald Kuntze-Fechner