Airbus Helicopters Deutschland Gmbh

Endress + Hauser Process Solutions Ag

Endress + Hauser Gmbh + Co. Kg

Stefan Probst

Christian Seiler

Marc Fiedler

Sebastian Mores

Werner Thoren

Christian Wehle

Marc Nothen

Frank Loeser

Ingo Laible

Alessandro D'Alascio

Michael Matt

Marius Bebesel

Uwe Kiesewetter

Alexander Mueller

Justus Steger

Marco Schneeberger

Qinyin Zhang

Uwe Mannbar

Johannes Frese

Philipp Walch

Wolfgang Huenecke

Gottfried Huebner

Antonia Horstmann

Johann Barnerssoi

Christian Buxel

Hartmut Jutt

Romed Schweizer

Thomas Wuerfl

Rainer Grodau

Robert Seiler

Roland Mueller

Frank LÖSER

Wolfgang Hünecke

A modular subfloor system comprises first longitudinal structural frames, lateral regions, and a modular tank system that is connected to the first longitudinal structural frames. The modular tank system comprises a bottom shell, an upper panel, second longitudinal structural frames arranged between the bottom shell and the upper panel and transversal structural frames that are arranged between the bottom shell and the upper panel. The transversal structural frames and the second longitudinal structural frames form compartments. The modular tank system further comprises tank bladders arranged in at least some of the compartments and sealing elements that seal the upper panel, the bottom shell, and the at least some of the compartments of the modular tank system.

Modular subfloor arrangement for an aircraft

A rotary wing aircraft comprising a fuselage tail boom, a tail cone and an interface frame, the interface frame in turn having a connecting structure directly attached to the tail cone by means of a tail cone mechanical connection and a connecting sleeve fitting axially the fuselage tail boom, the connecting sleeve and the fuselage tail boom being directly attached by means of a one boom mechanical connection; the interface frame thereby joining the fuselage tail boom and the tail cone.

Rotary wing aircraft with an interface frame joining the fuselage tail boom and the tail cone

A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.

Shrouded rotary assembly from segmented composite for aircraft

An aircraft comprising a rear opening and a rear door to close such rear opening, wherein the rear door is attached to the fuselage of the aircraft by means of an arrangement having two links due to which the rear door can be displaced longitudinally and in elevation up to a position at the interior of the fuselage.

Aircraft with inwardly foldable rear door

A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.

Tail assembly for a rotorcraft, rotorcraft and method of manufacture of a strengthened tail assembly

A method for setting energy supply parameters of a field device electrical current supply module. The field device electrical current supply module is connected, in such case, exclusively to one field device. The connected field device can be supplied electrical energy by the field device electrical current supply module. In the method, a field device type of the connected field device is identified first by the field device electrical current supply module. Then, a parameter setting of at least one energy supply parameter of the field device electrical current supply module is automatically read out from a database and this is loaded into the field device electrical current supply module.

Method for setting parameters of a field device electrical current supply module

An aircraft with a fuselage that comprises a framework structure having at least one hollow frame that is integrally formed in one piece and comprises fiber reinforced polymers, the at least one hollow frame defining an integrated ventilation air duct that is adapted for guiding ventilation air into the aircraft.

Aircraft framework structure with integral ventilation air duct

An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.

Aircraft with an air intake for an air breathing propulsion engine

A rotary wing aircraft with a tail rotor in a rotor duct of a shroud. A bumper projects from a lower transition region of said shroud, said lower transition region having a left hand and a right hand lower transition edge between respectively the left hand and the right hand annular surface around the rotor duct and the bumper. Upper leading edges of a vertical fin and of said shroud are provided with left hand and right hand trailing edges. A projection of the upper transition edge to an upright longitudinal plane is defined by a spline curve through points Pi (i=1 . . . 5) and a projection of the lower transition edge to the plane is defined by a spline curve through points Pi (i=6 . . . 10) defined by their respective coordinates (xi, zi) relative to a centre of the shrouded tail rotor.

Rotary wing aircraft with a tail shroud

A method for monitoring charge level or remaining capacity of a battery pack, a disposable battery or a rechargeable battery, which is used to supply energy for an automation technology, field device having a data storage unit associated with the battery pack, disposable battery or rechargeable battery. Specific information about the battery pack, disposable battery or rechargeable battery is stored in the data storage unit and process-specific and operation-specific information about energy consumption is written to the data storage unit. In the case of the battery pack, disposable battery or rechargeable battery being used in a second automation technology field device, remaining service life of the battery pack, the disposable battery or the rechargeable battery is calculated and output on the basis of the process- and operation-specific information.

Method for monitoring the state of charge, or remaining capacity, of a disposable or rechargeable battery

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 apparatus having an electronics unit and a battery unit for energy supply of the electronics unit, wherein the battery unit has a first formed part, and wherein the electronics unit has a second formed part. The first and second formed parts are connectable with one another, wherein, by orienting, especially by rotating, the first formed part, respectively the second formed part, the first formed part and the second formed part are connectable with one another in different installed positions, and wherein the energy supply of the electronics unit occurs from the battery unit as a function of the installed position, in which the first formed part is connected with the second formed part.

Transport securing device for a battery unit

A method for integrating a field device of automation technology into a radio network composed of a plurality of field devices, wherein the field device to be integrated switches, or is switched, at start-up, respectively, first start-up, into a special start-up mode, wherein, in the special start-up mode, a peer to peer connection to a service device or to a selected field device is produced on a specific channel and wherein integration data are transmitted from the service device or the selected field device to the field device to be integrated and/or diagnostic data of the field device are transmitted to the service device or to the selected field device.

Method for servicing a field device of automation technology in a radio network

A method, in the case of which it is monitored in a wireless adapter connected to a field device whether, in the context of communication with the field device, a status change of the field device is being reported. In case a status change has been reported, the wireless adapter queries for expanded status information of the field device. The expanded status information is transmitted event-controlled from the wireless adapter to a superordinated communication unit and provided through such to an evaluation tool, in case a comparison of the expanded status information with a status pattern adapted specifically for the field device shows that the relevant, expanded status information should be evaluated.

Growing community of inventors

Weil am Rhein, Germany

Stefan Probst